The Orbital Sciences X-34 was cancelled in the same NASA announcement as the vehicle in the previous article, on 1 March 2001, and the General Accounting Office gives both terminations the same cause, significant cost increases. Almost nothing else about the two is alike. The X-33 was enormous, used liquid hydrogen, carried an untried engine architecture, and failed a structural test in a way that made a photograph. The X-34 was small, burned kerosene, used an engine designed to be cheap rather than good, was finished, was towed and carried through the air by an airliner turned launch aircraft, and was cancelled without anything on the vehicle breaking at all. This is the thirty-fifth article in the X-Planes series, following the X-1, the X-2, the X-3, the X-4, the X-5, the X-6, the X-7, the X-8, the X-9, the X-10, the X-11, the X-12, the X-13, the X-14, the X-15, the X-16, the X-17, the X-18, the X-19, the X-20, the X-21, the X-22, the X-23, the X-24, the X-25, the X-26, the X-27, the X-28, the X-29, the X-30, the X-31, the X-32, and the X-33.

The difference that matters is not size or propellant. It is that the two programmes had different kinds of unknown. The X-33’s binding unknown was mass. Mass obeys a conservation law, a demonstrator can be weighed, and what came back was a number that did not close. The X-34’s binding unknown was cost, and cost obeys nothing.

The Research Question

The keystone is whether cost can be attacked as an engineering quantity, and what it costs to try.

The keystone is unusual for this series, and the difficulty should be stated at once. Every previous article has dimensioned an aircraft against a physical unknown. A drag rise, a heating rate, a divergence speed, a mass fraction. Those quantities have units, conservation laws and instruments. Cost has none of the three. It has no equation of state, it cannot be measured on the article, and every number attached to it is a forecast and none is a reading.

Why That Is Not a Reason to Refuse the Subject

The cost argument left physical fingerprints, and those can be computed. A programme that attacks cost does it by simplifying, and every simplification has a performance price with units. The X-34 chose an engine cooled by being destroyed, a propellant of lower specific impulse and about three times the bulk density of hydrogen and oxygen, an aeroplane to carry it to altitude instead of a launch pad, and a level of system testing that a later review found insufficient. Three of those four choices can be priced in kilograms, seconds and newtons. The fourth could not be priced at all until somebody tried to fly the vehicle.

The Question Behind the Question

A cheap demonstrator demonstrates that demonstrators can be cheap. Whether it demonstrates that an operational vehicle can be cheap is a separate claim and a much weaker one, and the distinction runs through this article.

The programme’s answer did not come from a test. It arrived as an arithmetic correction. Working from the restructure plan of June 2000, the General Accounting Office estimated the total requirement at about 348 million dollars against roughly 86 million budgeted in 1996, and the reason the agency gave was that reaching an acceptable level of risk needed more government technical insight, more hardware testing and more integrated assessment. Those are the things a low-cost programme removes.

Programme Origin

What the Agency Wanted and What It Bought

The X-34 belongs to the same family as the X-33 and answers a different half of the same question. Both were technology demonstrators under a reusable launch vehicle programme whose stated ambition was an order-of-magnitude reduction in the cost of reaching orbit. The X-33 pursued that by attacking the mass fraction, which is the physics of the problem. The X-34 pursued it by attacking the price of the hardware, which is not.

The contract went to Orbital Sciences in August 1996 as a fixed-price award of 49.5 million dollars, and with its later options and the engine project the vehicle was budgeted at about 86 million dollars, which set it against the X-33 at more than a billion. A ratio of that size is the argument in a single number, and testing whether the ratio survives contact with the vehicles is the work of the Where the Framing Breaks Down section.

The Company and the Method

Orbital Sciences had already done the thing the X-34 needed. The company operated an air-launched satellite booster carried by a modified airliner, so the carrier aircraft, the release mechanism, the separation problem and the operating culture existed before the X-34 did. A programme that reuses an existing carrier does not pay for one, and the saving it makes is a real one.

The Fastrac Engine

The Fastrac engine, also designated MC-1, was designed by a government laboratory to be cheap. It used a gas generator cycle, commercial parts where they would serve, a simplified turbopump, and a combustion chamber and nozzle cooled not by circulating its own fuel but by being consumed. An engine reported at around 1.2 million dollars in its development phase, against a production target near 350,000, is a different kind of object from the X-33’s engine, and the Sizing section takes it apart.

Sizing From First Principles

Three Quoted Numbers That Do Not Close

Begin with the engine figures as they are usually quoted, because they contain a discrepancy that turns out to be informative. They are a vacuum thrust of 60,000 pounds force, a vacuum specific impulse of 314 seconds, and a total propellant mass flow of 91.90 kilograms per second, as the engine’s usual specification gives them.

Those three quantities are related by the definition of specific impulse. Writing $F$ for thrust, $\dot{m}$ for mass flow and $g_0$ for standard gravity,

\[I_{sp} = \frac{F}{\dot{m} \, g_0}\]

in the form Sutton sets out for propulsion analysis.

Converting the thrust to 266,893 newtons, which is 266.9 kilonewtons, and substituting,

\[I_{sp} = \frac{266{,}893}{91.90 \times 9.80665} = 296.14 \ \text{s}\]

against a quoted 314, which is 5.69 percent adrift. A disagreement of that size in a quoted set is either an error or a distinction, and here it is a distinction, though not the one it first appears to be.

The Gap Is the Nozzle

The engine’s development status report resolves it. Ballard, Olive and Turner state that the engine runs at one rated power level, nominally 60,000 pounds force in vacuum with the 15:1 nozzle used for ground testing and slightly higher with the 30:1 nozzle built for the X-34. Their engine schematic gives both sets, 59,956 pounds force at 296 seconds for the 15:1 nozzle and 63,939 pounds force at 314 seconds for the 30:1 nozzle, at an engine mixture ratio of 2.17 in both. The usual quotation pairs the ground nozzle’s thrust with the flight nozzle’s impulse.

The same schematic gives the flows, 195.5 pounds per second into the main chamber and 7.10 into the gas generator, so the total is

\[\dot{m} = \left(195.5 + 7.10\right) \times 0.45359237 = 202.6 \times 0.45359237 = 91.90 \ \text{kg/s}\]

which is the quoted flow, now derived from the primary record. Put back through the definition with each nozzle’s own thrust, 284,415 newtons for the flight nozzle and 266,698 for the ground nozzle,

\[I_{sp}^{30} = \frac{284{,}415}{91.90 \times 9.80665} = 315.6 \ \text{s} \qquad I_{sp}^{15} = \frac{266{,}698}{91.90 \times 9.80665} = 295.9 \ \text{s}\]

with the superscript naming the area ratio, against the published 314 and 296. Each configuration closes on its own figures to within half a percent, and the 5.69 percent gap was never in the engine. The 296.14 seconds the quoted set implies is, to within rounding, the ground nozzle’s impulse.

The Cycle Is Smaller Than the Gap

A gas generator engine does not send all its propellant through the nozzle. A small stream is burned fuel-rich in a separate chamber to drive the turbopump, and the exhaust from that turbine is dumped overboard rather than expanded through the main nozzle, where it would contribute thrust. So the engine’s specific impulse is lower than its chamber’s.

Writing $\dot{m}c$ for the chamber flow and $\dot{m}{gg}$ for the gas generator flow, the schematic gives the generator’s share directly,

\[\frac{\dot{m}_{gg}}{\dot{m}} = \frac{7.10}{202.6} = 0.0350\]

which is 3.50 percent of the total. A gas generator typically spends between three and seven percent of the propellant it pumps, a range set out in Huzel and Huang’s design text on liquid propellant rocket engines, so the published cycle lands inside the range the architecture uses, near its economical end.

The same figures give what the cycle costs the vehicle. The chamber flow is 195.5 pounds per second, or 88.68 kilograms per second, and taking the turbine exhaust as contributing no thrust, the chamber alone would deliver

\[I_{sp,c} = \frac{F}{\dot{m}_c \, g_0} = \frac{284{,}415}{88.68 \times 9.80665} = 327.05 \ \text{s}\]

against the 315.59 seconds the whole flow gives, so

\[\Delta I_{sp} = 327.05 - 315.59 = 11.46 \ \text{s}\]

which is an upper bound, because a turbine exhaust duct recovers a little thrust. The two percentages are identical by necessity. The fractional impulse the cycle costs equals the fractional flow the cycle takes, exactly, because both are one minus the same ratio.

Two clusters below, on liquid rocket engines, turbopumps and combustion and on rocket nozzles, plumes and expansion, hold the gas generator and turbopump literature behind these figures. It includes the fuel-rich generator designs of Kwon et al 2004 and Jeon et al 2004 and the Fastrac’s generator testing in Nesman and Dennis 1999.

A Fourth Number That Closes on the Other Three

The vehicle’s propellant load and the engine’s flow rate give a burn time, and it can be checked against the longest engine test the programme published.

\[t_b = \frac{m_p}{\dot{m}} = \frac{13{,}600}{91.90} = 148.0 \ \text{s}\]

The longest hot fire in the engine development record ran 159.03 seconds against 159.0 planned, in a test on 14 May 1999 recorded in the test table of the development status report on the MC-1 engine. Writing $t_{\text{test}}$ for that duration, the margin over the mission burn is

\[\frac{t_{\text{test}}}{t_b} = \frac{159.03}{148.0} = 1.075\]

The masses, the flow rate and the test duration were published separately and by different parts of the programme, and they describe one vehicle burning one propellant load with about seven and a half percent to spare. Had the tested duration come out below the mission burn, one of the four numbers would have been wrong.

What the Vehicle Could Reach

The engine’s figures do not by themselves say what the vehicle can do with it, and the answer is a check on the published masses. The effective exhaust velocity is the flight engine’s published impulse of 314 seconds, which already carries the cost of the cycle, times standard gravity,

\[v_e = I_{sp} \, g_0 = 314 \times 9.80665 = 3{,}079.3 \ \text{m/s}\]

which is 3,079.3 metres per second. The mass ratio is the release mass over the burnout mass,

\[\frac{m_0}{m_f} = \frac{21{,}800}{8{,}200} = 2.6585\]

so the ideal velocity increment is

\[\Delta v = v_e \ln\!\left(\frac{m_0}{m_f}\right) = 3{,}010.9 \ \text{m/s}\]

The ideal increment is 3,010.9 metres per second, and adding the 236.1 the carrier aircraft already supplied gives 3,247.0, against a Mach 8 objective which at the burnout altitude is about 2,400 metres per second.

\[3{,}247.0 - 2{,}400 = 847.0 \ \text{m/s}\]

leaving 847.0 metres per second, or 26.1 percent of the ideal total, for gravity, drag and steering. A vehicle whose ideal increment exceeded its objective by only a few percent would be claiming no losses at all, and one that exceeded it by half would suggest an objective set well below what the vehicle could do. About a quarter is a plausible allowance for a suborbital ascent, which makes this a check on the published masses rather than on the trajectory.

The thrust to weight at release follows from the same figures,

\[\frac{F}{m_0 g_0} = \frac{284{,}415}{21{,}800 \times 9.80665} = 1.330\]

and a vehicle released in level flight needs no more than one, because the wing is already carrying it. Being above one lets an air-launched vehicle pitch up immediately instead of sinking while it accelerates.

The masses also fix the propellant mass fraction,

\[\zeta = \frac{13{,}600}{21{,}800} = 0.6239\]

or 62.4 percent, against 73.7 for the X-33 and the 89.0 percent an orbital vehicle needs. The X-34 is further from an orbital mass fraction than the X-33 was, and neither was required to be close, because neither was going anywhere near orbit. The distinction matters, because the temptation with a demonstrator is to read its numbers as predictions of the vehicle it stood for.

The Chamber That Is Consumed

The Fastrac’s combustion chamber and nozzle were cooled ablatively. There is no regenerative jacket circulating fuel through passages in the wall. Instead a silica-phenolic liner inside a composite overwrap absorbs heat by decomposing, and the gas that leaves the decomposing surface keeps the hot flow off the wall. The wall survives by being destroyed at a controlled rate.

Here the cost argument holds, and the manufacturing burden it avoids is set out in the same design text. A regeneratively cooled chamber is a precision assembly of hundreds of brazed passages and one of the most expensive parts of a rocket engine to make. An ablative liner is a moulding.

It has a consequence that the words reusable launch vehicle do not prepare anyone for. Taking the chamber flow, the chamber pressure $p_c$ and the characteristic velocity $c^{\ast}$ of liquid oxygen burning with RP-1 kerosene, the throat area follows from

\[A_t = \frac{\dot{m}_c \, c^{\ast}}{p_c}\]

Here the throat is published, so the relation can be run the other way. It is 8.25 inches across in the nozzle design report, which is 0.20955 metres, so

\[A_t = \frac{\pi D_t^2}{4} = \frac{\pi \times 0.20955^2}{4} = 0.034488 \ \text{m}^2\]

and with the nominal chamber pressure of 652 pounds per square inch, or 4.495 megapascals, that the development status report lists among the engine’s requirements, and the chamber flow of 88.68 kilograms per second,

\[c^{\ast} = \frac{p_c A_t}{\dot{m}_c} = \frac{4.495 \times 10^6 \times 0.034488}{88.68} = 1{,}748 \ \text{m/s}\]

The same report’s engine schematic shows 633 pounds per square inch in the chamber at its operating point, which would lower the characteristic velocity by 2.9 percent, and the requirement figure is used here as the nominal one. The vacuum thrust coefficient at the flight nozzle’s thrust is then

\[C_F = \frac{F}{p_c A_t} = \frac{284{,}415}{4.495 \times 10^6 \times 0.034488} = 1.8345\]

Those two quantities divide the engine’s performance between its two halves, since the characteristic velocity describes everything upstream of the throat and the thrust coefficient everything downstream,

\[I_{sp} = \frac{C_F \, c^{\ast}}{g_0}\]

That relation is shown for its structure and not as a check. The characteristic velocity above was derived from the same pressure, area and chamber flow, so multiplying the two factors returns the chamber impulse of 327.05 seconds by construction, and presenting the agreement as confirmation would be circular.

The area ratio then fixes the exit. The flight nozzle’s ratio is approximately 30 in both reports, so

\[A_e = \varepsilon A_t = 30 \times 0.034488 = 1.0346 \ \text{m}^2\]

an exit 1.148 metres across, which is a check on the published ratio, because a nozzle wider than the vehicle could not have been fitted to it.

How Fast the Wall Is Destroyed

A recession rate is the output of an energy balance rather than an input to one, and running the balance is instructive because it fails.

Start with the heat the wall has to survive. The standard estimate for a rocket throat is the Bartz correlation, which gives the gas-side heat transfer coefficient as

\[h_g = \frac{0.026}{D_t^{0.2}}\left(\frac{\mu^{0.2} c_p}{\mathrm{Pr}^{0.6}}\right)\left(\frac{p_c}{c^{\ast}}\right)^{0.8}\left(\frac{D_t}{R_c}\right)^{0.1}\]

With a chamber at about 3,500 kelvin and gas properties typical of liquid oxygen burning with kerosene, that gives 8,674 watts per square metre per kelvin, taking the throat’s radius of curvature equal to its diameter. The heat arriving is the coefficient times the difference between the recovery temperature and the ablating surface,

\[q = h_g \left(T_{aw} - T_w\right) = 8{,}674 \times \left(3{,}150 - 1{,}900\right) = 10.84 \ \text{MW/m}^2\]

Ten megawatts per square metre is the order of magnitude a rocket throat delivers. The correlation is good to perhaps a factor of two, a limit stated here because what follows depends on it.

Now the balance. A surface protecting itself by being destroyed removes heat at a rate set by how much energy each kilogram carries away, so writing $H_{\text{eff}}$ for that effective heat of ablation and $\rho_a$ for the material density,

\[\dot{s} = \frac{q}{\rho_a H_{\text{eff}}}\]

Run it forwards with the energy the material can actually absorb. On representative property values, heating silica phenolic from room temperature to 1,900 kelvin takes about 1.76 megajoules per kilogram and vaporising the silica about 12, so

\[H_{\text{absorb}} = 13.76 \ \text{MJ/kg} \qquad \Rightarrow \qquad \dot{s} = 0.463 \ \text{mm/s}\]

Over the 148 second burn that rate removes 68.6 millimetres, an absurd figure. A throat losing that much would not survive, and ablative chambers of this class do not behave that way.

So invert it. The nozzle design report set a throat erosion requirement of under 2 mils per second, which is 0.051 millimetres per second, and found no throat enlarged after 66 firings totalling 1,803 seconds, so a tenth of a millimetre per second is a generous upper figure, and putting that in gives

\[H_{\text{eff}} = \frac{q}{\rho_a \dot{s}} = \frac{10.84 \times 10^6}{1{,}700 \times 10^{-4}} = 63.8 \ \text{MJ/kg}\]

against 13.76 that the material can absorb, a ratio of 4.6, which a slower recession would only raise.

The ablator is not mostly absorbing the heat. It is blocking it. Pyrolysis gas leaving the decomposing surface blows into the boundary layer and thickens it, cutting the heat that arrives in the first place. Absorption is the small term and transpiration is the large one, by a factor of at least four, and an ablative wall survives because of the large term.

The forward calculation being wrong by that factor is the result. It explains why a recession rate is measured rather than predicted.

The Bartz correlation and the ablation balance are standard results and are not this article’s. This article’s contribution is the inversion, an arithmetic step on the balance that introduces no new relation, and the observation that the factor between the two answers is the transpiration term.

Both halves rest on literatures older than the programme. The convective heat transfer to a rocket nozzle was being estimated from the middle 1950s, as in Sibulkin 1956 and Mayer 1961, and the transpiration work that explains the blocking term runs alongside it, as in Bartle and Leadon 1960 and Librizzi and Cresci 1964, so the physics the X-34’s chamber depended on was some forty years settled when the engine was designed.

What That Costs the Chamber

At the upper figure of a tenth of a millimetre per second the liner loses

\[\Delta s = \dot{s} \, t_b = 10^{-4} \times 148.0 = 14.8 \ \text{mm}\]

over a full burn, so a chamber built to fly one mission needs a consumable layer of the order of a centimetre and a half, and at the published erosion requirement about half that.

Recession rate Liner consumed over the burn
0.05 mm per second 7.4 mm
0.10 mm per second 14.8 mm
0.15 mm per second 22.2 mm
0.20 mm per second 29.6 mm

The engine’s combustion chamber was a consumable on a vehicle whose entire purpose was reuse, and the engine’s fact sheet said so, with the ablative chamber and nozzle and the hypergolic ignition cartridge to be replaced after each flight and nearly all the rest reused. At the planned rate of twenty-five flights a year, that is twenty-five combustion chambers a year.

Whether that is cheap depends entirely on what a chamber costs. The article’s keystone has arrived as a component. A moulding at a few tens of thousands of dollars makes it right. A moulding at a few hundred thousand makes it wrong. The public record does not contain the number, and the Epistemic State records the gap without guessing at it.

What Air Launch Donates

The X-34 was carried to altitude under a modified airliner and released, and the usual argument for that is altitude and speed. It is the weakest of the several available.

Taking a release at 38,000 feet, which is 11,582 metres and is the approximate launch altitude that the engine development report gives for the X-34, at an assumed Mach 0.8, the specific energy the aircraft has already supplied is potential plus kinetic,

\[e = g_0 h + \frac{v^2}{2}\] \[e = 9.80665 \times 11{,}582 + \frac{236.1^2}{2} = 141{,}446 \ \text{J/kg}\]

The total is 141.4 kilojoules per kilogram. Expressed as the velocity increment that energy would buy,

\[\Delta v_{\text{equiv}} = \sqrt{2e} = 531.9 \ \text{m/s}\]

The figure is 5.7 percent of a 9,300 metre per second orbital budget. An argument for air launch from the altitude and the speed argues from the smallest of its benefits.

The larger measurable benefit is that the nozzle never sees sea level. Thrust falls below its vacuum value by the ambient pressure acting over the exit area,

\[F = F_{vac} - p_a A_e\]

so with the flight nozzle’s exit area of 1.0346 square metres, and ambient pressures of 101,325 pascals at sea level and 20,646 at the release altitude, the thrust recovered by launching high is

\[\left(101{,}325 - 20{,}646\right) \times 1.0346 = 83{,}470 \ \text{N}\]

which is 83,470 newtons, the difference between a loss at sea level of 104.83 kilonewtons and one at the release altitude of only 21.36. Launching from altitude recovers 83.47 kilonewtons, which is 29.3 percent of the flight nozzle’s vacuum thrust, about five times the share of an orbital budget that the altitude and speed donate. The simple relation overstates the sea-level case, because a 30:1 nozzle at sea level is badly overexpanded, and the nozzle design report records that the nozzle was sometimes truncated to 15:1 to prevent overexpansion and the side loads that come with it. That truncation is the 15:1 configuration whose thrust the usual quotation carries.

And the largest benefit is the one this article cannot compute. An air-launched vehicle needs no launch pad, no flame trench, no fixed azimuth and no launch window dictated by weather over a single site. For a programme whose keystone is cost, the ground infrastructure it never has to build is the argument, and it has no equation.

The Same Trade the Previous Article Answered With Hydrogen

Two consecutive vehicles in this series answered one question in opposite directions, and the question is which propellant to carry.

Writing $r$ for the mixture ratio, the bulk density of a propellant combination is

\[\rho_{\text{bulk}} = \left[\frac{1}{1+r}\frac{1}{\rho_f} + \frac{r}{1+r}\frac{1}{\rho_o}\right]^{-1}\]

The densities come from Huzel and Huang’s design text. Its table of cryogenic propellants gives liquid oxygen 1.142 grams per cubic centimetre at its normal boiling point, and its table of storable propellants gives RP-1 between 0.80 and 0.82 at 68 degrees Fahrenheit, so taking the middle of that range,

\[\rho_o = 1{,}142 \ \text{kg/m}^3 \qquad \rho_f = \frac{800 + 820}{2} = 810 \ \text{kg/m}^3\]

and the hydrogen side keeps the previous article’s 70.85 kilograms per cubic metre. At the engine mixture ratio of 2.17 that the development status report publishes,

\[\rho_{\text{bulk}} = \left[\frac{1}{3.17}\frac{1}{810} + \frac{2.17}{3.17}\frac{1}{1{,}142}\right]^{-1} = 1{,}011.2 \ \text{kg/m}^3\]

For kerosene and oxygen that is 1,011.2 kilograms per cubic metre, against 343.4 for hydrogen and oxygen at 5.5, a ratio of 2.945. The X-33 article, which assumed a generic kerosene mixture ratio of 2.56, found 1,024.1 and a ratio of 2.983 with the same densities. The difference is the mixture ratio alone, and the Fastrac’s published 2.17 is the value that applies to the X-34.

The fuel share of the propellant mass is fixed by the mixture ratio alone,

\[\frac{m_f}{m_p} = \frac{1}{1+r} = \frac{1}{3.17} = 0.3155\]

or 31.5 percent, so the X-34 carried 4,290 kilograms of kerosene against 9,310 of oxygen.

The previous article’s central sentence inverts. Hydrogen is 15.4 percent of the propellant mass and 74.6 percent of its volume, so the fuel tank is the vehicle. Kerosene is about a third of the mass and 39.4 percent of the volume, so the fuel tank is a tank.

The consequence is easiest to see in the load the X-34 carried.

\[\frac{13{,}600}{1{,}011.2} = 13.45 \ \text{m}^3 \qquad \text{against} \qquad \frac{13{,}600}{343.4} = 39.61 \ \text{m}^3\]

An extra 26.16 cubic metres, on a vehicle 17.77 metres long, is not a packaging problem. It is a different aeroplane.

Where the Previous Article’s Scale Invariance Stops Holding

The X-33 article proved that the membrane tank fraction contains no length. A thin vessel of volume $V$ at pressure $p$ has mass $k \rho_w p V / \sigma$ and holds $\rho_p V$ of propellant, so

\[\frac{m_{\text{tank}}}{m_{\text{prop}}} = \frac{k \, \rho_w \, p}{\sigma \, \rho_p}\]

and the size cancels. That cancellation is why a subscale tank was a valid test of a full-scale tank technology. It was the strongest thing the previous article had to say about demonstrators.

It cancels only while stress sets the thickness. The membrane thickness a pressure demands is

\[t = \frac{pR}{\sigma}\]

which falls with the radius, while the thinnest laminate anybody can lay up does not fall at all. Taking the same construction and pressure as the previous article so the comparison is controlled, and sizing the walls by the ordinary structural methods Bruhn sets out for flight vehicle structures,

Tank Radius Membrane thickness needed Per facesheet Minimum gauge as a multiple
X-33 hydrogen tank 2.15 m 1.384 mm 0.692 mm 1.45
X-34 tank, assumed 0.75 m 0.483 mm 0.241 mm 4.14

The smaller the tank, the more of its wall is material no load asked for. Once minimum gauge binds, the wall thickness stops depending on the pressure at all, and the tank fraction follows in three lines. For a cylinder of radius $R$ whose wall is two facesheets each at the minimum gauge, the wall mass and the propellant mass per unit length are

\[m'_{\text{wall}} = \rho_w \left(2 \pi R\right) \left(2 t_{\text{gauge}}\right) \qquad m'_{\text{prop}} = \rho_p \pi R^2\]

so the length and the constant both cancel, leaving

\[\frac{m_{\text{tank}}}{m_{\text{prop}}} = \frac{4 \rho_w t_{\text{gauge}}}{\rho_p R}\]

which goes as one over the radius instead of being independent of it.

Tank radius Hydrogen and oxygen Kerosene and oxygen
0.50 m 3.66% 1.24%
0.75 m 2.44% 0.83%
1.00 m 1.83% 0.62%
1.50 m 1.22% 0.41%
2.15 m 0.85% 0.29%
3.00 m 0.61% 0.21%

Two things follow and they point in opposite directions.

The scale penalty is real, so a small demonstrator’s tank is proportionally worse than a large vehicle’s and cannot stand in for it. The X-33’s tank could. The X-34’s could not. That is the previous article’s best argument about demonstrators failing at a smaller size, and it fails because of manufacture rather than because of mechanics.

And the propellant more than pays for it. At the X-34’s assumed tank radius of 0.75 metres, with the previous article’s laminate density of 1,570 kilograms per cubic metre and minimum gauge of one millimetre, the gauge-limited fraction for the two bulk densities above is

\[\frac{4 \times 1{,}570 \times 0.001}{343.4 \times 0.75} = 0.0244 \qquad \text{against} \qquad \frac{4 \times 1{,}570 \times 0.001}{1{,}011.2 \times 0.75} = 0.0083\]

so a hydrogen and oxygen tank is 2.44 percent of the propellant it holds and a kerosene and oxygen tank is 0.83, a factor of 2.945 which is exactly the ratio of the two bulk densities, since everything else in the numerator and denominator is common to both. The small vehicle is penalised by its size and rescued by what it chose to burn.

The Vehicle

The X-34 was a small winged rocket aeroplane, carried aloft under an airliner and released to fly a suborbital profile to about Mach 8. The agency’s fact sheet gives a length of 58.3 feet and a wingspan of 27.7 feet, which at 0.3048 metres to the foot are

\[L = 58.3 \times 0.3048 = 17.77 \ \text{m} \qquad b = 27.7 \times 0.3048 = 8.44 \ \text{m}\]

It had a composite airframe with composite propellant tanks, silica-based tiles and flexible blankets for thermal protection, and it was to land itself on a runway without a pilot.

The same fact sheet gives an unfuelled weight of 18,000 pounds and 30,000 pounds of liquid oxygen and kerosene. At 0.45359237 kilograms to the pound, and writing $m_e$ for the empty mass and $m_0$ for the release mass,

\[m_e = 18{,}000 \times 0.45359237 = 8{,}165 \ \text{kg} \qquad m_p = 30{,}000 \times 0.45359237 = 13{,}608 \ \text{kg}\] \[m_0 = m_e + m_p = 48{,}000 \ \text{lb} = 21{,}772 \ \text{kg}\]

This article rounds the 8,165, 13,608 and 21,772 kilograms to 8,200, 13,600 and 21,800, and the sum still closes after rounding. The closure holds by construction and is no check, because the fact sheet does not give the release mass separately, and it deserves mention only because the previous article’s did not.

What Was Deliberately Left Out

The list of things the X-34 did not have is the list a later review objected to, and it reads more fairly forwards than backwards. The vehicle had single-string avionics, meaning no redundant channel for a failure to fall back on. Its system-level testing was thin. Its automatic landing had not been validated in flight.

Every one of those is a defensible choice for a cheap demonstrator and an indefensible one for a vehicle about to be released over inhabited ground. The programme did not change its mind about engineering. It changed its mind about which of those two things it was building.

Dependent Systems

Thermal Protection

The X-34 used silica-based tiles on its nose and wing leading edges and flexible insulation blankets elsewhere rather than the metallic system the X-33 chose, as Wurster et al 1998 describe, and the requirement that shaped it was unusual. The vehicle had to survive subsonic flight through weather, because an air-launched vehicle spends its climb attached to an aeroplane flying through whatever is between the runway and a launch altitude that the engine development report puts at about 38,000 feet. A launch pad does not fly through rain.

Autonomy and Landing

An unpiloted vehicle that lands on a runway has to be right the first time, and the X-34 was to demonstrate automatic landing including in a twenty-knot crosswind, with navigation from a combination of satellite and inertial systems.

This is where the cost argument and the risk argument meet most directly. Automatic landing is cheap to specify and expensive to prove, because proving it means flying it, and flying it is what the programme had not yet done when it was asked what its residual risk was.

Aerodynamics

The aerodynamic work was conventional and the vehicle was small enough to be tested honestly, one advantage of a small demonstrator that the mass-fraction argument does not capture. A wind tunnel model of a 17-metre vehicle is a larger fraction of full scale than a model of a 21-metre one, and the Reynolds number gap is correspondingly smaller.

The Flight Test Record

There is no powered flight test record. The X-34 never fired its engine in the air.

Ground Tests and Captive Flights

The first unpowered airframe was rolled out in 1999 at the agency’s flight research centre. It was towed on the ground behind a vehicle, and it was carried aloft beneath the carrier aircraft on a first captive flight on 29 June 1999, with two more captive flights later that year. Two airframes were completed of the three planned. The engine was tested extensively on the ground, and its longest firing, of 159.03 seconds in the engine’s test record, is the firing set against the mission burn earlier, under A Fourth Number That Closes on the Other Three.

No free flight was ever made, powered or unpowered. The vehicle was never released from the carrier aircraft.

The Review That Ended It

A joint review in 2000 found that the project needed its approach, scope, budget and schedule redefined, and named the risks. They were inadequate system testing, single-string avionics and an unvalidated automatic landing. Reaching an acceptable level of risk would require more government technical insight, more hardware testing and integrated systems assessment, as the agency’s fact sheet of the period records.

An estimate drawn from the restructure plan that followed put the total requirement near 348 million dollars against roughly 86 million budgeted in 1996, in the oversight body’s testimony, and the programme ended on 31 March 2001, after a funding decision announced together with the X-33’s, with the agency stating that the benefits did not justify continued investment and that the funds of the initiative that replaced both should go to higher priority needs. The oversight body examined the two cancelled programmes together later that year.

\[\frac{348 - 86}{86} = 3.05\]

A growth of 305 percent on the rounded figures, and the arithmetic is not the interesting part. The oversight body, working from unrounded ones, gives 307 percent. What the number measures is.

Comparison With Ground Prediction

This section normally compares prediction with flight measurement. The X-34 produced no flight measurement at all, so what can be compared is prediction against the only two things the programme did produce, which are ground test results and a revised cost estimate.

Where the Ground Tests Agreed With Prediction

The engine worked. It was fired repeatedly, including for 159.03 seconds, which exceeds the 148 second burn a full propellant load implies, by the margin the burn-time check above derived. The published thrust, impulse and flow figures are mutually consistent to within half a percent once each nozzle’s thrust is paired with its own impulse, as the nozzle pairing above shows, and the generator fraction of 3.50 percent derived under The Cycle Is Smaller Than the Gap lands inside the range the cycle architecture uses. Nothing in the engine’s published numbers indicates a machine that was not doing what it was designed to do.

The airframe was built, twice. It was towed, it was carried, it held together, and the two airframes outlived the programme by nearly two decades.

Where Prediction and Outcome Diverged

The prediction that failed was the cost estimate, and it failed by a factor of four. No structure broke, the engine’s development problems were found and corrected on the ground, and no aerodynamic surprise appeared. The quantity that moved was the one with no conservation law.

That is a different kind of divergence from any this series has met. A drag rise that comes in higher than predicted is a fact about air. A cost estimate that comes in higher than predicted is a fact about what was left out of the estimate, and the review that produced the new figure named what had been left out.

The Comparison the Programme Never Got to Make

The X-34 was to demonstrate rapid turnaround, and turnaround is the one quantity that would have tested the whole cost argument. London and Lyles 1998 give the goal as 25 flights in a year with a surge of two flights within 24 hours. A vehicle that flies twenty-five times a year with a small crew is a different economic object from one that flies twice. The programme never flew once, so the number that mattered most was never measured, and the Epistemic State lists it as unsettled.

Work on operations and turnaround appears below under launch vehicle design, staging and operations and under risk, reliability, safety and health management. It includes the turnaround time model for conceptual rocket engines in Nix and Staton 2004 and the reliability and maintainability models for reusable launch vehicles in Unal et al 2000 and Unal et al 2004.

What the Data Changed

The Verdict on the Cost Argument, Tested Both Ways

Take the two programmes cancelled in the same announcement and divide what each spent by the mass of vehicle it produced. Mass is a poor denominator for cost. It is used here because it is the one comparable quantity both programmes published. Cost estimating for space systems has its own methods, set out in Wertz and Larson’s standard treatment of space mission design, and none of them is a division by mass. The article states that limit openly so that the ratio is not taken to mean more than it does.

The X-34’s release mass is the fact sheet’s 48,000 pounds, the sum displayed in the description of the vehicle above, against 285,000 for the X-33. The X-34’s spending is reported as just under 112 million dollars, and the X-33’s as about 1,280 million, being the 922 million the agency and 357 million Lockheed Martin put in.

\[\frac{112 \times 10^6}{48{,}000} = 2{,}333 \ \text{dollars per pound}\] \[\frac{1{,}280 \times 10^6}{285{,}000} = 4{,}491 \ \text{dollars per pound}\]

The X-34 comes to 2,333 dollars per pound against the X-33’s 4,491, so on money actually spent the low-cost vehicle was 1.92 times cheaper per pound of vehicle, and both programmes ended without a powered flight, so the comparison is between two equivalently incomplete efforts.

Now do it with the money it would have taken to fly the thing safely.

\[\frac{348 \times 10^6}{48{,}000} = 7{,}250 \ \text{dollars per pound}\]

The result, 7,250 dollars per pound, is 1.61 times the X-33’s actual spend per pound. The vehicle built to be cheap would have cost more per pound to finish than the vehicle everyone remembers as the expensive one.

Both figures are published and they answer different questions. The first says the programme was economical at building hardware. The second says that building hardware was not the expensive part.

What the Programme Settled

It settled that a small air-launched reusable demonstrator can be built for a fraction of the cost of a large one, which was never seriously in doubt and which the airframes themselves prove.

It settled that an ablatively cooled engine of that class can be built and run, and the Fastrac was fired far more than the X-34 ever flew.

It did not settle anything about the cost of an operational reusable launch vehicle, because the quantity that would have settled it, turnaround, was never measured.

These conclusions draw on the cluster on cost estimation, cost growth and acquisition, including the launch systems operations cost model of Prince and Hamaker 2001 and the cost analysis of a single-stage reusable ballistic launch vehicle in Koelle 1993.

What It Fed Into

The engine’s record after the vehicle is unclear, since one account dates the end of its programme to 2001 and the closure of its test project to 2009. The ablative low-cost approach did not become the standard route to a cheap engine, and the kerosene engine that followed the Fastrac’s methods is now regeneratively cooled.

What did become the standard route is visible in what replaced the programme’s premise. The decision history that produced this family of programmes is set out in Heppenheimer’s account of the shuttle decision. The reduction in launch cost that the reusable launch vehicle programme was chartered to pursue has since been sought through recovering and reflying an expensive engine many times, one Falcon 9 engine having flown twenty-two times, rather than through building a cheap one to throw away. The X-34’s bet was that the way to make launch cheap is to make the hardware cheap. The bet that paid was that the way to make launch cheap is to use expensive hardware more often.

That conclusion needs stating with care and without triumph. The two strategies are not opposites and a small launcher today may well be right to use a simple engine. What can be said is that the inference behind the X-34, that cheap hardware implies cheap access, was not the one that turned out to matter most.

What It Failed to Influence

The two airframes are the most direct evidence of influence, and they went to a scrapyard. They sat in storage at Edwards, moved to a desert airfield in 2010, then to a crane company’s yard, and were at a scrapyard by April 2020. A vehicle that is near completion and then abandoned teaches little beyond what was written down before it stopped. The programme appears in the agency’s history of the X-vehicles as a vehicle that was built and did not fly.

The Contemporary Literature

Cluster Records
The X-34, the Fastrac engine and the low-cost booster programme 87
Reusable launch vehicle programmes and demonstrators 109
Air launch, carrier aircraft and store separation 177
Launch economics, small launchers and reusability 112
Cost estimation, cost growth and acquisition 245
Ablative materials, charring and recession 455
Additive manufacturing and low-cost fabrication 258
Gas-side heat transfer and the cooling of chambers 504
Liquid rocket engines, turbopumps and combustion 678
Solid and hybrid rocket motors 338
Rocket nozzles, plumes and expansion 206
Thermal protection systems and hot structures 211
Propellant tanks and cryogenic storage 146
Composite structures and flight vehicle materials 186
Aerodynamics, aerothermodynamics and hypersonic flow 256
Automatic and autonomous landing 323
Guidance, control, avionics and trajectories 444
Risk, reliability, safety and health management 192
Design optimisation, uncertainty and computation 117
Launch vehicle design, staging and operations 305
Flight test, instrumentation and range operations 18
Total 5,367

The subjects this article computes are all active, and two of them are more active now than they were then, for reasons the programme would have found ironic.

Ablative Materials and Their Modelling

The ablation modelling the article treats as a recession rate is now a detailed thermochemical subject, with pyrolysis, char and surface chemistry resolved rather than lumped, and more of its recent titles concern planetary entry than cheap engines.

The cluster on ablative materials, charring and recession holds this literature. The pyrolysis of the phenolic impregnated carbon ablator is characterised in Wong et al 2015 and Torres-Herrador et al 2019, its arc-jet response in Smith et al 2015 and Milos and Gasch 2015, and the full-scale Stardust heat shield is modelled in Weng et al 2021. The engine application continues in Wunderlin et al 2024, an ablative thrust chamber for a liquid engine, and in Chandler 2023, a test of an ablative chambered engine.

Low-Cost Propulsion Through Manufacture

The X-34’s answer to expensive engines was to make a cheap one badly on purpose. The modern answer is to make an expensive one quickly, with additive manufacturing cutting the fabrication time, the cost and the number of separate manufacturing steps of the regeneratively cooled chamber the Fastrac avoided. NASA’s low-cost upper stage propulsion project and its bimetallic chamber work with Virgin Orbit both report those reductions. The constraint the Fastrac was designed around has largely dissolved. This is the second time in two articles that a 1990s architecture has been overtaken by a change in how things are made rather than in how they work.

The additive manufacturing of that chamber is developed and hot-fired in Gradl et al 2017 and Gradl et al 2019, summarised in Gradl et al 2018, and applied to a low-cost upper stage chamber in Protz et al 2016. The remainder is spread across the clusters on additive manufacturing and low-cost fabrication, on gas-side heat transfer and the cooling of chambers and on liquid rocket engines, turbopumps and combustion.

Small Launch Vehicles and Their Economics

The market the X-34 was pointing at exists now, and the literature on small launch vehicle economics, reusability and cost per kilogram is where the argument the programme could not finish is being had.

Its cluster, launch economics, small launchers and reusability, includes the industry analyses of Sun 2022 and Puteaux et al 2024, the survey of small launch vehicles in Niederstrasser 2022, and the cost analysis of the Starship system in Harris et al 2022.

The Commercial Verdict on Air Launch

The argument for air launch is no longer being had, because the market has spent the last decade running the experiment.

The operating method the X-34 borrowed was already commercial when the programme started, and the air-launched booster that supplied it flew for decades at a price that rose, from an initial offer of six million dollars to about forty million by 2017 for some 450 kilograms to low orbit,

\(\frac{40{,}000{,}000}{450} \approx 89{,}000 \ \text{dollars per kilogram}\) A later attempt, Virgin Orbit’s LauncherOne, put a liquid-fuelled orbital rocket under a widebody airliner and flew it six times between 2020 and 2023. Four of the six reached orbit. The operator filed for bankruptcy in April 2023 and was wound up the following month, its remaining assets sold at auction for about thirty-six million dollars, and the carrier aircraft was bought by another company to carry a hypersonic test vehicle in place of a launcher.

Reaching orbit was not the problem. Four flights out of six did that. What failed was the thing the X-34 existed to demonstrate.

This is a harder verdict on the X-34’s premise than anything in the programme’s record, and it should be stated with its limits. One company failing is a fact about one company. But the claim that removing the launch pad removes enough cost to change the economics has now been tested with real money by people who believed it, and the answer that came back was the same one the restructure plan gave in 2000. The infrastructure a vehicle does not build is not where the cost is.

The literature on small launch economics is where this argument now lives, and most of it is recent. Of the 112 records gathered below on launch economics, small launchers and reusability, 67 date from 2015 or later, while 113 of the 177 records on air launch, carrier aircraft and store separation predate 2015.

The cluster on air launch, carrier aircraft and store separation runs from the Pegasus flight test programme in Elias and Knutson 1995 to the description of LauncherOne in Vaughn et al 2017, the towed glider concept of Budd and Monheim 2015, the business-jet captive-carry demonstration in Miller et al 2018 and the comparison of ground and airborne launch for hybrid small launchers in Casalino et al 2022.

Autonomy, Landing and the Risk Case

The unvalidated automatic landing that helped end the programme is now routine for reusable launch stages, and it is routine because vehicles fly it repeatedly rather than because anybody proved it on paper. Falcon 9 boosters land vertically under power, where the X-34 was to land on a runway. They first landed in December 2015 and have since landed nearly six hundred times. The risk argument against the X-34 has since been resolved by the method the X-34 could not afford.

Landing is covered below by the clusters on automatic and autonomous landing and on guidance, control, avionics and trajectories. The powered landing of reusable rocket stages is a large part of the recent work, with landing guidance in Sagliano et al 2021, Ma et al 2019 and Su et al 2022 and trajectory optimisation in Wang and Song 2018.

Structures, Tanks and Thermal Protection

The clusters on thermal protection systems and hot structures, on propellant tanks and cryogenic storage and on composite structures and flight vehicle materials collect the literature on structures, tanks and thermal protection. Recent threads include linerless composite tanks for liquid hydrogen in Olsson et al 2024 and flexible thermal protection in Tobin and Dec 2015 and Rossman and Braun 2016.

Method, Uncertainty and Computation

Method draws on the clusters on design optimisation, uncertainty and computation, on risk, reliability, safety and health management and on launch vehicle design, staging and operations. Uncertainty quantification for launch vehicle design is treated in Brevault and Balesdent 2021 and Novack et al 2016.

The vehicle’s own record stops when the programme does. Of the 39 research records whose titles carry the X-34 designation, 37 date from 2001 or earlier, one from 2002, and one, a 2015 paper on the Fastrac’s memorandums of misunderstanding in Hawkins and Turner 2015, from 2015. A cancelled programme stops generating literature under its own name almost immediately, which means the documentary trace of a vehicle is not a measure of what it contributed but of how long it survived.

The X-34, the Fastrac engine and the low-cost booster programme

The vehicle, its Fastrac engine and the low-cost booster technology programme that produced the engine, with the programme’s status reports and its successors under the Future-X heading.

The record is the programme’s own and it stops when the programme does. Of the 87 records, 78 date from 2001 or earlier and 3 from 2015 or later. Of the 45 titles that name the Fastrac or the MC-1, 38 date from 2002 or earlier.

87 records. [Aron et al 2001] [Ballard et al 2000] [Barton and Tragesser 1999] [Beech and Chandler 1997] [Berry et al 1998] [Beshears 2000] [Beshears 2000] [Blades and Redgrave 2000] [Brauckmann 1998] [Brown 2000] [Brown 2002] [Brown and Brunty 2001] [Brown et al 1998] [Brown et al 2000] [Brown et al 1998] [Bullard 1998] [Burchett 2008] [Champion and Darrow 1998] [Christensen and Nesman 1998] [Component and System Level 1999] [Davis 2001] [Davis and Phelps 2001] [Dennis and Sanders 2000] [Dill et al 2001] [Dobson et al 2000] [Dragone 2000] [Fisher and Ise 1998] [Fisher et al 1998] [Frady et al 2000] [Garcia et al 1998] [Goode 2001] [Griffin and Dorney 1999] [Griner and Lyles 1999] [Hawkins and Turner 2015] [Hedayat et al 1998] [Hedayat et al 1998] [Hedayat et al 2000] [Heflin et al 2000] [Hwang et al 2020] [Kelb et al 1998] [Kim and Kim 2012] [Klem 1999] [Koelbl and Van Hooser 2015] [Laszar 2003] [Lawerence et al 2000] [Lawrence et al 2001] [London and Lyles 1998] [London and Sumrall 1999] [Ly and Roe 2001] [McDonald et al 1998] [McDonald et al 1998] [Miller 1999] [Miller 2000] [Milos and Squire 1999] [Milos et al 1997] [Moon and Beveridge 1997] [Moon and Beveridge 1997] [Nesman and Dennis 1999] [Nesman and Dennis 2001] [Nguyen 1998] [Pamadi and Brauchman 1999] [Pamadi et al 2000] [Peters and Turner 2000] [Peters et al 2000] [Prabhn and Weilmuenster 2001] [Prabhu 2001] [Riley and Kleb 1998] [Rocker and Jones 2002] [Rocker and Nesman 1998] [Rocker and Nesman 1999] [Rocker et al 2001] [Rogers and Dragone 1996] [Santi 1999] [Shadoan et al 2000] [Skelley and Zoladz 1999] [Skelley and Zoladz 2001] [Soots and Burchett 2008] [Springer and London 2000] [Springer 1999] [Tragesser and Barton 1999] [VanHooser and Turner 2001] [Vu et al 2000] [Wallace 1999] [Wood 1999] [Wurster et al 1998] [Zoladz 2000] [Zoladz and Turner 2001]

Reusable launch vehicle programmes and demonstrators

The other reusable and experimental launch vehicle programmes the article sets the X-34 beside, chiefly the X-33, the Space Shuttle, the DC-X and the Kistler K-1.

It is a literature of the programmes’ own period. Of the 109 records, 83 date from 2001 or earlier.

109 records. [Aggarwal 2018] [Andrews 1998] [Armstrong 1977] [Baumann et al 2008] [Bell Aerospace Co Buffalo Ny 1955] [Bell Aerospace Co Buffalo Ny 1955] [Bell Aerospace Co Buffalo Ny 1957] [Bott et al 1983] [Brauckman and Scallion 2003] [Chiesa et al 2005] [Clayton 1989] [Cook 1996] [Cook and Coffey 1973] [Cook et al 1989] [Curry et al 1971] [Dean and Mena 1983] [DeMott and Bigler 2017] [Development of a large scale Chimera grid system for the Space Shuttle Launch Vehicle 1993] [Donahue 1997] [Donahue 2001] [Dotts et al 1982] [Dotts et al 1982] [Dotts et al 1983] [Dwoyer et al 1982] [Edwards and Foster 1973] [Edwards et al 1975] [Elegante and Bowman 1978] [Fagan et al 2003] [Ferguson 2011] [Fitzsimmons 1996] [Foster 1989] [Foster et al 1989] [Fullerton 1975] [Graves et al 1989] [Greenberg 1993] [Gregory and Wilcox 1970] [Gregory et al 1971] [Gupta et al 2018] [Hanson et al 1998] [Harris 1993] [Harris et al 2018] [Harsh et al 1991] [Hartman and Stallings 1982] [Health monitoring and controls for a Single Stage To Orbit vehicle propulsion system 1994] [Henry and McLELLAN 1971] [Hudson 1988] [Ingalls and Cipolletti 2011] [ISRO Releases the Special Issue on ‘Reusable Launch Vehicle-Technology Demonstrator’ 2018] [Jameson 2001] [Jensen 2000] [Justiz and Patel 1988] [Kai and Ohtake 1996] [Ketner and Hess 1979] [Kobald et al 2017] [Koelle 1993] [Kuo 1976] [Lanshin and Sosunov 1995] [Lee 1974] [Lee et al 2026] [Lockheed Martin Skunk Works 1999] [Lomas et al 2001] [London and Rogacki 2000] [Lui and Mason 1991] [Lycans 1998] [McWhorter and Ewing 2001] [McWhorter et al 2004] [Meyerson 1998] [Molinari et al 2024] [Mueller Hm and Lepore 2000] [Naftel 2000] [Niedermeyer 2003] [Ohern 1975] [Olynick 1998] [Palmer et al 1999] [Peebles 2007] [Perlo 2026] [Peterson and Uney 1978] [Picka and Glenn 2011] [Powers and Bailey 1980] [Powers and Bailey 1982] [Powers et al 1981] [Rice 1979] [Roberts and Huynh 1998] [Ronquillo 1985] [Roush et al 2026] [Rozycki et al 1993] [Sawyer et al 1999] [Schmidt and Mann 1996] [Schwabacher et al 2002] [Schweikhard et al 1998] [Schweikhard et al 2001] [Seward and Jumper 1990] [Shoyama and Hirakawa 2024] [Sivan and Pandian 2018] [Smith et al 1974] [Stanley and Powell 1990] [Support to X-33/Reusable Launch 2000] [Chambers 1977] [Tartaglione and Mazzola 1982] [The air-breathing launch vehicle for earth- orbit shuttle - New technology and development approach 1970] [Trefny 1999] [Trimmer et al 1972] [Patil 2025] [Wang et al 2001] [Wang and Cornelison 1996] [Whitesides et al 1990] [Whitmore et al 2004] [Wierzbanowski and Ramasubramanian 2020] [Zubrin and Clapp 1996]

Air launch, carrier aircraft and store separation

Air launch to orbit, the Pegasus booster and LauncherOne, carrier aircraft and captive carry, and the store separation problem that release from a carrier shares with weapons.

The operating method has a continuous literature. Of the 177 records, 113 name air launch, Pegasus, LauncherOne or Virgin Orbit, and 64 date from 2015 or later.

177 records. [AIR LAUNCH ORBITAL PLANE FROM WIG-CRAFT 2019] [Aircraft store separation motion prediction via grid data trajectories 1980] [Arnodo et al 2018] [Atwood 1994] [Atwood 1995] [Belbruno et al 1992] [Bell and Moser 1999] [Black 1969] [Black and Picklesimer 1971] [Blackburn and George 1964] [Bolster and Googins 1967] [Boltz 2004] [Bonometti and Sorensen 2006] [Brooks 1971] [Budd 2015] [Budd 2018] [Budd and Jensen 2015] [Budd and Monheim 2015] [Budd and Webb 2016] [Butler 1975] [Butler 1976] [Cai et al 2023] [Carlson et al 1995] [Carriage and launch characteristics 1994] [Casalino et al 2022] [Cenko et al 1994] [Chao et al 1993] [Ching 2000] [Chow and Marconi 1989] [Clegern and Ostrander 1995] [Cline et al 1996] [Coleman et al 1996] [Coogan and Musgrove 2017] [Corda et al 2018] [Dana Fanggidae and Kusumahardi 2025] [Daniels and Clare 1973] [Davids and Cenko 2001] [Davis and Welterlen 2003] [Davis et al 2006] [Deitchman 1957] [Demir 2018] [Deslandes and Seifert 2000] [Development and Prospect of Air Launch Vehicle 2004] [Dileep et al 2019] [Dillenius et al 1974] [Dillenius et al 1975] [Donegan and Fox 1991] [Doolan 2006] [Elias and Knutson 1995] [Elkman et al 2022] [Elkman et al 2022] [Elkman et al 2022] [Feaux et al 1989] [Goerttler and Schnepf 2024] [Gothard and Granlund 2022] [Gregory 2001] [Guo et al 2024] [Hampsten 1996] [Hendrick and Saint-Mard 1999] [Hochstetler et al 2016] [Hoffren and Salminen 1999] [Hoyt 2006] [Huan-Ding et al 2018] [Hudson 2005] [Ito et al 2019] [Jenkins 1982] [Joshi et al 2023] [Kansas Univ Lawrence 1952] [Kaykayoglu 1996] [Keen 1990] [Kelly et al 2017] [Lasek and Sibilski 2002] [Lee and Sarigul-Klijn 2020] [Lempert 1975] [Lengyel and Sosa 2021] [Lepore 2006] [Li et al 2022] [Lijewski and Suhs 1992] [Lijewski and Suhs 1994] [Lindberg 1989] [Liu 2003] [Logan et al 2006] [Lyu and Wang 2024] [Maddox 1980] [Maddox et al 1979] [Markarian 1971] [Martineau et al 1990] [Meyer et al 1992] [Miller et al 2018] [Mizrahi and Raveh 2019] [Mosier et al 1991] [Mosier et al 1991] [Murman et al 2004] [Newman et al 1992] [Nichols and Denny 1999] [Noffz and Curry 1991] [Noh et al 2007] [Numerical Investigation of Mother 2005] [Olejnik et al 2020] [Olejnik et al 2022] [Parkinson et al 1995] [Pegasus Key to Low-Cost 1990] [Peters et al 2024] [Poth et al 1993] [Pritts 1974] [Qian et al 2017] [Rafique and LinShu 2009] [Rafique et al 2009] [Rafique et al 2009] [Rafique et al 2009] [Rafique et al 2009] [Rafique et al 2009] [Rafique et al 2010] [Rafique et al 2010] [Rafique et al 2011] [Raharema et al 2026] [Reed and Curry 1969] [Rovner 1991] [Roychowdhury et al 2019] [Rutherford and Wells 1999] [Ryan 1966] [Salt 2015] [Sarigul-Klijn et al 2004] [Sarigul-Klijn et al 2005] [Sarigul-Klijn et al 2006] [Sarigul-Klijn et al 2006] [Sarigulklijn et al 2012] [Shubov 2023] [Sikharulidze et al 2005] [Silaidis et al 2024] [Singh et al 2022] [Sohier et al 2014] [Sohier et al 2014] [Sohier et al 2015] [Song et al 2020] [Sorensen and Schafer 2001] [Spahr 1974] [Spahr 1975] [Spahr and Sumlin 1974] [Spahr and Sumlin 1975] [Spivey et al 2018] [Stallings 1982] [Stewart et al 2026] [Stokes et al 1999] [Study on Reliability Test 2023] [Svob and Bills 1984] [Szalai 2025] [Talbot and Moyer 1993] [The Bigger Picture Virgin 2018] [Thomas et al 2007] [Tomaro et al 2000] [Tsybriy and Guskov 2025] [Urbahs et al 2021] [van den Broek 1984] [Van Kesteren et al 2014] [Vaughn et al 2017] [Verstraete and Hendrick 2003] [Verstraete et al 2009] [Virgin Orbit could have 2021] [Vishwajeet et al 2025] [Vlasyk and Korshunova 2025] [Wang 2015] [Wang and Ma 2024] [Waskiewicz et al 1981] [Waters et al 2013] [Whitehead 2006] [Xu and Tang 2010] [Yang et al 2016] [Yang et al 2021] [Yavuz 1997] [Yin et al 2024] [Zhang and Xu 2025] [Zhang and Zhang 2020] [Zhang et al 2013] [Zhao and Wang 2020] [Zheng and Zhang 2018] [Zhou et al 2019]

Launch economics, small launchers and reusability

Launch cost, cost per kilogram, the small launch market, commercial launch and the economics of reusability.

The market literature is recent. Of the 112 records, 67 date from 2015 or later.

112 records. [Akiyama and Inatani 2009] [Beers et al 2013] [Bos and Morrison 1964] [Buursink 1998] [Carrick et al 1998] [Casalino et al 2019] [Casalino et al 2019] [Casalino et al 2022] [Chandler 2019] [Chelaru et al 2015] [Chelaru et al 2017] [Chen 2019] [Chen and Wu 2018] [Choi et al 2022] [Christie 2026] [Cordes and Hertzfeld 1997] [Daniel and Ramusat 2005] [Deschamps 1985] [Duret and Fabrizi 1999] [Ellery 2017] [Fanciullo 2000] [Felix Mwiya and Wisdom Simwila Kalunga 2024] [Ferrandon 1997] [Frazier and Moser 1995] [Garvey et al 2003] [Goldsborough 2005] [Gomez Fernandez 2024] [Griffin and Claybaugh 1994] [Grim et al 1969] [Gulliver et al 2017] [Haws and Bowman 2022] [Hayward 2017] [Hemza et al 2018] [Hubbel 2000] [Hutchison 2011] [Imamura et al 1994] [Jiawei 2024] [Jo et al 2021] [Jo et al 2021] [Jones 2017] [Jones 2017] [Jones 2018] [Jones 2018] [Jung 2026] [Kaushal 2024] [Keith 1995] [Kim 2024] [Kim et al 2022] [Koelle 1989] [Koelle 1992] [Kozedra et al 2021] [Kumar et al 2026] [Kuriakose et al 2020] [Kutter 2006] [Larsen 2000] [Larsen 2003] [Lee et al 2025] [Mankins 1994] [Maquera Ortega et al 2024] [Marcucci et al 2026] [Merriam 2002] [Meserole 1993] [Mingireanu 2016] [Morrison and Festa 2000] [Moser and Frazier 1994] [Najam 2014] [Nguyen and Aleti 2025] [Niederstrasser 2022] [Oldson and Carroll 1995] [Onel et al 2019] [Palac 1999] [Park et al 2024] [Park et al 2024] [Parkinson 1995] [Parkinson 2000] [Parsons 1970] [Parsons Engineering Sciences Inc Pasadena Ca 1991] [Pizzuto and Ziegler 2024] [Prince 1999] [Puteaux et al 2024] [Ridosko et al 2024] [Rouillon and Senegas 2026] [Satellite Power Systems SPS 1980] [Schilling 2016] [Schmierer et al 2019] [Schneider and Breda 2024] [Schutte and Thoreau 2016] [Seo et al 2022] [Shaw and Greenberg 1998] [Shaw et al 1997] [Skoczylas et al 2019] [Sun 2022] [Tiffin and Friz 2021] [Torres and García 2018] [Ueda et al 2026] [Villanueva and Abbas 2015] [Vital et al 2025] [Vrankar 2026] [Waters et al 2013] [Webb 2016] [Whitfield 1998] [Wilken 2024] [Wilken 2025] [Williams et al 2015] [Wolfe and Knight 1988] [Wunderlin et al 2018] [Yaddala Somasekhar 2024] [Yang 2020] [Zapata 2012] [Zhang et al 2018] [Zhang et al 2021] [Zhang et al 2021]

Cost estimation, cost growth and acquisition

Cost estimation, cost growth, design to cost and acquisition, for launch vehicles and space systems and for the defence programmes whose cost-growth literature is the larger one.

The keystone’s literature is split between two customers. Of the 245 records, 118 name a launch vehicle, a rocket, a booster, an orbit or space, and 46 name acquisition, weapons, defence or a military service. 24 titles in the survey name faster, better, cheaper.

245 records. [Accola et al 1990] [Aerojet-General Corp Sacramento Ca 1963] [Affordable In-Space Transportation An 1996] [Affordable In-Space Transportation Phase 1996] [Aggarwal et al 2010] [Alawadhi et al 2025] [Alexander and Fournier 1963] [Alvey 1966] [Analysis of the relationship between mass, speed and cost of an unmanned aircraft 2024] [Apgar 2003] [Arockiam et al 2012] [Asher and Maggelet 1980] [Aso et al 2018] [Avery et al 2026] [Backlund and Rossen 1971] [Baldus et al 2013] [Balut et al 2003] [Baruah et al 2025] [Bedzyk et al 1987] [Bell et al 1964] [Bignami 2000] [Blalack 2020] [Boehm 2012] [Boehm 2012] [Boger and Nussbaum 1990] [Bonnín Roca et al 2019] [Borowski et al 2015] [Borowski et al 2015] [Borowski et al 2014] [Borowski et al 2016] [Bradford et al 2004] [Bradshaw et al 1971] [Braun et al 1970] [Brennan and Finizie 1976] [Brown 1978] [Browning 1993] [Campbell and Schneider 1969] [Capitano and Eldridge 1984] [Catena et al 2000] [Chace 2015] [Chase and McKinney 2005] [Cheaper, Faster, Better? Commercial 2000] [Cifani and Martino 2013] [Cloos and Nelson 1990] [Computer-Aided Conceptual Design and 1988] [Cook] [Coopersmith 2011] [Cork and Mulcahy 1977] [Corso 1969] [Corso 1969] [Crispo and Kim 2026] [Crose 1965] [Cruz et al 2025] [Curtis et al 1996] [Davis 1973] [Davis 2011] [Davis 1988] [Defense Acquisition Univ Ft Belvoir Va 2004] [Degelsmith et al 1993] [DeLauer 1984] [Della Vecchia et al 2022] [Dement 1990] [Deutsch et al 1997] [DoD Office of Inspector General 2015] [Dodson 1978] [Donahue et al 2008] [Dreier 2022] [Drenthe et al 2019] [Drown and Graham 2010] [Du et al 2025] [Duffy 1993] [Eaton et al 2022] [Ehricke 1963] [Ehricke 1964] [Enthoven 2019] [ESTIMATION OF THE COST OF THE PROJECT TO LAUNCH A SMALL SATELLITE INTO ORBIT 2023] [Etzenbach et al 2026] [Faster, Better, Cheaper? 2003] [Feltus 1979] [Fernandes et al 2019] [Figueroa 2024] [Fisher 2000] [FOURTEEN. Faster, Better, Cheaper 2017] [Franck and Dillard 2006] [French 1983] [Friedland 1965] [Fritz and Sackheim 1982] [Friz et al 2018] [Friz et al 2022] [Gansler et al 2010] [Graham and Hoffman 1999] [Greaves 1997] [Greer 2010] [Gstattenbauer et al 2006] [Guinivan 2004] [Hagnell and Åkermo 2015] [Hamaker 1999] [Hamaker 2000] [Hamid and MacDermott 2015] [Hanford 1969] [Harris et al 2022] [Harvey 2017] [Hauer et al 1963] [Hellman 2006] [Hertzfeld 2000] [Hinkle et al 2011] [Hodson et al 2017] [Ingalls and Scott 2011] [Ivkić et al 2024] [Ivkić et al 2025] [Jacobs 1999] [Jain 2022] [Jo and Ahn 2022] [Jorden and Siegel 1973] [Kang et al 2025] [Kasunic 2004] [Keating 1979] [Keaton 2015] [Keeler 2005] [Kennedy and McClure 2005] [Kha and Hamaker 2015] [Knesek et al 2025] [Koelle 1981] [Koelle 1984] [Koelle 1992] [Koelle 1994] [Koelle 1998] [Koelle 1999] [Koelle 2000] [Kokan et al 2014] [Komar 2017] [Krevor and Wilhite 2006] [Lee et al 1969] [Lee et al 1969] [Lehman et al 2000] [Li 2022] [Long 2014] [Lynch 2011] [Maddux 1999] [Man 1996] [Marcopulos 1998] [Martin 1993] [Maykut 1977] [Maynard 1969] [Maze 1985] [McCleskey and Bartine 2006] [McCleskey et al 2012] [McCown 2011] [McCurry 1995] [McDaniel 2004] [McNicol 2014] [McNicol and Wu 2014] [Meisl 1986] [Meisl 1988] [Meisl 1989] [Miles 1996] [Moore and Cozzolino 1978] [Morel et al 1993] [Morgenthaler 1991] [Mossman and Perkins 2001] [Naseh and Jafarpanah 2022] [Neiss and Brown 1967] [Netzel et al 2025] [Novick 1979] [Oki 2024] [Osterbeck et al 1979] [Parrish 1978] [Pate-Cornell and Dillon 2001] [Friz 2020] [Paxton 2007] [Peffley 1991] [Perry 1979] [Perry 1999] [Porter and Hewitson 2005] [Portz 2004] [Prince and Hamaker 2001] [Prosser 2003] [Puening 1990] [Ralph 1999] [Rasky et al 2001] [Rasky et al 2000] [Rhodes et al 2009] [Rhodes et al 2009] [Rice and Locksley 2000] [Roark and Cuda 2010] [Robinson and Smith 1999] [Robinson et al 2008] [Rogacki 2000] [Rosch and Schor 1990] [Roschli et al 2025] [Rozum 1992] [Rubinstein 2014] [Ruiz-Torres and McCleskey 2000] [Rush et al 1967] [Rutledge 1993] [Sebring and Young 1981] [Shah et al 2023] [Sharma 2019] [Shearer 1997] [Shi et al 2025] [Shuman 2002] [Sims 1978] [Sobel 2013] [Son and Ryu 2015] [Stahl et al 1984] [Stekler 1982] [Stewart et al 2011] [Stroup 1967] [Stuart 1983] [Swan and Swan 2025] [Syscon Corp Washington Dc 1983] [Systems Cost Analysis 1999] [Theisen et al 2015] [Thomas and Hanagud 1975] [Toten et al 1991] [Townsend and Hamilton 1981] [Unal 1990] [Van Wie 1979] [Voas 2001] [Waiss 1987] [Walton and Dumas 1999] [Wang and Stockton 2001] [Washington Univ Seattle Dept Of Statistics 2007] [Watson et al 2014] [Watzin 2001] [West et al 2016] [Westmoreland 1977] [Westwick 2006] [Whitehead 2000] [Wickert 1985] [Winbush and James O. 2012] [Wodele 2013] [Woeppel et al 2014] [Woerner 1995] [Womer and Camm 2003] [Yang 2019] [Yang et al 2016] [Yao et al 2016] [Yelverton 1995] [Yi et al 2023] [Yoo et al 2011] [Young 1992] [Zhao and Tan 2026] [Zhou et al 2026] [Çam and Özkol 2023]

Ablative materials, charring and recession

Ablative materials, charring and pyrolysis, surface recession and throat erosion, in rocket chambers, nozzles and motor insulation and in entry heat shields, with the fire science of charring polymers.

The engine application is the older one. Of the 455 records, 232 date from 2001 or earlier. Of the 186 from 2015 or later, 58 name atmospheric entry, a heat shield or thermal protection, and 44 name a rocket, a motor, a nozzle, a chamber or insulation.

455 records. [Canfield et al 1987] [Abdullah et al 2020] [Ablative material tests under transient heating simulating ballisticreentry 1969] [Achambath et al 2019] [Acharya and Kuo 2007] [Acharya and Kuo 2010] [Achenbach 1971] [Adams 1960] [Adarkar and Hartsook 1966] [Aeschliman et al 1975] [Agrawal et al 2016] [Ahn et al 1998] [Akers et al 1970] [Amar et al 2016] [Amokrane et al 2024] [Ananth et al 2003] [Anderson 1969] [Anderson et al 2024] [Atreya and Baum 2002] [Auerbach 1966] [Ablative Properties of Filament 1966] [Bae et al 2017] [Baker 1969] [Baker 1972] [Balhoff and Pike 1973] [Bano et al 2026] [Bartlett 1964] [Bartlett et al 1971] [Bauer and Kummer 1965] [Başkaya and Hickel 2025] [Beck and Laub 1983] [Behrens and Minier 1998] [Benjamin 1966] [Bernstein et al 2023] [Bhat et al 2016] [Bianchi and Nasuti 2011] [Bianchi and Nasuti 2015] [Bianchi et al 2019] [Bishop and Dicristina 1967] [Bishop and Dicristina 1968] [Blackwell 1988] [Blome et al 1975] [Blumenthal et al 1966] [Boehrk 2017] [Borsch-Supan and Hunter 1987] [Boury et al 2011] [Boyer 2017] [Brecheisen and Ehresman 1971] [Brewer 1970] [Brewer 1970] [Brewster 1989] [Bryan et al 2026] [Budzinski et al 2020] [Bueche 1977] [Bulmer 1972] [Bunker and Nelson 1985] [Butler et al 2016] [Carman 1966] [Castets et al 2001] [Chandler 2023] [Chang et al 2021] [Chang et al 2022] [Chang et al 2023] [Chasman et al 2005] [Chen and Boyd 2017] [Chen and Gokcen 2015] [Chen and Gökçen 2024] [Chen and Milos 1998] [Chen and Milos 2000] [Chen and Milos 2001] [Chen and Wu 2008] [Chen et al 1993] [Chen et al 2015] [Chen et al 2015] [Chen et al 1994] [Chiang and Ma 2004] [Chinnaraj et al 2023] [Chiodi et al 2022] [Clayton 1971] [Clayton and Back 1986] [Clayton 2017] [Clayton 2017] [Clever and Denny 1975] [Cline and Schultz 1967] [Clinton and Wendel 1998] [Cohen et al 1974] [Coheur et al 2017] [Coheur et al 2023] [Cohz et al 1966] [Coleman et al 1968] [Colombo et al 1994] [Condren et al 2024] [Congdon 1973] [Congdon 1974] [Congdon 1995] [Congdon 1996] [Congdon and Curry 2001] [Congdon et al 2002] [Congdon et al 2003] [Cortopassi et al 2008] [Cortopassi et al 2009] [Coskun and Sert 2024] [Coskun et al 2019] [Couch 1973] [Cross 1967] [Cross and Boyd 2017] [Cross and Boyd 2017] [Cross and Boyd 2018] [Dahm and Schaefer 1966] [Damane and Pitot 2024] [Davies and Park 1982] [Davis 1966] [Davis 1968] [Davis and Evensen 1969] [Davuluri et al 2022] [De et al 1990] [Dean et al 1990] [Dec and Braun 2005] [Dec and Braun 2006] [Dec et al 2011] [Delaney et al 1964] [Di Blasi 1993] [Dickerson et al 2004] [Dickey 1968] [Dickey and Jones 1967] [Dicristina and Richards 1977] [Dimitrienko 1997] [Divo et al 1998] [Dolan 1970] [Droms et al 1976] [Eberhart et al 2016] [Effect of water to ablative performance under solid rocket exhaust environment 1993] [Fabrizi et al 1996] [Farmer 1970] [Feng et al 2015] [Feng et al 2016] [Fio Rito 1964] [Fleming 1965] [Fleurotte et al 2022] [Flow Simulation over a Bulbous Heat Shield of a Typical Launch Vehicle 2019] [Fortner et al 2022] [Friedman et al 1967] [Fu and Martin 2023] [Fu et al 2019] [Fu et al 2020] [Fu et al 2021] [Fujita et al 2015] [Funatsu and Hiroyuki 2001] [Gannon and Laszlo 1966] [Gao et al 2019] [Gao et al 2020] [Gao et al 2023] [Gao et al 2024] [Giardini 1986] [Gilligan et al 1989] [Gluck et al 1964] [Gomez 1970] [Gosma et al 2022] [Gosma et al 2023] [Green and Nicolet 1978] [Noffz and Bowman 1996] [Grigat et al 2020] [Gui et al 1999] [Gulick and Edquist 1998] [Guo and Huang 2018] [Guo et al 2020] [Hagemaier and Kleint 1966] [Hahn 1964] [Hall 1988] [Hamad and Nagmeldin m. elamin 2021] [Hannah and Muessig 1970] [Hasan 2022] [Haviland and Medford 1967] [He and Zhou 1992] [He et al 2023] [Henderson and Tant 1983] [Henderson et al 1981] [Herrick 1968] [Hickey et al 2000] [Hickey et al 2001] [Hillberg 1967] [Hoffman et al 2003] [Horiuchi et al 2017] [Howse and Lawrence 2004] [Hsiao and Chung 1986] [Huang et al 1996] [Huang et al 2026] [Hui et al 2023] [Humphrey and Madden 1971] [Ito et al 2020] [Joatton 1970] [Johnstun 2001] [Jones et al 1986] [Joseph et al 2024] [Jumper and Hitchcock 1986] [Kaminsky and Johnson 1964] [Kamps et al 2016] [Kamps et al 2019] [Katcher 2019] [Kaul et al 2002] [Kawabata et al 2019] [Keller 1968] [Kelley and Thompson 1989] [Kemp 1968] [Kendall and Rindal 1964] [Kennedy 1966] [Keswani et al 1983] [Keswani et al 1985] [Kim et al 2000] [Kim et al 2020] [Kimura et al 2019] [Kishore Nath and Mallesham 2023] [Klein 1987] [Klein and Gentilman 1985] [Klein et al 1987] [Knight and Quinn 1971] [Kobayashi and Saperstein 1981] [Kojima et al 2022] [Koo et al 1991] [Koo et al 2023] [Kovach and Moise 1969] [Kryvoruka 1976] [Kuby et al 1962] [Laganelli et al 1974] [Lai and Leu 2023] [Lai and Leu 2023] [Langston et al 2018] [Lariviere and Kezirian 2019] [Laub and McHenry 1982] [Laub and White 2002] [Lee 1965] [Letson et al 1989] [Lewis and Anderson 1998] [Li et al 2015] [Li et al 2015] [Li et al 2015] [Li et al 2016] [Li et al 2016] [Li et al 2016] [Li et al 2019] [Li et al 2020] [Li et al 2021] [Li et al 2025] [Liggett and Menon 2007] [Lin and Ma 2000] [Lin et al 2000] [Lincoln 1981] [Liu and Qizhi 1996] [Liu et al 2019] [Lizhong et al 2002] [Lundell 1969] [Lundell 1982] [Lundell et al 1964] [Lundell et al 1965] [Luo et al 2003] [Maahs 1972] [Machado and Torsani 2020] [Maddu et al 2023] [Marquis et al 2016] [Martin and Boyd 2015] [Martin Co Denver Co 1965] [Mastanaiah 1976] [Mayberry et al 1968] [Mazzaracchio 2018] [McGuire et al 2018] [McHenry and Laub 1983] [McWhorter et al 1999] [Medford 1964] [Menon and Liggett 2007] [Mezines 1968] [Migliorino et al 2021] [Miller et al 2018] [Mills et al 1971] [Milos 1996] [Milos 1997] [Milos and Gasch 2015] [Milos and Marschall 1994] [Milos et al 1997] [Milos and Chen 2010] [Minyushkin and Kryukov 2019] [Mitchel 1971] [Mohan Kumar et al 2015] [Mohan Ramu and Poovathingal 2024] [Morlang and Strassburger 2024] [Morris et al 2026] [Mottram et al 1992] [Moyer and Wool 1970] [Murugan et al 2018] [Nagler 2026] [Narsai et al 2016] [Naughton et al 1998] [Navaneethan et al 2024] [Navaneethan et al 2025] [Nelson and Mezines 1978] [Nichols and Sichel 1967] [Nichols and Sichel 1969] [Nicolet et al 1976] [Nix and Escher 1999] [North 1983] [Odak et al 2025] [Ogawa et al 2019] [Oliver 2017] [Oliver and Stephanou 1963] [Olsen and Chapman 1972] [Ono et al 2024] [Orlik-Ruckemann 1968] [Paglia et al 2019] [Palumbo and Begun 1977] [Papadopoulos et al 2014] [Park and Kang 2002] [Park et al 2004] [Parmenter et al 2001] [Patton et al 2001] [Piacquadio et al 2023] [Pimentel et al 2018] [Potts 1984] [Price et al 2022] [Prussing and Krier 1978] [Puiroux et al 2004] [Py and Daguerre 2000] [Qin et al 2026] [Quinn et al 2023] [Quinn et al 2024] [Randall 1978] [razmjooei et al 2020] [Reich and Jahn 1996] [Research on fabrication and 2026] [Richman 1967] [Richter and Smith 1995] [Riley and Landahl 1968] [Rindal and Moyer 1968] [Ringel et al 2022] [Rinta-Paavola et al 2023] [Risch 2017] [Risch and Laub 1990] [Rito 1965] [Romie 1967] [Rostkowski and Panesi 2022] [Rostkowski et al 2022] [Rotondi et al 2022] [Sabarilal and Kumar 2018] [Saha and Bhowmick 2017] [Saha Deuri et al 1988] [Salazar and Amar 2021] [Salazar et al 2016] [Salvi et al 2026] [Scandelli et al 2023] [Schrooyen et al 2017] [Schrödter and Baltes 1991] [Scoggins et al 2015] [Serio et al 1994] [Shah and Navajas Ortega 2025] [Shi et al 2015] [Shi et al 2018] [Shi et al 2021] [Shih and Cheung 1997] [Shinn 1967] [Shishov et al 1990] [Shivakumar and Cozart 2002] [Shortland and Tsai 1995] [Silver et al 2024] [Slattery 1993] [Slosarik and Swope 1964] [Smith et al 1992] [Smith et al 2015] [Snowdon 1974] [Sohn et al 1999] [Sperow 1965] [Sprague 1963] [Sreejith and Krishnamurthy 1999] [Sreejith et al 1999] [Sreejith et al 1999] [Sreejith et al 2000] [Stadter and Weiss 1976] [Strauss 1967] [Strauss 1974] [Stroud and Brinkley 1975] [Stroud et al 1987] [Su et al 2022] [Sullivan and Kobayashi 1987] [Suzuki et al 2003] [Suzuki et al 2004] [Swann et al 1964] [Swann et al 2017] [Swann and South 1961] [Szasz et al 2015] [Tahmasbi and Noori 2021] [Tatar 2019] [Tatar 2021] [Thakre and Yang 2009] [Thermal Investigation of Charring Materials Based on Pyrolysis Boundary Representation 2015] [Thermal Protection for a Re-Entry Vehicle Using Heat Ablation Process 2015] [Thibaudeau and Whitmore 2026] [Thibaudeau and Whitmore 2026] [Thongsri et al 2022] [Tian et al 2022] [Tian et al 2025] [Tian et al 2025] [Torres-Herrador et al 2019] [Torres-Herrador et al 2020] [Trevino and Candler 2015] [Triebes et al 1978] [Trinh 1994] [Trotsky and Baccarella 2024] [Trotsky and Baccarella 2025] [Tsukamoto et al 2022] [Verderaime 1986] [Viventi 1961] [Vural and Ak 1997] [Wagner 1992] [Wagner et al 2025] [Wakefield and Lundell 1971] [Wakefield and Pitts 1980] [Walker and Zeigler 1968] [Wang and Li 1999] [Wang et al 2019] [Wang et al 2025] [Wei and Zien 2000] [Wei and Zien 2001] [Weng and Martin 2015] [Weng et al 2021] [Wernimont 1993] [White 2014] [Wichman 1985] [Wichman and Atreya 1987] [Wilhelm 1964] [Wilhelm 1965] [Williams and White 2001] [Williamson et al 1973] [Winter et al 2014] [Wise et al 1999] [Wong et al 2015] [Wong et al 2016] [Wool et al 1971] [Wu et al 2024] [Wu et al 2025] [Wunderlin et al 2024] [Xiao et al 1991] [Xu and Yang 1993] [Yamada et al 1997] [Yinda 1986] [Yoko et al 2018] [Yoko et al 2019] [Zhang et al 2023] [Zhang et al 2024] [Zheng 2009] [Zheng et al 2023] [Zheng et al 2024] [Zheng et al 2025] [Zheng et al 2025] [Zhu et al 2022] [Zibitsker et al 2022] [Zibitsker et al 2023] [Zien 1978] [Zien and Wei 1999]

Additive manufacturing and low-cost fabrication

Additive manufacturing and other low-cost fabrication, of rocket chambers, injectors and thrusters and as a process in its own right.

It is almost all recent. Of the 258 records, 236 date from 2015 or later.

258 records. [A Review on Properties of Aerospace Materials Through Additive Manufacturing 2017] [A Simulation Study On A Flexible Manufacturing Systems For Producing Aircraft Engine Parts (WIP) 2017] [Abdala et al 2025] [Adamou et al 2022] [Akbulatov et al 2023] [Allison et al 2019] [An and Li 2023] [Andrianov et al 2025] [Ang et al 2020] [Aqailan and Huh 2025] [Aremu et al 2024] [Aryal et al 2024] [Azhagan et al 2023] [Balles 2022] [Balles 2022] [Barnes et al 2010] [Barros et al 2025] [Battegazzore et al 2024] [Bauer et al 2020] [Benkelman et al 2017] [Betts et al 2011] [Betts and Hardin 2011] [Betts et al 2011] [Biberstein et al 2021] [Biedermann and Meboldt 2020] [Blösch-Paidosh and Shea 2018] [Boyd and Fazelpour 2019] [Broomby and Trifoni 2024] [Bryant 2021] [Bua 1963] [Buchholz et al 2022] [Buettner et al 2023] [Capparelli et al 2026] [Carneiro et al 2020] [Catina et al 2016] [Chandler 2024] [Chandler et al 2026] [Charan and Tibrewal 2025] [Chaudhary et al 2025] [Chekurov 2019] [Chen and Smith 2021] [Chen et al 2021] [Chen et al 2023] [Chen et al 2025] [Cheng and Chou 2017] [Cican et al 2023] [Connell et al 2019] [Cubeda et al 2021] [Cui 2025] [Dangal and Jung 2023] [Deng et al 2020] [Di Caprio et al 2019] [Diegel et al 2020] [Dobrodomov 2025] [Dong et al 2020] [Dong et al 2021] [Dorrell et al 2024] [Durkee et al 2020] [Dziubek et al 2026] [Easley et al 2019] [Effinger et al 1999] [Ehlers et al 2021] [Eom and Hong 2025] [Ergin et al 2024] [Ermakova and Mehmanparast 2022] [Ertugrul 2024] [Eskue 2023] [Fasel et al 2020] [Features of the Development of Additive Manufacturing Methods in Application to Liquid Propellant Rocket Engines 2023] [Fedotowsky et al 2024] [Fodor 2017] [Fritz et al 2017] [Fuller 1973] [Gawron et al 2023] [Gaynor and Johnson 2020] [Giambelli et al 2026] [Giurgiutiu and Lin 2004] [Gleadall 2021] [Godderidge et al 2024] [Gotzig 2015] [Gradl and Protz 2020] [Gradl et al 2017] [Gradl et al 2018] [Gradl et al 2018] [Gradl et al 2021] [Gradl et al 2024] [Gradl and Brandsmeier 2016] [Gradl et al 2019] [Gradl et al 2019] [Großmann et al 2020] [Gu et al 2017] [Gu et al 2023] [Guo et al 2020] [Gupta et al 2022] [Han and Lu 2018] [Hanks and Frecker 2019] [Hernandez et al 2019] [Hernandez-McCloskey et al 2023] [Hicks and Siddiqui 2026] [Hitt 2018] [Hitt 2018] [Hoppin et al 1980] [Hudson and Fidan 2024] [Imani and Khanzadeh 2021] [Jansari et al 2026] [Jere et al 2025] [Jing et al 2021] [Johnson and Kujawski 2025] [Vishnu Prasad et al 2025] [Kalia and Ameli 2024] [Kamps et al 2018] [Kapelyushin et al 2026] [Karakai and Karpovych 2026] [Keller et al 2024] [Keller et al 2025] [Keller et al 2025] [Kennedy and Weldon 2024] [Kerstens et al 2021] [Kim et al 2019] [Kim et al 2025] [Knauer and Edman 1991] [Knauer et al 1993] [Ko et al 2021] [Krishnan and Thakur 2024] [Krishnanand and Taufik 2021] [Kumar et al 2019] [Kumar et al 2020] [Kunka and Jacob 2017] [Kuntanapreeda and Hess 2020] [Lan 2017] [Landau et al 2020] [Lang et al 2021] [Lazarets 2026] [Lee et al 2020] [Lee et al 2023] [Leonetti et al 2026] [Li 2020] [Li et al 2020] [Li et al 2023] [Lim et al 2025] [Lindberg and Campbell 2019] [Liu et al 2020] [Luo 2024] [Ma et al 2024] [Mackey et al 2026] [Mahan and Menold 2020] [Malim et al 2023] [Man’ko and Коzis 2019] [Stachulla et al 2019] [Mathur et al 2023] [McClain et al 2019] [McClain et al 2019] [McConaha and Anand 2020] [McCoy 1988] [McKnight et al 2015] [Meier and Key 2025] [Melo et al 2022] [Michell 2016] [Minguella-Canela et al 2023] [Moetazedian et al 2021] [Monokrousos et al 2024] [Mosolov et al 2021] [Mozaffar et al 2023] [Muhammad 2021] [Murugan et al 2023] [Nagulin et al 2022] [Nair et al 2019] [Norman et al 2021] [Ntintakis et al 2025] [Oh et al 2018] [Ortega et al 2020] [Ortega et al 2023] [Oztan and Coverstone 2021] [Oztan et al 2021] [Palacios Hervas 2026] [Pantoja and Wallick 2023] [Patel et al 2019] [Peng et al 2020] [Peterson and Liu 2015] [Petsiuk and Pearce 2022] [Peugeot et al 2014] [Phillips et al 2020] [Polizzi et al 2025] [Poulopoulos et al 2026] [Prasad et al 2022] [Protz et al 2014] [Protz et al 2016] [Pu et al 2026] [Pustovyi 2026] [Qu et al 2024] [Rahimi et al 2023] [Rastegarzadeh and Huang 2023] [Ringel et al 2022] [Rivas Santos et al 2020] [Robertson et al 2021] [Rouina et al 2021] [Rupert and King 2025] [Sandoval et al 2018] [Schuller et al 2024] [Shams et al 2021] [Shen et al 2020] [Shynkarenko et al 2024] [Simpson 2021] [Sirenko 2025] [Slowik 2019] [Smith and Bardaweel 2018] [Snow and Hunsaker 2021] [Special Section Designing for 2017] [Springer et al 2020] [Stickler and Keller 1998] [Sung and To 2026] [Swensen 2024] [Tam et al 1996] [Tam et al 1997] [Tam et al 1998] [Tam et al 2000] [Tam et al 2002] [Teasley et al 2021] [Teoretical-experimental Comparison of the Models of Additively Manufactured Swirl Injectors Based on the Hydraulic Testing Results 2023] [Thomas 2022] [Thomas 2023] [Thompson et al 2019] [Thompson et al 2026] [Thostenson et al 2024] [Tian 2025] [Titotto 2024] [Tommila and Hartsfield 2017] [Tucker and Schmidt 2016] [Unternbaumen et al 2026] [Van Den Berghe et al 2020] [Veerasamy et al 2025] [Wakefield 1986] [Walker et al 2020] [Wang and Song 2025] [Wang and Xia 2022] [Wang et al 2017] [Wang et al 2018] [Wang et al 2021] [Wang et al 2021] [Warga 1970] [Weber and Ruff-Stahl 2017] [Whitmore 2015] [Whitmore and Heiner 2019] [Whitmore and Merkley 2019] [Wiberg et al 2019] [Woodger et al 2025] [Woods et al 2016] [Wright et al 2023] [Wu and Baur 2024] [Wu and Yuan 2025] [Wu et al 2024] [Xiong et al 2022] [Yaghi et al 2019] [Yang et al 2023] [You and Park 2021] [Zappino et al 2026] [Zawaski and Williams 2020] [Zhuravlev et al 2025]

Gas-side heat transfer and the cooling of chambers

Gas-side heat transfer in chambers and nozzles, and film, regenerative and transpiration cooling, with the conjugate heat transfer and cooling-channel studies that share their physics.

504 records. [A.A. et al 2025] [Ables and Davis 2014] [Abulawi et al 2025] [Agarwal et al 2021] [Aksonov 2023] [Alves Avelino and Chalhub 2021] [Amato et al 2016] [Amos et al 1958] [An Overview on the Design Variants for Organization of the Liquid Film Cooling in Lpre Combustion Chambers 2023] [Anderson et al 1993] [Andrews et al 1986] [Anum et al 2022] [Arakeri 1980] [Arhami et al 2025] [Martinez et al] [Armstrong 1986] [Arun and Prakash 2018] [Aslan et al 2015] [Assadi et al 2022] [Assonitis et al 2024] [Azuma et al 2016] [Azuma et al 2019] [Bacci et al 2025] [Back and Cuffel 1970] [Back and Cuffel 1971] [Back and Cuffel 1972] [Back et al 1964] [Back et al 1970] [Back et al 1970] [Back et al 1969] [Baek and Ahn 2020] [Barbato 2023] [Bartle and Leadon 1960] [Bassina et al 2001] [Bates et al 2002] [Batista et al 2024] [Batista et al 2026] [Becchi et al 2016] [Beddini and Owano 1987] [Beitel 1991] [Bejan 1983] [Benderskii and Chernova 2022] [Benderskiy and Chernova 2021] [Benderskyi and Chernova 2020] [Best 1982] [Betti et al 2015] [Bi et al 2025] [Bills et al 2016] [Bobisud 1983] [Boden 1951] [Bohn and Moritz 2001] [Boldman et al 1967] [Bolshov et al 1996] [Bose 1978] [Broatch et al 2019] [Broatch et al 2020] [Brooker et al 1998] [Brown and Cornwell 1964] [Brown 1991] [Buchanan et al 2018] [Bulat et al 2024] [Burkhardt and Hayes 1992] [Busam et al 1999] [Bäker et al 2015] [Calhoon et al 1973] [Campo et al 1996] [Carden 1964] [Cardillo et al 2023] [Champion and Deshaies 1995] [Chang 1956] [Chang et al 1996] [Chang et al 2026] [Chavez and Dawson 1978] [Chen et al 2015] [Chen et al 2021] [Cheng and Wong 2023] [Cherkupalli and Sandeep 2022] [Chiu 1986] [Choi et al 1997] [Chou and Kalina 1982] [Chu et al 2019] [Chu et al 2025] [Clayton 1999] [Clayton 2001] [Cocirla et al 2025] [Coleman 1986] [Concio et al 2021] [Concio et al 2023] [Connell et al 1992] [Cooper and Martin 2021] [Coulbert 1963] [Crachi et al 2024] [Croce et al 2015] [Cui 2020] [Lise, i, M H N 1995] [Da Soghe and Bianchini 2019] [Daimon et al 2017] [Darbandi and Jalali 2022] [Das et al 1988] [Delogu et al 2026] [Delogu et al 2026] [Deng et al 2016] [Deng et al 2026] [Development of a Differential Model for Cooling an Lpre Chamber by an Incompressible Fluid 2024] [Dharshan 2019] [Di et al 2026] [Dicristina 1979] [Dillon and Line 1956] [Dinh and Trifoni 2023] [Djeffal et al 2024] [Dmitrenko 1998] [Dresia et al 2023] [Drobyshev 2026] [Du et al 2019] [Duan et al 2022] [Dudareva 2025] [Dunlap and Kuethe 1961] [Dutta and Smith 2020] [Dutta et al 2016] [Dzodzo 2022] [Eaton and Mathias 2000] [Eckert and Goldstein 1982] [Elkind 1964] [Elliott and Rose 1957] [Emidio et al 1998] [Emory 2022] [Enomoto and Furuhama 1989] [Evaluation on the Regenerative 2004] [Fan and Cheung 1996] [Fan et al 2024] [Fassin et al 2016] [Fayyazi et al 2025] [Fehr and Wensley 1970] [Feldkamp et al 2025] [Ferreira and Dourado 2018] [Fidler and Hays 2026] [Fiedler et al 2015] [Fiedler et al 2019] [Fiore et al 2024] [Fiore et al 2025] [Fischer and Norris 1949] [Fragnaud 1996] [Franceschetti et al 2025] [Froehkle et al 1998] [Fu et al 2026] [Furlong et al 2025] [Garcia et al 2020] [Garimella and Nenaydykh 1996] [Gelain et al 2022] [Georgieva 2026] [Giovanetti et al 1983] [Giovanetti et al 1984] [Gordon 1950] [Gorelov 2019] [Gorelov 2023] [Gorelov and Tyul’kov 2018] [Graber and Clark 1972] [Hall et al 1994] [Han et al 2024] [Hao et al 2017] [Harvazinski and Houba 2022] [Harvazinski and Houba 2023] [Harvazinski et al 2024] [Hasegawa and Yoshioka 2019] [He and Liu 2018] [He et al 2019] [Hegab and Kassoy 2001] [Heldens et al 2021] [Herman and Melnik 1962] [Heyda 1957] [Hishida et al 1982] [Ho et al 2016] [Hodge and Taylor 1991] [Hoffman and Eaton 2021] [Hoffman et al 2018] [Hoffmeyer et al 2019] [Horton 1976] [Hou et al 2017] [Howell 1968] [Hu and An 2024] [Huang et al 2022] [Höglauer et al 2015] [Hötte and Haupt 2020] [Ichiyanagi et al 2020] [Indelicato et al 2021] [Ingebo 1961] [Ishii et al 2019] [Issakhov et al 2024] [Campbell et al 1964] [Jaiswal et al 2024] [Jennings and Morel 1987] [Jeon and Park 2026] [Jeong et al 2023] [Jeong et al 2024] [Jia 1987] [Jia and Chung 1996] [Jia et al 2018] [Jiang et al 2023] [Jing et al 2018] [Johnson et al 2026] [Kacynski and Hoffman 1994] [Kacynski et al 1987] [Kang et al 2024] [Karabey and Bozdogan 2022] [Kaufman and Louis G. 1964] [Kaye and Brown 1954] [Keener et al 1995] [Kendall and Holman 1996] [Kilham and Dunham 2019] [Kim and Choi 2024] [Kim et al 2015] [Kim et al 2025] [Knab et al 1998] [Kolesnik and Novikov 2023] [Kringe et al 2022] [Krinsky 1978] [Krishnamoorthy 1982] [Kumar and Bansal 2024] [Kumar et al 2015] [Kumar et al 2021] [Kuwahara et al 2001] [Kühlwein et al 2024] [Laganelli 1970] [LaGraff 2001] [Lakshminarayana and Luo 1996] [Latini et al 2022] [Lee 1963] [Lee 1964] [Lee and Lee 1995] [Lee and Smith 1974] [Lee et al 2024] [Leitner 1986] [Levikhin and Musteikis 2025] [Li and Wang 2024] [Li et al 2017] [Li et al 2024] [Li et al 2025] [Librizzi and Cresci 1964] [Lienhard and Napolitano 1996] [Lieu 1964] [Lindqvist et al 1997] [Linne 1993] [Liquid rocket engine fluid-cooled 1972] [Litchfield and Norton 1982] [Liu and Tiwari 1996] [Liu et al 1998] [Liu et al 2022] [Liu et al 2022] [Liu et al 2023] [Liu et al 2023] [Liu et al 2026] [Lobanov et al 1998] [Longobardo et al 2026] [Luan et al 2017] [Ludescher and Olivier 2018] [Lv et al 2023] [Lytle and Webb 1994] [Ma 2016] [MacFarlane and Madell 1964] [Machado 2025] [Maciejewski 1995] [Makhija et al 2024] [Maldonado 1994] [Manjhi and Kumar 2019] [Marocco and Franco 2016] [Masiulaniec et al 1995] [Mastanaiah 1978] [May and Burkhardt 1991] [Mayer 1961] [Mayer and Prickett 1986] [Mayo et al 2016] [Mecklenburg 1966] [Mehdizadeh et al 2017] [Mehta 1981] [Meinicke et al 2018] [Mendu and Parameswaran 1995] [Merzlikin et al 2019] [Michel 1983] [Micklow 1996] [Noel and Massier 1962] [Mirzamoghadam 1991] [Mitsuishi et al 2020] [Miyashita et al 2026] [Modise and Magalakwe 2022] [Modlin and Colwell 1992] [Mondal and Sharma 2025] [Moosaie 2024] [Mukambetov and Borovik 2022] [Mulla et al 2023] [Multi-dimensional modeling of convective heat transfer with application to I. 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Liquid rocket engines, turbopumps and combustion

Liquid rocket engines, their cycles, gas generators, turbopumps, injectors and combustion, including combustion instability and kerosene, methane and hydrogen propellants.

678 records. [Adams 2004] [Adoua and Page 2017] [Aerojet-General Corp Sacramento Ca 1966] [Air Force Research Lab Edwards Afb Ca 2000] [Alliot et al 1990] [Altseimer 1952] [Alves Almeida et al 2024] [Alvis and Chessman 1957] [Amateur Gas-Propelled Rocket Engine Development and Advanced Rocket Design 2004] [Aminov et al 2023] [An experimental study on air intake performance for a rocket/ramjet engine 1981] [Analysis of the Influence of the Design Parameters of the Upper Stage Liquid Propellant Rocket Engine Pump on Its Cavitation Characteristics 2023] [Anderson et al 2012] [Anderson et al 2013] [Anderson et al 2015] [Andreadis et al 2002] [Andreadis et al 2003] [Andrews et al 2018] [Anisimov et al 2016] [Appel and Kruger 1980] [Application of the functional diagnostics system and the emergency protection system of a liquid rocket engine during fire tests 2024] [Ardema et al 1995] [Arita et al 2000] [Armbruster et al 2021] [Atamanchuk 2025] [Augousti et al 2018] [Ayran et al 2026] [Bailey 1964] 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1995] [Duggleby et al 2025] [Duke and Houghton 1966] [Duke and Houghton 1967] [Dunn 1990] [Durham and Kirk 1972] [D’Alessandro et al 2021] [D’Souza et al 2022] [Edwards et al 2003] [Effect of Distributed Injection of Air into the Afterburning Chamber of a Ram-Rocket Engine on the Efficiency of Combustion of Boron Particles 2017] [Eggleston 1995] [Eklund 2004] [Elias and Gordon 1952] [Ellis 2013] [Ellis et al 2001] [Emdee 2001] [Enomoto and Furuhama 1985] [Enomoto and Furuhama 1986] [Erol and Ünsal 2026] [Etzenbach et al 2025] [Fang 1984] [Fanqi et al 2023] [Farmer et al 1996] [Farmer et al 1998] [Farmer et al 1999] [Felix and Bohl 1959] [Feng et al 1985] [Fernandez et al 2018] [Ferraiuolo et al 2023] [Frady et al 2002] [Franklin and Tinsley 1970] [Freiherr 2016] [Friedman 1953] [Fujio and Ogawa 2024] [Fultyn 1968] [Funazaki et al 2020] [Fusselman et al 2019] [Gale and Moedt 1962] [Ganesan et al 2025] [Gangeh et al 2023] [Gao et al 2023] [Gao et al 2025] [Garwol 2024] [Gavitt et al 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al 1990] [Keith 1992] [Keller and Gerlinger 2016] [Keller et al 2023] [Kemp et al 2007] [Kenny et al 2011] [Kerrian et al 2022] [Khalil and Whitelaw 1977] [Khalimonov and Ng 2025] [Khan et al 2022] [Kim and Kim 2026] [Kim et al 2020] [Kim et al 2021] [Kim et al 2025] [Kim et al 2025] [Kimura et al 2015] [Kimura et al 2019] [Kirchberger et al 2019] [Klimenko et al 2002] [Kobayashi 2024] [Koehlinger et al 1992] [Kolesovas and Svitra 1976] [Komar and Christenson 1996] [Koschel 1998] [Kretschmar 1953] [Krühsel 2003] [Kunz 1967] [Kurokawa et al 1994] [Kwak et al 2018] [Kwon et al 2004] [Lacefield and Sprow 1994] [Lakshminarasimha 1991] [Lakshmipuram Raghu et al 2024] [Large eddy simulation of 2023] [Larosiliere and Jeng 1991] [Larson 1973] [Lawdensky and Culbreth 2018] [Lawhead and Combs 1963] [Lawrence 1945] [Lebrun and Ngendakumana 1990] [Lechtenberg and Gerlinger 2020] [Lee 2026] [Lee and Kim 2015] [Lee et al 2015] [Lee et al 2015] [Lee and Elam 2001] [Leese 1966] [Lentini et al 2003] [Leto 2019] [Leto 2020] [Leto et al 2016] [Levine 1965] [Li et al 2009] [Li et al 2011] [Li et al 2021] [Li et al 2025] [Liang et al 1985] [Liang et al 1986] [Liang et al 2021] [Liang et al 2022] [Liavåg et al 2024] [Lim et al 2020] [Lin 1989] [Lin et al 2017] [Lin et al 2023] [Lin et al 2023] [Lineberry et al 2004] [Liou et al 1993] [Litchford and Jeng 1992] [Litchford et al 2000] [Liu et al 1995] [Liu et al 2025] [Llewellyn et al 2025] [Lokhtin et al 2020] [Loomis 1994] [Ludwig et al 2021] [Lutsenko 2023] [Ma et al 2025] [Ma et al 2026] [Mah 1999] [Majumdar 1975] [Majumdar et al 2000] [Majure and Robinson] [Makaron and Fedyayev 1996] [Malekzadeh et al 2025] [Manski and Martin 1988] [Marszałek 2019] [Martin 1992] [Martin and Webb 1958] [Maru et al 2026] [Maskery et al 1995] [Matheson 1968] [Matthews 1957] [Mattice 1982] [Maul et al 2004] [Maul et al 2005] [Mayer and Kruelle 1992] [Mayer and Krulle 1995] [Mayer and Tamura 1995] [Mboyi et al 2015] [McDowell et al 2025] [McGarr 1947] [McKamey and Landrum 2001] [McLAFFERTY 1970] [Medvedev 1971] [Meinköhn 2001] [Mellish 1979] [Mellish 1980] [Micci 1997] [Mickola 1961] [Mikhalchenko 2023] [Mishra and Ghosh 2017] [Mishra and Ghosh 2017] [Mitchell 1946] [Mohler 1965] [Morehart 2021] [Morinière et al 2023] [Morris 2003] [Morris 2003] [Morse et al 2024] [Moruzzi et al 2018] [Mosolov and Sidlerov 2019] [Motomura 2025] [Mueller 1966] [Mueller et al 1999] [Murashko 2025] [Murphy et al 2026] [Muss et al 1991] [Mykhalchyshyn et al 2018] [Müller et al 2017] [Nagashima et al 2022] [Nagashima et al 2023] [Nagata 2023] [Najjar and Zaamout 1992] [Naul 1945] [Newhall 1965] [Ni et al 2021] [Nicastro et al 2025] [Nie et al 2025] [Niiya et al 1993] [Nikitaeva 2020] [Nix and Staton 2004] [Noland et al 2026] [None 1959] [Noonan et al 2001] [Nuclear rocket engine cycle selection 1963] [Numerical Modeling of Pulse 2003] [Obrien and Salkeld 1980] [Oefelein 2003] [Okayasu et al 1983] [Olds and Bradford 2001] [Olds et al 1997] [Olds 1996] [Omata and Tsutsumi 2022] [Omata et al 2022] [Omori 1973] [Optimal Design of Fuel-Rich Gas Generator for Liquid Rocket Engine 2004] [Ortwerth et al 1997] [Osborn and Schiewe 1958] [Otsuka and Takiyama 1967] [Otto and Flage 1960] [Ozaki et al 2025] [O’Brien and Lewis 2001] [Pages and Achipa 2026] [Paing 2023] [Palaszewski 1990] [Palaszewski 1998] [Palaszewski 1999] [Palaszewski and Powell 1991] [Palaszewski and Powell 1994] [Palaszewski and Zakany 1995] [Pande 1994] [Parkes and Conomos 2024] [Patel 2016] [Paula et al 2026] [Pempie et al 2001] [Penner and Datner 1955] [Perez et al 2024] [Perry et al 2019] [Petrenko 2025] [Petrishchev 2017] [Piecewicz 1942] [Pillow 1968] [Platt and Hanner 1965] [Podolchak 2019] [Popov et al 2016] [Popov et al 2017] [Popp and Schmidt 1996] [Pouliquen 1978] [Pouliquen 1978] [Preller and Smart 2015] [Princeton Univ Nj 1952] [Prochnicki et al 2018] [Prudviraj et al 2020] [Puccinelli et al 2025] [Purcell et al 2025] [Putre 1971] [Qi et al 1998] [Qi et al 2021] [Qi et al 2022] [Qin et al 2016] [Quentmeyer 1990] [Sackheim 1992] [RADIATION EFFECTS ON A NUCLEAR ROCKET ENGINE SYSTEM. Final Report 1961] [Ragsdale 1970] [Rahn et al 2021] [Rajan et al 2019] [Ram et al 2025] [Ramsthaler et al 1991] [Ray 2003] [Reardon 1997] [Reardon et al 1964] [Reeves et al 2024] [Rehder 1977] [Rehder 1977] [Reinhardt 1968] [Reinkenhof and Schmucker 1978] [Reusable single-state-to-orbit vehicle concept utilizing composite engines 1984] [Ricci et al 2016] [Ricci et al 2023] [Rich and Mellor 1995] [Robertson et al 2021] [Robison 1953] [Rocker et al 2003] [Rodríguez Otero et al 2020] [Rojas-Oviedo et al 2001] [Rose and Niemeyer 2021] [Rubey 1985] [Rudinskii and Yagodnikov 2021] [Saboktakin and Monjezi 2024] [Saccone et al 2018] [Saccone et al 2019] [Sackheim et al 1974] [Sakai et al 1973] [Sakai et al 2024] [Sangwan and Banik 2023] [Santhini S Lal et al 2015] [Sasmal et al 2023] [Sato et al 2018] [Schley 1994] [Schmid and Yamada 2017] [Schoenman 1988] [Schoenman 1982] [Schweitzer 1952] [Scott 1963] [Scott and Ko 1968] [Seifert 1952] [Seitz and Gerlinger 2021] [Seitz and Gerlinger 2024] [Senchev et al 2024] [Seo et al 2022] [Seralathan et al 2022] [Sergienko et al 1995] [Shaffer and Askari 2020] [Shalmaee et al 2024] [Sharmila and Samad 2026] [Sheer 1961] [Shen et al 2025] [Shi 2016] [Shoji 1981] [Sichler et al 2018] [Sierra et al 2017] [Singelmann and Mueller 1948] [Siva et al 2023] [Siva et al 2023] [Slawecki et al 2026] [Small Engine, Big Output 2019] [Smallwood et al 2025] [Smith 1956] [Smith et al 1975] [Smith et al 2002] [Smith et al 1998] [Smith et al 1998] [Snell 1963] [Snellgrove et al 2003] [Sofyan and Wuwung 2018] [Sohn et al 2004] [Son et al 2012] [Son et al 2021] [Soudarin et al 2025] [Souverein et al 2019] [Stechmann and Heister 2016] [Stephenson 1988] [Sternfeld 1972] [Stewart and Martin 1995] [Strauss 1964] [Streby et al 1999] [Stryczniewicz et al 2025] [Sukachevskyi 2026] [Summerfield 1951] [Summerfield 1951] [Sung et al 2001] [Sutton 1970] [Swaim and Dennies 1991] [Swan and Vizzini 1988] [Szalkowski et al 2024] [Rafeeque 2025] [Tacussis et al 2016] [Tamura et al 1987] [Tamura et al 2003] [Tang et al 2022] [Tang et al 2026] [Taylor 1992] [Taylor and Emrich 2016] [Taylor et al 1971] [Techniques for rocket engine 1965] [Tedrick 1965] [Tellier 1964] [The Application of the Extended Cells Method to Simulate the Flow of Combustion Gases in the Lpre Chamber 2023] [Thiede et al 2016] [Thiede et al 2017] [Thomas and Leonard 1995] [Thornburg 2002] [Tokunaga et al 2024] [Tou et al 1978] [Tournes and Johnson 1998] [Tournes et al 1998] [Traudt 2024] [Trinh 1999] [Truong et al 2018] [Trushlyakov and Zharikov 2016] [Trushlyakov et al 2018] [Tsentis et al 2021] [Tsongas and White 1989] [Tsutsumi et al 2019] [Tsutsumi et al 2021] [Turbine Engine Hot Section 1984] [Turner 2024] [Turushov et al 1995] [Ueda et al 2015] [Umeoka et al 2021] [Valeev and Kondratyeva 2022] [van Schyndel et al 2025] [Ventrice et al 1979] [Ventrice et al 1979] [Ventura and WErnimont 2001] [Vickers 2015] [Vinogradov et al 1992] [Vulpetti 1987] [Wahlen 1995] [Walker et al 2017] [Waltrup et al 2002] [Wan et al 2026] [Wang et al 1996] [Wang et al 1999] [Wang et al 2009] [Wang et al 2011] [Wang et al 2017] [Wang et al 2022] [Wehrmeyer et al 2000] [Wei et al 2022] [Weiss and Merkle 1991] [Wen 2023] [White 2000] [Wickman 1994] [Widargo and Anghaie 1999] [Widmer 1963] [Wilcox] [Williams 1968] [Williams et al 2017] [Winter et al 2025] [Wisler et al 2007] [Wisniewski et al 2019] [Wong and Brown 1965] [Wu et al 2020] [Wu et al 2023] [Xie et al 2026] [Xiong et al 2025] [Yamanishi et al 2004] [Yamashiro et al 2024] [Yang 2004] [Yang et al 2015] [Yang et al 2024] [Yang et al 2024] [Yao et al 2022] [Yaqun et al 2020] [Yatsuyanagi et al 1985] [Ye et al 2025] [Yi et al 2019] [Yi et al 2023] [Yi et al 2025] [Yong and Wu-Qi 2023] [Young 1970] [Youngquist 1947] [Yu 2024] [Yu et al 2026] [Yungster and Trefny 1999] [Yungster et al 1997] [Yuwei et al 2024] [Zakrajsek 2000] [Zarubin et al 2016] [Zarubin et al 2018] [Zeng et al 2021] [Zhang and Li 2017] [Zhang et al 2020] [Zhang et al 2023] [Zhang et al 2023] [Zhang et al 2024] [Zhang et al 2025] [Zhao et al 2025] [Zhen et al 2024] [Zhou et al 2021] [Zhuang and Sun 2002] [Zhuang et al 1999] [Zhukov and Heinrich 2019] [Zimmerli et al 2025] [Zinn and Powell 1971] [Zinn et al 2005] [Zucrow 1949] [Zucrow and Warner 1950] [Zurbach et al 2002] [Ševčík 2025]

Solid and hybrid rocket motors

Solid and hybrid rocket motors, their propellants, grains, cases and combustion.

338 records. [Advisory Group for Aerospace Research and Development 1979] [Akiba et al 1983] [Alanyalioglu 2017] [Alavilli et al 2000] [Albanese et al 2012] [Alqaleiby et al 2022] [Alsaidi et al 2024] [Amano 2024] [Amano and Yen 2015] [Amano et al 2015] [Ao et al 2022] [Aoki and Fukuchi 2010] [Arkhipov et al 1999] [Bachrach 1987] [Bachurin et al 2015] [Baetz 1975] [Baetz 1976] [Baker et al 1994] [Barato et al 2017] [Barkley et al 2019] [Baron et al 1998] [Baum and Levine 1982] [Baum and Levine 1984] [Benderskyi and Chernova 2020] [Benton et al 1976] [Berman and Cheney 1953] [Berman and Logan 1952] [Bianchi and Neri 2015] [Bianchi et al 2019] [Biggs 2022] [Blomshield 1989] [Bowman 1967] [Brewer et al 2016] [Briones and Wuerker 1978] [Browne 1964] [Brownlee 1963] [Buckmaster 2001] [Bunker and Prince 1992] [Cai and Hou 1990] [Campbell 1962] [Candler 2001] [Cang and Wang 2024] [Cantey 1965] [Carpenter and Jeffus 1962] [Carpenter and Jeffus 1963] [Cha and de Oliveira 2022] [Chen et al 2026] [Cheng 1961] [Chiba et al 2015] [Chiba et al 2016] [Chow and Jin 1991] [Ciepluch 1971] [Clayton 2012] [Coates 1971] [Coats 1981] [Cohen 1980] [Cohen and Strand 1981] [Composite propellant combustion modeling with a porous plate burner 1976] [Cook et al 1991] [Cook et al 1997] [Cortopassi et al 2012] [Crocco and Cheng 1953] [Culick 1970] [Culver and Mueggenburg 1991] [Daines and Boyd 1977] [Dalla Vecchia de Lima et al 2025] [Davis 1982] [Davydov and Egorov 2001] [De Leo 1963] [De Morton 1977] [Deng et al 2022] [Deng et al 2025] [Derr and Osborn 1970] [Derr and Osborn 1970] [Desnoyer 1987] [Dethloff 1961] [Devadoss 1985] [Di Martino et al 2019] [Don and Phen 1971] [Donat 1993] [Dong et al 2021] [Dosbolayev et al 2026] [Dunlap et al 1974] [Dyer and Warner 1971] [Egorov 2022] [Elston 1963] [Ergin and Karabeyoglu 2025] [Esiyok and Candarli 2018] [Estler 1989] [Excelco Developments Inc Silver Creek Ny 1963] [Fasulo et al 2023] [Flanagan et al 1995] [Fong 1964] [Fong et al 1964] [French and Coats 1999] [Sclippa et al 1999] [Gao et al 1999] [Gao et al 2023] [Glick 1974] [Glick 1976] [Gomez Monroy and Flores Moreno 2024] [Gostintsev et al 1972] [Gowariker 1965] [Gowariker 1966] [Green 1963] [Grey 1954] [Grossi et al 2024] [Grubelich et al 1993] [Haff 1984] [Haff 1983] [Hammond et al 1970] [Harayama et al 1983] [Hardesty 1970] [Hart and McClure 1965] [Hassan 1965] [Haugen 1998] [Hauser and Helfrich 1963] [Heeg et al 2020] [Helmy 1994] [Hermance 1967] [Hermsen 1981] [Herrington 1964] [Hosomi et al 2019] [Hutcherson et al 2024] [Hydrogen peroxide hybrid rocket engine performance investigation 1994] [Ignition Characteristics of a Metallized Composite Solid Propellant by a Group of Hot Particles 2016] [Inami and Shanfield 1964] [Istratov et al 1996] [Iwasaki et al 2016] [Izham Izzat Ismail et al 2022] [Paul Murugan et al 2025] [Jain and Kumar 2022] [Jesen 1977] [Jin et al 2024] [Johnson and L’Ecuyer 1968] [Jones and Kruse 1965] [Kageyama et al 2019] [Kahraman et al 2020] [Kanazaki et al 2016] [Kanazaki et al 2017] [Karthikeyan and Shimada 2017] [Kawata et al 1994] [Kearney and Moss 1993] [Kerstein 1987] [Kim and Kim 2001] [Kim and Kim 2026] [Kim et al 2024] [King 1980] [King 1982] [King 1985] [Kishore et al 1989] [Kitagawa et al 2016] [Knauber 1995] [Ko et al 2019] [Kordig and Fuller 1967] [Kovalev et al 2023] [Kozlov et al 1992] [Krepski et al 2025] [Kuby 1964] [Kumar Bihari et al 2022] [Lapp and Quesada 1992] [Larson 1987] [Leighton 1982] [Lemoine 1975] [Levinsky et al 1970] [Li and Li 2023] [Li et al 2023] [Li et al 2024] [Liaw and Chen 1995] [Liaw et al 1993] [Lin and Chiu 1995] [Lips 1976] [Liu and Wang 1999] [Liu et al 2004] [Liu et al 2015] [Liu et al 2021] [Lores and Zinn 1973] [Lyon Inc Detroit Mi 1961] [Lyon Inc Detroit Mi 1963] [Ma et al 2020] [Macek and Semple 1972] [Majerus and Tamekuni 1965] [Marlow 1992] [Martin 1962] [Martinez et al 2019] [Marxman and Gilbert 1963] [marxman and Wooldridge 1969] [Mason and Broadhurst 1992] [Masuhara et al 2024] [Mathes 1961] [Matos et al 2022] [Maw et al 2004] [Mayer and Stowe 2000] [McClain et al 2021] [Meadors et al 2000] [Mehta et al 2011] [Meichin and Tanaka 2019] [Miccio 1998] [Miccio 2016] [Michigan Univ Ann Arbor 1963] [Moon and Lee 2016] [Moore and Phelps 2011] [Moran and Houston 2011] [Morita 2020] [Morrow and Petersen 2017] [Moto et al 2021] [Mugot et al 2024] [Mugot et al 2026] [Mungas et al 2003] [Murari et al 2019] [Naka 2021] [Nardozzo et al 2019] [Naval Weapons Center China Lake Ca 1963] [Naval Weapons Center China Lake Ca 1964] [Neilson and Gilchrist 1968] [Nelson and Fields 1995] [Netzel et al 2025] [Nguyen 2020] [Nidagalkar et al 2024] [Nielsen 1966] [Obreque and Díaz 2022] [Ogawa and Sasaki 2017] [Oishi et al 2023] [On the axial velocity profile in nozzleless solid rocket motors 1982] [Osborn and Bonnell 1961] [Osborn and Davis 1961] [Osherov and Natan 2000] [Osherov et al 1996] [Passarani et al 2026] [Pearson and Sutton 1966] [Perlmutter and DePierre 1965] [Person et al 2026] [Pesqueira 1945] [Petrenko and Popov 1996] [Pinalia et al 2021] [Plane 1963] [Plane 1964] [Plane 1964] [Plane 1964] [Povinelli and Rosenstein 1964] [Prianto et al 2021] [Price 1964] [Price 1965] [Price and Dehority 1967] [Price et al 1971] [Prince et al 1989] [Prins et al 1992] [Qu et al 2024] [Quero Granado et al 2021] [Quilici 1984] [Raji and Rose 2024] [Ramadhan et al 2024] [Ramohalli and Magiawala 1981] [Rampazzo and Barato 2023] [Rastogi and Ouseph 1965] [Riehl et al 2002] [Rison et al 1967] [Rosciszewski 1965] [Rotondi et al 2023] [Rowland and Grubelich 1996] [Roys 1977] [Ruesch et al 2021] [Sagawa et al 2019] [Saha and Chakraborty 2016] [Saiki et al 2026] [Sakurai and Hayashi 2015] [Schulze and Meyer 1993] [Schöyer and Korting 1986] [Sebisty 1959] [Seidel 1965] [Setiadi et al 2022] [Shannon 1970] [Sharn 1962] [Shiwa et al 1990] [Shiwa et al 1990] [Shiwa et al 1994] [Shiwa et al 1994] [Shynkarenko and Cunha Martins 2017] [Shynkarenko et al 2024] [Smallwood 1966] [Smallwood 1967] [Smith-Kent et al 1993] [Song et al 2023] [Sparks 1988] [Srivastava and Jayachandran 2022] [Srivastava and Jayachandran 2023] [Srivastava and Thakur 2022] [Srivastava et al 2024] [States 2001] [Stehling 1952] [Stephenson 2018] [Stoker 1964] [Story 2014] [Story 2015] [Strahle and Handley 1978] [Strand et al 1993] [Swoyer et al 2026] [Szatkowski 1985] [Tajima 1965] [Takaki and Kawabata 2022] [Tamang 2025] [Terashima et al 2021] [Thomas and Nandi 1976] [Thomas and Petersen 2022] [Thomas and Petersen 2023] [Tseng and Yang 1994] [Tsien 1952] [Valencia et al 2026] [Villanueva 2016] [Villanueva 2018] [Villar and Rezende 2015] [Waesche and Summerfield 1965] [Wagner and Cleveland 1991] [Wang 1993] [Wang and Feng 1999] [Wang et al 1996] [Wang et al 2016] [Wang et al 2022] [Wang et al 2024] [Wang et al 2025] [Ward 1971] [Ward 1970] [Wardach-Święcicka and Kardaś 2024] [Wei 1987] [Wenzhi et al 2024] [Whitney and Hennessey 1992] [Wong 1968] [Wormhoudt 2003] [Wyld 1947] [Xiao et al 2001] [Xu et al 2019] [Xu et al 2020] [Yoda et al 2015] [Zhang et al 2025] [Zhu et al 2021] [Zinn 1972] [Zinn 1973] [Zolla et al 2026]

Rocket nozzles, plumes and expansion

Rocket nozzles, their flow, expansion and thrust vector control, and exhaust plumes.

206 records. [Ahmed and Gross 2023] [Aikens et al 2015] [Alexandrov 2026] [Altman and Penner 1949] [Application of Double Divergent Annular Rocket Nozzle 2022] [Ashforth-Frost and Jambunathan 1996] [B. et al 2019] [Baetz 1974] [Balwanz 1965] [Bauer 1980] [Bekka et al 2015] [Bennaceur et al 2026] [Bhaskar and Sahu 2021] [Blades et al 2017] [Boraas 1983] [Bowles and Tenney 1981] [Brazzel 1963] [Broadwell 1963] [Brodsky 1970] [Brogan 1984] [Brunner and Buse 1977] [Bryson 1968] [Bundy and Strong 1948] [Burdett 1946] [Butler 1964] [Cabello et al 2025] [Cai 2015] [Cai et al 2019] [Candler 2005] [Chaiaiad and Thongsri 2023] [Chang 1980] [Chaplin 1957] [Chen 2018] [Computational analysis of combustion in recirculating flow for rocket exhausts in supersonic streams 1981] [Conte et al 2019] [Crowe 1967] [Crowe and Willoughby 1966] [Crowe and Willoughby 1967] [Crowe et al 1968] [Crown 1950] [Daily 1989] [Davidian 1987] [Daviller et al 2020] [Demetriades 1977] [Denton et al 2025] [Dillaway 1957] [Ding et al 2019] [Dominguez Calabuig et al 2024] [Dougherty and Liu 1991] [Driggers 1975] [Ebrahimi et al 1998] [Ederouich et al 2021] [Eggers 1961] [Electrodeposition Forms Rocket Nozzle Coating 1961] [Ellison and Ojala 1969] [Erhart 1992] [Ferrero and Pastrone 2019] [Fisher 1978] [Franco-Ferreira 1967] [Franco-Ferreira 1968] [Fredericks and Shorr 1972] [Gale et al 2017] [Gandge and Hampali 2022] [Gates and Cochran 1961] [Ghosh and Gunasekaran 2021] [Glowacki 1971] [Gregg 1988] [Guimond et al 2015] [Gummadidala et al 2025] [Gundersen 2001] [Hadjadj et al 1997] [Hale 1963] [Harikrishnan and Lokavarapu 2021] [Harroun et al 2020] [Hauptman 1965] [He et al 2022] [Hiers and Knapke 2019] [Hoertel 1961] [Hosack and Stromsta 1969] [Huskey 1975] [Ilie and Sullivan 2022] [Isono and Fujikawa 2025] [Janardan and Zinn 1977] [Janardan et al 1974] [Janardan et al 1975] [Jayaprakash et al 2022] [Jenkins 1990] [Jensen and Jones 1981] [Jensen and Wilson 1975] [Jiang et al 2018] [Jones et al 2013] [Jones et al 2014] [Joseph et al 2020] [Kanfoudi and Zgolli 2015] [Kimura et al 2018] [Knickerbocker et al 2026] [Krieger 1951] [Krishna 2020] [Krishnan and Tucker 1992] [Krzycki 1965] [Kumar and Ghosh 2018] [Kumar and Siddapureddy 2025] [Kurita et al 2020] [Langford et al 2007] [Lankford 1987] [Lebedev et al 2000] [Lee 2018] [Lent 1944] [Lepicovsky 1990] [Lewis and Harrison 1961] [Lewis and Williams 1975] [Liao et al 2023] [Liu and Ramamurti 2018] [Maicke 2017] [Manda 1966] [Manski and Hagemann 1994] [Manski and Hagemann 1996] [Matveev et al 2018] [Mehta et al 2017] [Metghalchi 2009] [Micci 1975] [Mikhail 1979] [Miley et al 2020] [Monroe 1945] [Muhammad et al 2024] [Murphy 1999] [Naylor 1951] [Numerical Simulation Study on Flow Field of Aerospike Rocket Engine Nozzle 2025] [Oblanas 1968] [Onodera and Idomura 2018] [Patel et al 2025] [Paxson et al 2022] [Penner 1949] [Perez 1964] [Petrie 1982] [Pietrykowski et al 2020] [Pike 1991] [Placzek et al 1969] [Platov et al 2003] [Pratt 1971] [Price et al 1967] [Ramamurti 2001] [Ramsey et al 2023] [Ranlet 1965] [Rao 1961] [Rastogi and Pandya 1956] [Reddy et al 2023] [Ringuette et al 2001] [Robinson 1978] [Robinson and High 1974] [Rothschild and Martin 1976] [Sampson and Gibson 1982] [Samuelson 1967] [Saokhede et al 2025] [Saxena et al 2023] [Sichel and Yin 1966] [Silnikov and Chernyshov 2017] [Simons 1972] [Smith 1983] [Soni 2026] [Soto and Williams 2024] [Spencer and Beggs 1977] [Spencer et al 1983] [Stephen 1974] [Stephenson 1958] [Stewart et al 2020] [Streiff 1953] [Strome 1969] [Stubbs 1964] [Sullivan 1999] [Takeishi et al 2017] [Tempelman 1972] [Thayer et al 2004] [The Pressure Analyzing of the C-D Rocket Nozzle Considering Isentropic Flow Theory 2023] [Thompson and Epstein 1977] [Thomson 1961] [Tian et al 2026] [Tinney and Valdez 2026] [Varé and Bogey 2022] [Verma 2006] [Victor 1979] [Vijayakumaran and Lemma 2018] [Walker et al 1963] [Wang et al 2022] [Wang et al 2025] [Wang 1995] [Watson 1961] [Watts 2016] [Williams et al 1993] [Wong and Brown 1968] [Wongprapinkul et al 2024] [Woods 1963] [Xie and Du 2024] [Xu and Jangi 2025] [Yagodnikov et al 1995] [Yahiaoui and Olivier 2015] [Yan et al 2017] [Yao et al 2023] [Yin and Li 2015] [Yoshihara 1963] [Yu et al 2019] [Zhang et al 2015] [Zhao et al 2026] [Zheng 2024] [Zhu et al 2025] [Zirkind 1967]

Thermal protection systems and hot structures

Thermal protection systems, tiles, blankets and insulation, and hot structures for reusable and entry vehicles.

211 records. [4680010 Re-radiating heat shield assembly 1989] [Achambath and Schwartzentruber 2018] [Agrawal et al 2010] [Ai et al 2022] [Ajayi et al 2021] [Akamine et al 2026] [Anderson and Kinzel 2023] [Aprovitola et al 2019] [Aronov and Klyagin 2021] [Babashov and Varrik 2020] [Banerjee and Poovathingal 2021] [Bao et al 2019] [Bauer and Kummer 1970] [Bernstein et al 2024] [Blosser 1997] [Bose et al 2016] [Brociek et al 2022] [Brociek et al 2023] [Brociek et al 2023] [Brockmeyer 1993] [Brown 2003] [Brune et al 2016] [Cassell et al 2016] [Castro Júnior and Andrianov 2025] [Chao et al 2024] [Chaturvedi et al 2024] [Chen et al 2024] [Chen et al 2024] [Chen et al 2025] [Chen et al 2025] [Cheng et al 2026] [Chinnaraj et al 2024] [Christiansen and Lear 2015] [Chu et al 2015] [Cinquegrana et al 2017] [Clarke 2008] [Covington and Vojvodich 1971] [Cui et al 2017] [Curtin 2026] [D’Souza et al 2022] [Dang et al 2021] [Peterson and Hagen 1975] [De Prisco et al 2026] [Dec and Mitcheltree 2002] [Duston et al 2004] [Fan 2015] [Feng et al 2024] [Gage et al 2019] [Ghosh et al 2023] [Gong et al 2018] [Grabow et al 1976] [Gramola et al 2022] [Green et al 1984] [Green and Davy 1981] [Gudhenia and Chakrabarty 2025] [Gulli and Maddalena 2015] [Gupta and Ramkumar 2015] [Hao et al 2020] [Hasan et al 2018] [Hassan et al 2024] [Hays et al 2020] [He et al 2025] [Heisler et al 2017] [Henline et al 1996] [Herbell and Eckel 1993] [Hetmaniok et al 2024] [Hiltz et al 1968] [Hopkins and Rutledge 2024] [Hoter et al 2026] [Hou et al 2021] [Hou et al 2025] [Hou et al 2025] [Hovey 1964] [Hovey 1965] [Huang and Dai 2023] [Huang et al 2018] [Hunt 1976] [Hunt et al 1976] [Hussein 2025] [Hwang et al 2016] [Ikenson 2025] [Ivanchenko et al 2021] [Brown 2006] [Ji 2017] [Ji et al 2027] [Jiang et al 2020] [Johnston 1974] [Jumper et al 1993] [Kammer et al 1963] [Khan and Chakraborty 2023] [Kim 2017] [Kim and Choi 2026] [Koch et al 2025] [Kolodziej and Rasky 2002] [Koo 2022] [Korabelnikov and Kuranov 2002] [Kourtides et al 1997] [Krishna and Ricklick 2017] [Kubota and Uchida 1999] [Kumar and Mahulikar 2016] [Kumar and Mahulikar 2016] [Kumar and Mahulikar 2017] [Kundu 2013] [Kurth et al 2015] [La Sorsa et al 2026] [Lakatos 2016] [Lakatos 2019] [Lakatos 2025] [Lakatos et al 2021] [Lane and Kirlin 1978] [Le et al 2023] [Lee 1984] [Lehman and Christensen 1973] [Leiser et al 2002] [Li et al 2021] [Li et al 2026] [Li et al 2026] [Liu et al 2019] [Lu 1996] [Luo and Han 2026] [Luo et al 2026] [Lv et al 2026] [Maiorova et al 2016] [Mathieu et al 1990] [McAfee et al 2025] [McGuire et al 2004] [McGuire 2011] [Medvedev et al 2025] [Mehta et al 2022] [Menees 1983] [Milos and Arnold 2001] [Milos et al 2012] [Morgan and Williams 2025] [Mungiguerra et al 2021] [Myers et al 1999] [Myers et al 2000] [Nabi and Najafi 2024] [Nagabandi et al 2020] [Nakhod 2026] [Nestler 1985] [Nikpourian and Bahramian 2020] [Noel et al 2026] [Ohtake 1998] [Olds and Cowart 2001] [Olds and Izon 2002] [Pallix et al 2000] [Palmer et al 1997] [Panerai and Mansour 2016] [Penide-Fernandez and Sansoz 2019] [Prabhu et al 2012] [Price et al 2025] [Pronina et al 2022] [Prosuntsov et al 2017] [Qu et al 2026] [DiviaHarshaVardini et al 2023] [Raghunandan et al 2021] [Rasky 1995] [Ren et al 2021] [Rezin et al 2001] [Robinson et al 1995] [Rossman and Braun 2016] [Rossman and Braun 2017] [Rufolo et al 2024] [Sanson et al 2017] [Sawant et al 2019] [Schiavazzi and Juliano 2020] [Seif et al 2018] [Sepka and Samareh 2015] [Shao et al 2017] [Shao et al 2026] [Shen and Liu 2020] [Shih et al 1988] [Shilav et al 2021] [Sirmalla et al 2022] [Skolnik and Putnam 2020] [Skolnik and Putnam 2022] [Skolnik and Putnam 2022] [Stewart et al 1985] [Stoll et al 1975] [Structural design aspects of reusable surface insulation thermal protection systems 1972] [Sun et al 2019] [Sun et al 2024] [Tanchuk et al 2001] [Thermal design of composite 1972] [Tianyang 2025] [Tikhy et al 2015] [Tobin and Dec 2015] [Tsukahara et al 2001] [Turner et al 1985] [Vakhitov and Klygach 2016] [Valentine and Gradl 2019] [Violette 2024] [Visnov 1966] [Vozar et al 2015] [Wang et al 2022] [Wang et al 2025] [Williamson et al 2025] [Woollard et al 2016] [Wurster 1981] [Xu et al 2023] [Yan et al 2015] [Yang et al 1990] [Yang et al 2003] [Yang et al 2003] [Yee et al 2023] [Yuan et al 2024] [Yue et al 2025] [Zhang et al 2024] [Zhao et al 2015] [Zhukov 2019] [Zuccarini 2024]

Propellant tanks and cryogenic storage

Propellant tanks, cryogenic storage, pressurisation, sloshing and propellant management.

146 records. [Ambur et al 1996] [Angirasa 2015] [Avila et al 2016] [Bailey et al 1986] [Baillif et al 1995] [Baralle and Fournier 1989] [Benton and Debreceni 2004] [Bershadskyi et al 2022] [Carden et al 1967] [Chandler 1948] [Cheng et al 2025] [Chowdhury et al 2023] [Colquitt 1969] [Colquitt 1968] [COMPARATIVE STUDY OF THE MATHEMATICAL MODEL OF THE PROPELLANT TANK PRESSURIZATION SYSTEM 2024] [Crisan et al 2026] [Dahlene et al 1969] [Debreceni et al 1995] [Debreceni et al 1996] [Debreceni et al 2004] [Der and Stevens 1987] [Ducret et al 1996] [Dudley et al 1992] [Engberg 2005] [Enhanced reliability drain safety valve for LV propellant tank 2021] [Estey et al 1983] [Fairall 1967] [Frank and Drikakis 2017] [Gallo et al 2023] [Ge et al 2022] [Gilliland et al 1966] [Gonçalves et al 2024] [Greenberg 1994] [Greenberg 1994] [Guan et al 2024] [Guan et al 2024] [Gyftos et al 2026] [Heathman et al 1970] [Heilemann et al 2021] [Himeno et al 1999] [Himeno et al 2001] [Hughes 2025] [Hv et al 2017] [Imai and Wada 2025] [Imai et al 2020] [Jan and Aaron 1990] [Jayaseelan et al 2022] [Jha et al 2003] [Johnson et al 2004] [Johnson et al 1998] [Johnson et al 2005] [Ju and Zhang 2025] [Kana and Gormley 1967] [Karahan and Cadirci 2024] [Kartuzova and Kassemi 2019] [Kassemi et al 2018] [Kavalli et al 2026] [Kerebel and Dugat 1986] [Kumazawa et al 2003] [L’Heureux 1987] [Lapilli 2015] [Leakage Detection Experiment of Composite Low-Temperature Tank 2023] [Lee et al 2024] [Li et al 2019] [Liang et al 2022] [Liu et al 2021] [Logan 1985] [Lopez and Rajkumar 2025] [Lu et al 2024] [Macconochie et al 1988] [Macés-Hernández 2026] [Majumdar and Steadman 2001] [Majumdar et al 2016] [Manko et al 2026] [Manokaran et al 2025] [Mazurkivich et al 2005] [Michihara et al 2018] [Mitikov and Shynkarenko 2022] [Moghadasi et al 2018] [Morino et al 2001] [Morita 1964] [Moser and Keith 1992] [Murashko 2026] [Nair et al 2024] [Nandi 2001] [Netter et al 1999] [Nosseir et al 2024] [Olsson et al 2024] [Ashwath 2023] [Park et al 2023] [Pasley 1972] [Pasley 1972] [Pazhani et al 2024] [Pei and Rothhaar 2015] [Pharokhipanah and Bouckenooghe 2024] [Pietrzyk et al 1993] [Price et al 1992] [Sundharesan and Jv 2024] [Rankin et al 1969] [Reske and Brodnick 2024] [Rhee et al 2025] [Robertson and turnbow 1966] [Robinson 1994] [Rollins et al 1983] [Rollins et al 1984] [Rollins et al 1986] [Rollins et al 1988] [S. Prasanraj 2019] [Saha et al 2025] [Sakai et al 2025] [Sakowski et al 2019] [Sato et al 2020] [Schmidt 1991] [Scholz et al 1992] [Sidoruk et al 2020] [Skleznev 2023] [Smeltzer and Bowman 2002] [Solomon and Tamiru 2026] [Spier et al 1966] [Sreeyesunath and Sugathan 1994] [Streetman and Graves 1963] [Structural arrangement trade study 1995] [Structural Arrangement Trade Study 1995] [Su 2017] [The Flight of Rocket No. 4: 600 Mile An Hour Speed Attained By Multi-Nozzle Tandem Tank Rocket 1934] [Torre 1986] [Torre et al 1986] [Trushlyakov and Urbansky 2023] [Trushlyakov et al 2024] [Tzoumakis et al 2024] [Utsumi 1997] [Vamsi et al 2019] [Wang et al 2016] [Wei et al 2025] [Werlink and Pena 2015] [Woodsum and Rowland 1968] [Yang et al 2023] [Yang et al 2025] [Ye et al 2025] [Yoon 2025] [Yoon et al 2024] [Zhao et al 2021] [Zhao et al 2025] [Ziglar 2025] [Ziglar and Elsperman 2026] [Zimmerman et al 2015]

Composite structures and flight vehicle materials

Composite and metallic structures and the materials of flight vehicles, their loads, fatigue and aeroelasticity.

186 records. [Akimov 2026] [Aksoy et al 2019] [Alexander et al 1996] [Allen et al 1983] [Allen et al 1984] [Ambrus and Herman 1988] [American Institute of Aeronautics and Astronautics 1993] [Anooj et al 2023] [Askins et al 2008] [Bai et al 2017] [Balageas 2002] [Bendix Field Engineering Corp Columbia Md 1974] [Bennaceur and Xu 2019] [Brich et al 2025] [Briskman 2000] [Burkhard 1973] [Burrows and Allaire 2019] [Case and Reifsnider 2003] [Cenko and Madson 1993] [Chaloff et al 1974] [Chilles et al 2015] [Clausing 1969] [Clinton et al 1999] [Cohn et al 1963] [Corvi 1990] [Cox et al 2022] [Dai et al 2025] [Dash et al 2025] [De Leon et al 2022] [De Luca et al 2026] [Demirel and Demirci 2026] [Diodati et al 2023] [Dion 1992] [Dotson and Tiwari 1996] [Dziopa and Koruba 2015] [Fischer et al 2015] [Flanigan 1989] [Gade and Inman 1998] [Ganilova et al 2022] [Gourab et al 2021] [Goyal et al 2021] [Goyal et al 2026] [Guo et al 2019] [Gupta and Mishra 2024] [Guratzsch and Mahadevan 2004] [Hadjria and D’Almeida 2019] [Hafizuddin Baderillah and Fadhli Zulkafli 2025] [Hartung 1963] [Holladay et al 2019] [Honchar 2026] [Howard and Hansen 2006] [Howdyshell et al 1998] [Huangpeng et al 2021] [Hwang 1963] [Hwang et al 1979] [Hwang et al 2025] [Inada 2004] [Ireman et al 1994] [Ivanco et al 2020] [Ivanco et al 2021] [Ivanco et al 2024] [Jadhav and Sridharan 2001] [Jaiswal et al 2024] [Janney and Rogers 1986] [Jayanthi and Jain 2019] [Joint DoD/NASA Advanced Launch 1990] [Jones 1976] [Kashefinishaburi and Hoa 2022] [Kayran 2004] [Kayran 2004] [Kemp et al 1972] [Khamlak 2026] [Khan and Chakraborty 2021] [Kieffer 2006] [Kim et al 2013] [Kim et al 2026] [Kirikera et al 2003] [Koley et al 2026] [Koliada 2026] [Krishna 2022] [Krishna et al 2019] [Kumar 2001] [Kumar 2002] [Kumari and Kumar 2022] [Kunal and Chakraborty 2026] [Lemke et al 2008] [Liu et al 2016] [Loesch and Pawlowski 1973] [Lu et al 2025] [Lutz et al 2022] [Ma et al 2024] [Mahdi et al 2024] [Manwatkar et al 2016] [Manwatkar et al 2016] [Mayank et al 2022] [McGehee et al 1978] [Mehta 2016] [Mehta 2022] [Miller and Breslau 1956] [Muin and Miah 2025] [Murugesan et al 2018] [Naval Air Systems Command Patuxent River Md 1999] [Naval Air Systems Command Patuxent River Md 2000] [Nettles and Ratcliffe 2006] [Noll and Huttsell 1978] [Norton 1990] [Oliver et al 2004] [Orsatelli et al 2023] [Osama et al 2025] [Osuna and Adibi 2024] [Paek and Lee 1996] [Paulini 2019] [Pavanasam et al 2024] [Pawar et al 2026] [Phelan and Niemann 1998] [Piatak and Sekula 2019] [Piatak et al 2019] [Podliesnyi 2026] [Poursartip et al 2024] [Primer on composite materials: Analysis 1985] [Proroka and Lypovskyi 2019] [Puertolas and Perraud 2019] [Pulford and Lake 2023] [Purushotham and Yathin 2018] [Rafla 2019] [Rainey 1964] [Raouf and Pourtakdoust 2017] [Ratnayake et al 2020] [Richards et al 2013] [Riley and McNamara 2016] [Riley and McNamara 2017] [Rochefort and Yorra 1976] [Roma Rubi et al 2025] [Schpey 1980] [Shimizu et al 2024] [Silva Guimaraes and d’Andrade Souto 2021] [Sioutis and Tserpes 2023] [Skelly 1989] [Sleight et al 2019] [Song et al 2021] [Srinivasan et al 2023] [Srivastava and Jain 2023] [Stamatelos and Labeas 2025] [Strganac 2007] [Stuber et al 2012] [Tamma and Yurko 1988] [Tang and Dowell 1998] [Tanner 1997] [Tao et al 2023] [Tate 1969] [Tekin and Kapan 2016] [Thedy and Liao 2023] [Theoretical Analysis on Large-Stroke Dry Friction Vibration and Shock Isolation Composite Structure for Satellite Launch Environment 2026] [Toda et al 2000] [Torres et al 2019] [Triplett 1972] [Tuma et al 2008] [Turner 1982] [Vagins 1972] [Vargas Venegas and Huang 2022] [Vargas Venegas and Huang 2023] [Vaughn 1999] [Veyret et al 1993] [Wang 2025] [Wang et al 2021] [Weitz et al 2025] [Wells 1999] [White et al 2005] [Whitman 1962] [Wignall and Houlden 2020] [Wild et al 2021] [Wire mesh-plastic composite material for heat exchangers 1981] [Wood 1991] [Wrenn et al 2001] [Xie et al 2025] [Xing et al 2024] [Yadav et al 2020] [Yang et al 2015] [Yu et al 2025] [Yue et al 2018] [Zaitsev et al 2020] [Zeiler et al 1999] [Zhang et al 2024] [Zhao and Bao 2023] [Zheng et al 2026] [Ziglar 2026]

Aerodynamics, aerothermodynamics and hypersonic flow

Aerodynamics and aerothermodynamics of launch and entry vehicles, hypersonic flow, boundary-layer transition and aerodynamic heating.

256 records. [A Supersonic/Hypersonic Aerodynamic Investigation 1966] [Aero-heating prediction model for hypersonic vehicles 2025] [André et al 2015] [Aogaki et al 2017] [Arabshahi 2021] [Areias et al 2023] [Atay et al 2026] [Balakumar and Chou 2016] [Balakumar and Chou 2018] [Beck et al 2019] [Bender et al 1992] [Blanco 2024] [Brice et al 1966] [Buzuluk et al 2020] [Byczkowski and Rao 2023] [Candler 2015] [Chan et al 2016] [Chavez and Schmidt 1994] [Chen 2020] [Chen and Gibbons 2022] [Chen and He 2025] [Chen et al 2022] [Chen et al 2022] [Chen et al 2023] [Chen et al 2023] [Chen et al 2025] [Chen et al 2026] [Cheng et al 2023] [Ching et al 2017] [Ching et al 2024] [Cooper and Martin 2023] [Corke and Bowersox 2018] [Danehy et al 2019] [Dias et al 2026] [Ding and Ziviani 2026] [Direct numerical simulations of hypersonic boundary layer transition over a hypersonic transition research vehicle model lifting body at different angles of attack 2023] [Dong and Li 2021] [Donohue and Fletcher 1996] [Dreus et al 2021] [Duan et al 2026] [Duan et al 2026] [Dwivedi and Sidharth 2026] [Edquist 2006] [Effect of Ground Proximity on Aerodynamic Forces and Moments of Reusable Launch Vehicle at Subsonic Speed 2016] [Effects of mass transfer on hypersonic turbulent boundary layer properties 1972] [Erickson 2020] [Esposito and Lappa 2026] [Favaregh et al 2016] [Fidkowski 2022] [Fievet et al 2020] [Fine 1979] [French et al 2021] [Fu et al 2021] [Fujio and Taguchi 2026] [Gai and Cao 2025] [Gajoni et al 2026] [Garbeff et al 2017] [Gee et al 2025] [Gnoffo and Inger 1999] [Gokcen 2018] [Gokcen and Skokova 2017] [Gros 1963] [Grossir et al 2015] [Gui et al 2023] [Guo et al 2024] [Hader and Fasel 2021] [Hader and Fasel 2024] [Hader et al 2020] [Hahne 1997] [Han and Cao 2019] [He et al 2026] [Heaney et al 2021] [Hill and Borg 2024] [Holifield and Tufts 2024] [Hollis 2024] [Hoskin et al 2024] [Hu et al 2015] [Huynh and Kriz 2009] [Ifergan et al 2021] [Inatomi et al 2019] [Iqbal and Akbar 2026] [Ishimoto 1995] [Jaffrezic et al 2015] [Jameson et al 2024] [Jeong and Jo 2026] [Jeong et al 2026] [Ji et al 2025] [Jia et al 2020] [Jiang et al 2016] [Jiang et al 2017] [Jo 2026] [Johnston et al 2026] [Joseph et al 2026] [Kelly and Cruz 2009] [Kiehn 2020] [Kikuchi et al 2016] [Kim and Lee 2025] [Kim et al 2025] [Kim et al 2026] [Kim et al 2026] [Klaproth and Hornung 2022] [Koike and Babinsky 2019] [Kumar et al 2023] [Lawrence and Mills 2002] [Lee and Chen 2018] [Lei et al 2017] [Li and Zhang 2021] [Li et al 2019] [Li et al 2020] [Li et al 2022] [Li et al 2025] [Li et al 2025] [Li et al 2026] [Lin and Miller 2025] [Lindsay and Fikes 1976] [Liu et al 2021] [Liu et al 2023] [Liu et al 2025] [Liu et al 2025] [Liu et al 2025] [Lüdeke et al 2015] [Makhnun et al 2024] [Marineau 2016] [Mathavaraj and Padhi 2020] [Matsunaga et al 2017] [Matsuyama 2024] [Mazzone et al 2024] [Meersman et al 2022] [Mehta 2015] [Mehta 2021] [Melander and Candler 2024] [Menon et al 2025] [Miró Miró and Pinna 2018] [Miró Miró and Pinna 2020] [Murray and Lewis 1978] [Narayanan et al 2026] [Nguyen et al 2023] [Niu and Su 2023] [Olejnik et al 2022] [Ort and Dosch 2019] [Oyama et al 2021] [Ozawa and Bruce 2025] [Palmer et al 2015] [Paredes et al 2018] [Paredes et al 2019] [Paredes et al 2021] [Parent and Hanquist 2021] [Patrick 2019] [Paxton et al 2020] [Pei et al 2025] [Peng and Wang 2026] [Peng et al 2018] [Perry 2024] [Poggie 2015] [Pollock et al 2023] [Prabhu 2012] [Pu and Jiang 2019] [Qi et al 2021] [Qiu et al 2024] [Quan et al 2026] [R. C. Mehta 2023] [Raghunathan et al 2026] [Rana and Chudoba 2016] [Ransom and Srinivasan 2024] [Rao and Chimata 2024] [Rat et al 2015] [Reusable Reentry Satellite RRS 1990] [Rich et al 2001] [Roschke 1955] [Roussos et al 2025] [Ryu et al 2024] [Sakamoto et al 2023] [Santos et al 2020] [Santos et al 2021] [Schrage 2025] [Sekula et al 2015] [Selvakumar and Palanisamy 2020] [Selvam and George 2026] [Sha et al 2026] [Shimmy 2026] [Shrestha and Candler 2018] [Shrestha et al 2017] [Shukla 2025] [Sidharth and Dwivedi 2026] [Signorelli et al 2024] [Singh et al 2024] [Sippel et al 2017] [Smith 2021] [Spanelis and Walker 2022] [Striz and Jang 1987] [Su and Liu 2025] [Su et al 2025] [Sudarshan et al 2021] [Sun et al 2018] [Sun et al 2020] [Swanson and Daniel 2016] [Takahashi et al 2018] [Tao and Sun 2019] [Tauber et al 1999] [Tewell 1984] [Tian et al 2025] [Türkoğlu et al 2026] [Ullah et al 2024] [Unnikrishnan and Gaitonde 2018] [Uzun et al 2019] [Vargas Venegas and Huang 2021] [Vo et al 1993] [Vohra et al 2026] [Vu and Candler 2026] [Walker et al 1993] [Wan et al 2025] [Wang and Josyula 2016] [Wang et al 2016] [Wang et al 2016] [Wang et al 2024] [Wang et al 2024] [Wang et al 2025] [Wang et al 2026] [Welker and Maynes 2026] [Wilcox et al 2016] [Winski et al 2019] [Wolverton 2018] [Wu and Yu 2018] [Wu et al 2026] [Xinguo et al 2024] [Xu and Wang 2023] [Xu et al 2022] [Xu et al 2026] [Yakubayev et al 2026] [Yamin and Hadi 2026] [Yan et al 2019] [Yang et al 2022] [Yang et al 2025] [Yang et al 2026] [Yang et al 2026] [Ye et al 2017] [Yin et al 2023] [Yu and Yuan 2016] [Yu et al 2025] [Zeng et al 2026] [Zhang and Li 2019] [Zhang et al 2023] [Zhang et al 2026] [Zhang et al 2026] [Zhao et al 2019] [Zheng et al 2025] [Zhou et al 2015] [Zhou et al 2016] [Zhou et al 2018] [Zhou et al 2023] [Zhu 2022] [Zhu et al 2020] [Ziegler 1963] [Zou et al 2015] [Zugaj 2017] [Zuppardi and Esposito 2016]

Automatic and autonomous landing

Automatic and autonomous landing of aircraft, unmanned aircraft, reusable rocket stages and planetary landers, and the approach and touchdown problem they share.

Unmanned aircraft and rocket stages now carry the subject. Of the 323 records, 72 name an unmanned aircraft, a drone or a rotorcraft, 65 name a rocket, a launch vehicle, a reusable vehicle or a stage, and 130 date from 2001 or earlier.

323 records. [180 Fault Tolerant navigation system for aircraft landing 1994] [Ahmed 2021] [Ahmed 2023] [Ahmed and Wyatt 2024] [Akash and Anbarasu 2025] [Al-Bakri et al 2020] [Alijani and Osman 2020] [Analysis of Quasi-three-dimensional Landing Dynamics and Attenuation Performance under Extreme Conditions for Launch Vehicle 2021] [Anderson and Schmidt 1987] [Aoki and Ishigami 2022] [Approach to solving the problem of landing an unmanned aerial vehicle on a moving landing platform 2025] [Automatic Landing 1964] [Automatic Landing 1969] [Ayyasamy et al 2023] [Baca et al 2017] [Balanis and Cheng 1975] [Banerjee et al 2016] [Bhargavapuri et al 2019] [Bicer et al 2019] [Bischoff et al 1974] [Boriotti and Maali 1993] [Borowczyk et al 2017] [Botelho et al 2022] [Broglio 1961] [Brown 1996] [Bryson et al 1970] [Bu et al 2016] [Burrous et al 1974] [Burton 1981] [Carson et al 2015] [Chamitoff 1994] [Chen et al 2025] [Chen et al 2026] [Chessman 2022] [Chester 1995] [Childers et al 2001] [Chitrakaran et al 2005] [Chowdhury et al 2026] [Cockburn 1965] [Colwell 1966] [Cook 1985] [Costache and Stoica 2026] [Crassidis and Mook 1991] [Crassidis et al 1993] [D’Souza and D’Souza 1997] [Danjun et al 2015] [Davies 1938] [Davison and Schroeder 1994] [de Lafontaine 1992] [De Oliveira and Lavagna 2024] [Development of algorithmic support for detecting an aircraft carrier using machine vision technology for automatic landing of UAV 2022] [Development of visual landing aids for jet aircraft: 1960] [Digges 1971] [Doehler and Korn 2004] [Doherr et al 1997] [Dong et al 2023] [Doniger 1967] [Dougherty and Lee 2016] [Douglas Aircraft Co Long Beach Ca 1963] [Epp et al 2015] [Evaluation of the navigation performance of shipboard-VTOL-landing guidance systems 1979] [Fazeli and Narayan 2017] [Federici et al 2026] [Fenwick 1966] [Fenwick 1967] [Ferguson and Radke 1993] [Fischer 1981] [Flying Controls and Automatic Landing 1963] [Fortenbaugh 1972] [Foster 1972] [Franklin 1995] [Fujimori et al 2000] [Gai and Curry 1977] [Garcia-Pardo et al 2001] [Garcia-Pardo et al 2002] [Gardinier and Taylor 1999] [Gautam et al 2017] [Guadagnini et al 2023] [Guo et al 2022] [Guo et al 2025] [Günsel et al 2025] [Hameed and Bindu 2019] [Hara et al 2024] [Harris 1961] [Hayashi et al 2025] [He et al 2019] [Helliwell 1952] [Hendrick and Horn 2024] [Hess and Judd 1976] [Horn et al 2014] [Horn et al 2015] [Hornbuckle 2015] [Hsu et al 2022] [Hu et al 2022] [Huan et al 2015] [Huang and Zhang 2026] [Huang et al 2018] [Huang et al 2020] [Huang et al 2020] [Igreja and Lemos 2022] [Ilango and Ramanathan 2020] [Jin et al 2016] [Jung et al 2015] [Jung et al 2025] [Jung et al 2025] [Senthil Kumar and Shanmugam 2023] [Kaneko and Yamato 2025] [Ke and Feng 2015] [Kerr et al 1995] [Kidwell 1963] [Kim et al 2017] [Kim et al 2023] [Kluever 2004] [Kluever and Neal 2015] [Klumpp 1966] [Knopp et al 1992] [Kock et al 1972] [Koester and Vaillancourt 1992] [Koryanov 2021] [Krishnan and Sajikumar 2023] [Kubota et al 2003] [Kuhn 1979] [Kulumani and Lee 2022] [Kumar and Padhi 2024] [Kumar and Padhi 2024] [Lambregts 1982] [Landy and Kim 1984] [Lawrence et al 2001] [Lee and Chiou 1994] [Lee and Mesbahi 2017] [Lee and Park 2025] [Lee et al 1973] [Lee et al 1998] [Lee et al 2025] [Leeman et al 2022] [Lehman 1964] [Lei et al 2022] [Li and Hu 2018] [Li et al 2024] [Li et al 2025] [Li et al 2025] [Li et al 2026] [Li et al 2026] [Lighthill 1963] [Lin et al 2026] [Ling 1970] [Littell 2019] [Liu and Zhang 2022] [Liu et al 2017] [Liu et al 2023] [Liu et al 2024] [Lowrance and Smith 1996] [Lunghi et al 2015] [Lunghi et al 2022] [Lungu and Lungu 2018] [Lykken and Shah 1971] [Lykken and Shah 1972] [Ma and Zhao 2019] [Ma et al 2019] [Ma et al 2025] [Maass et al 2020] [Maces-Hernandez et al 2017] [Mackay et al 2016] [MACKlNNON and Madden 1972] [Maiuzzo 1970] [Mann 1987] [Martin et al 1995] [McDonald 1980] [McGee 1977] [McGee et al 1981] [McGee et al 1984] [Miele et al 1989] [Miso et al 1999] [Missile guidance to landing sites based on image correlation 2022] [Miyazawa et al 1993] [Miyazawa et al 1999] [Mobile Autonomous Recovery Landing Principle and Control Method for Unmanned Aerial Vehicle 2024] [Modali et al 2020] [Mohan et al 2025] [Moore et al 1979] [Mu et al 2025] [Mukhopadhyay 1969] [Muskardin et al 2016] [Nagarjuna and Suresh 2015] [Negre 1975] [Negre 1977] [Nho and Agarwal 1998] [Ni et al 2023] [Nugroho et al 2024] [Numerical Optimization on Approach and Landing for Reusable Launch Vehicle 2016] [Oakes 2021] [Ohara et al 2001] [Papadopoulos 1998] [Parker and Templeman 1967] [Parkinson and Fitzgibbon 1989] [Parks and Tubb 1970] [Patrick 1972] [Perez and Benner 1973] [Persson and Wahlberg 2019] [Pessanha Santos et al 2023] [Phillips et al 1983] [Pierson 1985] [Pogust and Taylor 1972] [Poritzky 1970] [Poritzky 1971] [Poulose 1992] [Pozzi and Mugnuolo 1998] [Pulk and Stolarik 1977] [Qu et al 2016] [Qu et al 2018] [Raei et al 2022] [Rankin 1994] [Recker et al 2018] [Reitan and Saib 1976] [Reusable Launch Vehicle Landing 2026] [Riley et al 1994] [Rimer and Sperling 1965] [Rimer and Sperling 1966] [Robaglia et al 2018] [Rohan et al 2023] [Roy and Davison 1986] [S. Hameed and G. R 2021] [Sachan and Padhi 2016] [Sagliano et al 2021] [Sagliano et al 2024] [Sagliano et al 2025] [Salt 1995] [Sanchez et al 2018] [Sanuki 1965] [Sarrafian 1986] [Schmidt 1985] [Schmitt and Burchett 2004] [Schoenman and Doniger 1965] [Shayler 1961] [Shen et al 2020] [Shivam et al 2023] [Silva et al 2017] [Simplício et al 2019] [Smith and Meyer 1981] [Smith et al 1972] [Smith et al 1973] [Sotirakos and Prazenica 2025] [Steinberg 1992] [Strozecki and Mammar 2021] [Su and Wang 2015] [Su et al 2022] [Sullings and Waller 1967] [Suresh and Ratnoo 2019] [Tanaka and Matsumoto 2019] [Tariq et al 2026] [Templeman and Parker 1968] [The algorithm of the color signal recognition at landing an unmanned aerial vehicle on an aircraft carrier in autonomous mode 2020] [Thies 2022] [Thompson 1965] [Tiana and Pond 1997] [Trajectory Shaping Guidance for Vertical Landing of Launch Vehicle Stage 2025] [Tripathi and Padhi 2016] [Tripathi and Patel 2019] [Tripathi et al 2025] [Tsitses et al 2024] [Tsoukalas et al 2026] [Tsuyuki et al 2005] [UAV control with active disturbance suppression for the safety landing on an aircraft carrier 2023] [van Slagmaat 1992] [Velasco et al 2017] [Volkov et al 2022] [Vredevoogd and Thompson 2021] [Wagdi 1984] [Walker 1960] [Walker 1961] [Wang and Carl 1999] [Wang and Song 2018] [Wang and Song 2019] [Wang et al 2015] [Wang et al 2020] [Wang et al 2020] [Wang et al 2022] [Wang et al 2022] [Wang et al 2022] [Wang et al 2023] [Wang et al 2026] [Wasserman and Mitchell 1973] [Watson et al 2020] [Webber and Page 1963] [Wei and Shao 2021] [Wei et al 2024] [Weichelt et al 1986] [Elke et al] [Williamson Jr. 1963] [Wilz and Johnson 1975] [Woestemeyer 1964] [Wong et al 2002] [Wu et al 2018] [Wu et al 2018] [Wu et al 2024] [Wygle 1965] [Wynn and McLain 2019] [Xiangyu et al 2004] [Xiao 2026] [Xu and Lan 2018] [Xu et al 2017] [Xu et al 2018] [Xu et al 2025] [Yan et al 2023] [Yanagihara et al 1999] [Yang 2025] [Yao and Xin 2023] [Yelin Zhang et al 2016] [Yue et al 2019] [Yue et al 2022] [Yue et al 2022] [Zeh et al 1989] [Zhang et al 2017] [Zhang et al 2017] [Zhang et al 2019] [Zhang et al 2021] [Zhang et al 2025] [Zhang et al 2025] [Zhao et al 2020] [Zhou et al 2024] [Zhou et al 2026] [Zhu et al 2026] [Çelik and Demirezen 2024]

Guidance, control, avionics and trajectories

Guidance, navigation and control, avionics, flight software and trajectory design and optimisation for launch, entry and unmanned vehicles.

444 records. [Aamer et al 2023] [Abbas et al 2023] [Abdi-Moradi 1988] [Abdo et al 2021] [Abdullah 2025] [Adaptive Fault Tolerant Servo Scheme For Launch Vehicle Control Actuation System 2025] [Adimurthy 1987] [Agarwal and Gupta 2004] [Akiyama et al 2024] [Aktas et al 2016] [Alexander 1978] [Algorithm for evaluation the navigation complex of a carrier-based aircraft 2020] [Alizo Ewald et al 2026] [Allen 2005] [An et al 2020] [Ancel et al 2019] [Andrews 2000] [Ansari and Bajodah 2015] [Ansari and Bajodah 2016] [Ansari and Bajodah 2016] [Army Aviation School Fort Rucker Al 1961] [Asamura et al 2024] [Ashraf et al 2022] [Attia et al 2025] [Autonomous flight control of drone equipped with microcomputer for flight control and GPS 2018] [Autonomous Flight Safety System 2008] [Averyanov et al 2021] [Bail 1968] [Bakirci 2023] [Balesdent et al 2022] [Batory et al 1995] [Bauer 1996] [Beaudoin et al 2018] [Beaudoin et al 2018] [Best et al 1988] [Bi et al 2020] [Bielaszka 2026] [Boersma et al 1970] [Boglis and Stoica 2019] [Bolton 2016] [Boskovic et al 2017] [Boydston et al 2015] [Brehm and Goettge 1995] [Briese et al 2018] [Briese et al 2020] [Brodecki and Subbarao 2015] [Bull and Martel 2000] [Bull and Lanzi 2007] [Burchett 2003] [Burkhard et al 1974] [Cai et al 2024] [Calamoneri et al 2024] [Calhoun 2000] [Canepa et al 2022] [Carter et al 1993] [Castaldi et al 2023] [Cato 1964] [Cato 1965] [Chen et al 2021] [Chen Liu et al 2016] [Cheng et al 2021] [Childers and Condon 2004] [Chin et al 2016] [Cho et al 2021] [Cho et al 2021] [Choi and Li 2026] [Civek and Özgören 2017] [Cole et al 2007] [Corban et al 2004] [Cotton 1974] [Cowling 2011] [Craig and Russell 1978] [Crawford and Wallace 1998] [Cronin 2013] [Crook and Meyer 1981] [Cruz et al 2022] [Culp and Bickley 1993] [Czuchry et al 1979] [Czuchry et al 1979] [D’Andrea 2008] [Dai et al 2017] [Dana-Bashian et al 2001] [Davis 1988] [Dees et al 2015] [Deets et al 1988] [Demidovich 2017] [Denton et al 2022] [Design and Optimization of Mechatronic Integrated Control System 2023] [Design of an autonomous flight control system for imitation falcon flapping-wing aircraft 2022] [Determination of External Power Factors Acting on an Unmanned Aerial Vehicle in Critical Flight Modes 2019] [Dhief et al 2025] [Diamant et al 1979] [Dinelli et al 2019] [Dire et al 1986] [Drozd 2026] [Du et al 2019] [Duan and Luo 2016] [Edwards 2019] [Elliott et al 2025] [Emma and Pernicka 2003] [Estimating trajectory correction requirements for the Outer Planets Grand Tour missions 1972] [ETE Model and High Precision Positioning for Autonomous Flight in 5G 2022] [Ferrell et al 2004] [Fielding and Vaziry-Z 1995] [Filippoli 2026] [Fisher et al 2002] [Fu et al 2019] [Fu et al 2021] [Fuchs 1980] [Gadhvi and Shankar 2023] [Gainer 1963] [Gamble and Jenkins 2001] [Garg et al 2022] [Gates and Shipp 1978] [Gebman 1989] [General Electric Co Schenectady Ny 1952] [Gente et al 2024] [Ghori et al 2022] [Ghosh and Chattopadhyay 2015] [Gourab et al 2021] [Gourab et al 2023] [Gourab et al 2023] [Green et al 1993] [Grigoriev and Proskuryakov 2024] [Guiliano 1999] [Guo et al 2017] [Guo et al 2025] [Hajiyev and Cilden Guler 2023] [Hale 2018] [Han et al 2019] [Hanc et al 2022] [Hanlon 2016] [Hanson et al 2015] [Hao and Zhang 2021] [Hao et al 2017] [Harris and Howell 1988] [Hart 1956] [Hasani et al 2017] [Haswell and Murray 2025] [Havey et al 1998] [Hayre et al 1992] [He and Wu 2022] [Heatwole and Lanzi 2010] [Rediess 1976] [Hiroi et al 2020] [Hitt and Brim 1977] [Holibaugh 1992] [Hu et al 2022] [Huang 2016] [Huang 2026] [Huang et al 2024] [Hussein and de Weck 2025] [Hwang et al 2016] [Ossai 2020] [Simplified Vehicle Operations Pathway 2024] [Ishkov et al 2019] [Jakeman 2024] [Jang et al 2010] [Jang et al 2014] [Jarvis 1974] [Ji et al 2016] [Jia et al 2025] [Jiang and Tan 2023] [Jianguo et al 2016] [Jo and Ahn 2020] [Johnson and Schrage 2004] [Johnson et al 2011] [Jones 2001] [Jones et al 2001] [Joshi et al 2023] [Ju et al 2022] [Junaid R and Beebi M 2015] [Jutty K et al 2000] [Kabashkin and Filippov 2020] [Karali et al 2024] [Karas 1990] [Keaton 1986] [Keaton 1987] [Keith and Rothschild 1999] [Khamvilai et al 2022] [Kim 2016] [Kim and Lim 2020] [Kim et al 2022] [Kinsey et al 1987] [Klion 1977] [Kluever 2022] [Knox-Seith 1963] [Kose et al 2023] [Kotikalpudi et al 2020] [Kovalenko 2021] [Krause et al 2024] [Krishnan et al 2023] [Krivenko 2026] [Kumar 2024] [Kumar et al 2024] [Kumar et al 2025] [Kumar V V and Beebi M 2015] [Kumari et al 2023] [Kurz 1963] [Lala and Adams 1987] [Langston 1967] [Launch vehicle booster avionics 2000] [Laurence et al 2015] [Lee 2026] [Lee et al 1993] [Lee et al 2020] [Lee et al 2024] [Lee et al 2025] [Lewis 2016] [Li and Ru 2019] [Li et al 2017] [Li et al 2020] [Liu et al 2017] [Liu et al 2025] [Liubimov 2025] [Llinas and Bowman 2001] [Logan et al 2015] [Lombaerts et al 2020] [Lu 1997] [Lu et al 2016] [Lu et al 2022] [Lu 1999] [Lugo et al 2019] [Lungu et al 2018] [Luton 1963] [Lytovchenko 2026] [Ma and Li 2020] [Ma et al 2018] [Ma et al 2023] [Ma et al 2024] [Martin 1963] [Martin 2007] [Marzioli and Frezza 2021] [Mascareñas et al 2019] [Mase et al 2000] [Masjukov and Konovalov 2022] [Mathematical modeling for flocking flight of autonomous multi-UAV system, including environmental factors 2020] [Mathur and Avižienis 1970] [Mayorga-Macías et al 2020] [McCormick and Compton 1986] [McKinney 1986] [McLaughlin and Perhinschi 2020] [Melliar-Smith and Schwartz 1981] [Melliar-Smith and Schwartz 1982] [Mendez 1975] [Menon and Lehman 1986] [Strickland and Palumbo 1988] [Migneault 1980] [Millar and Smrcek 2001] [Miotto and LePome 2003] [Miquel Parra et al 2024] [Mittal 2025] [Mo et al 2024] [Modular avionics systems architecture (MASA) - Seeds of destruction or seeds of progress? 1988] [Mohan and Kishore 2021] [Mooij 2020] [Moon et al 2015] [Moore 1969] [Morando et al 2024] [Morgan 1970] [Morgan and Barton 2022] [Muda et al 2023] [Mukundan et al 2022] [Muthukumar et al 2020] [Myung 2022] [Nagarajan and Karthikeyan 2017] [Naigle 2025] [Nair et al 2016] [Naji and Stoica 2023] [National Research Council Washington Dc 2001] [Naval Air Systems Command Arlington Va 1993] [Nedresky 1996] [Ness et al 1983] [Nguyen et al 2021] [Nikolaou et al 2026] [Novack et al 2018] [Oh and Han 2021] [Oka et al 2025] [Orsagh et al 2005] [Ostroff and Wood 1977] [Venkataramana et al 2023] [Panda et al 2015] [Panda et al 2016] [Panda et al 2017] [Papakonstantinou et al 2022] [Park et al 2023] [Pasciuti et al 2025] [Patapoff 1961] [Paterson 1991] [Patterson and Arena 2015] [Pei et al 2017] [Peng et al 2025] [Perhinschi 1999] [Perhinschi and Perhinschi 1997] [Phạm Đức et al 2026] [Prediction of errors of an autonomous inertial navigation system 2025] [Priyadarshini et al 2023] [Provost et al 2017] [Pullen 1973] [Qi et al 2015] [Qiao 2024] [Qu et al 2023] [Radhakrishnan et al 2023] [Radhakrishnan et al 2024] [Rahnamai et al 2018] [Rajendran and Smith 2018] [Ramírez Navidad et al 2024] [Rauf Guliyev 2025] [Redondo Gutierrez et al 2022] [Reed 1977] [Kulikova N.V. CHulin N.A. 2023] [Regulator with reference model for u nmanned aircraft control when boarding on unmanned vehicle 2022] [Resemini and Souza Costa 2018] [Rice and McCorkle 1979] [Rice et al 2022] [Rico and Turkoglu 2016] [Risko 1999] [Robust Optimal Trajectory Design of a Launch Vehicle Using Particle Swarm Optimization 2022] [Robust Super-Twisting Sliding-Mode Controller for Launch Vehicle 2025] [Rogers et al 2017] [Rosenfeld and Davis 1986] [Ryan and Cummings 2015] [Ryan and Granger 2023] [Saju et al 2025] [Sabán et al 2024] [Sahani et al 2017] [Salahudden 2025] [Salehi et al 1995] [Satterthwaite 1994] [Savuran and Karakaya 2015] [Schierman et al 2001] [Schierman et al 2001] [Schlatt 2004] [Schoettle and Hillesheimer 1991] [Schultz and Grefenstette 1992] [Scott 2003] [Seltzer 1970] [Seltzer 1981] [Settanni et al 2015] [Shan et al 2023] [Shen et al 2019] [Shepperd and Staugler 1999] [Shi et al 2024] [Shishkin and Khachumov 2025] [Shivers 2010] [Shtessel et al 2000] [Shukla and Woolsey 2018] [Simms et al 2014] [Simpson 2010] [Simpson 2005] [Simpson et al 2005] [Sinha and Kumar 2024] [Sobel and Joshi 2002] [Sobocinski 1981] [Song and Choi 2018] [Sorensen 1962] [Sorgenfrei et al 2017] [Sruthi S et al 2015] [Stolarik 2007] [Su and Liu 2025] [Su et al 2021] [Sun and van Kampen 2020] [Sun et al 2026] [Surender et al 2021] [Surkova A.D. and Neusypin K.А. 2026] [Szabolcsi 2018] [Taghizadeh et al 2022] [Tai and Jang 2017] [Taranto and Abdulrahim 2023] [Tatsuya et al 2018] [Tauke-Pedretti 2016] [Teofilatto and De Pasquale 1998] [Thuillier et al 2024] [Tian et al 2015] [Tomczyk 2003] [Tong and Fen 2016] [Tony and Arun Kishore 2015] [Toso and Maddock 2017] [Tournes and Johnson 2001] [Trotta et al 2021] [Tullino et al 2023] [Ukigai et al 2017] [Using Cell-DEVS for Prototyping Unmanned Aircraft System Traffic Simulation 2017] [Usmonov and Kretov 2020] [Vaheed et al 2024] [Vidan 2016] [Vijayan and Suresh Babu 2015] [Vittal and Bhat 1993] [Walter 1988] [Wang et al 2015] [Wang et al 2015] [Wang et al 2018] [Wang et al 2024] [Wang et al 2025] [Wang Pei et al 2017] [Weinert and Meyer 1984] [Wenxuan 1991] [White 1989] [White and Clark 1980] [White and Clark 1979] [White and Clark 1980] [Wigginton et al 2015] [Wilcox 1963] [Wilson 2019] [Wilson and Storey 2016] [Wu et al 2020] [Xiang et al 2025] [Xingjun 2023] [Xu and Zhang 2018] [Xu et al 2016] [Xu et al 2023] [Xu et al 2024] [Xu et al 2025] [Xue et al 2024] [Xuefei et al 2023] [Yan et al 2016] [Yang et al 2024] [Ye et al 2021] [Yesilbas 2025] [Yeşilbaş 2025] [Yin and Zhu 2018] [Yin et al 2021] [Ying Xiong 2015] [Yue 2024] [Zanatta et al 2017] [Zhang 2023] [Zhang 2023] [Zhang et al 2017] [Zhang et al 2019] [Zhang et al 2019] [Zhang et al 2020] [Zhang et al 2022] [Zhang et al 2023] [zhang et al 2023] [Zhao et al 2023] [Zhao et al 2025] [Zhao et al 2026] [Zheng et al 2020] [Zhi et al 2015] [Zhiqiang et al 2015] [Zhou and Tan 2024] [Zhou et al 2020] [Zhou et al 2024] [Zurera et al 2025]

Risk, reliability, safety and health management

Risk, reliability, redundancy, safety and health management, with probabilistic risk assessment as a method.

192 records. [5132663 Vehicle safety system and method for monitoring toxic and combustible fuels 1993] [Abbott 2003] [Aerospace Corp El Segundo Ca 1963] [Air Force Space Command Space Missile Sys Ctr 2014] [Alkhatib et al 2025] [Alsafadi and Martinez 1993] [Alvord et al 2024] [An et al 2021] [Anderson and McWilliams 2003] [Anderson et al 2015] [Aras et al 2023] [Aras et al 2023] [Aras et al 2025] [Arisandi 2017] [Atamuradov and Camci 2020] [Atamuradov et al 2020] [Bae et al 2018] [Ballard 2006] [Ballard and Brown 2005] [Barlow 1982] [Barmin et al 2018] [Baroth et al 1999] [Berkowitz and Titulaer 2024] [Bhatt and Singh 2025] [Bibhorr and Anand 2021] [Bird 2020] [Bird and Shao 2020] [Bird et al 2020] [Bishop et al 2018] [Bougacha and Varnier 2021] [Bougacha et al 2021] [Bouhadra and Forest 2024] [Boyd et al 1988] [Brevault et al 2016] [Bridges 1988] [Buzzatto 2015] [Cao 2017] [Cao 2024] [Casel and Bickford 2026] [Chang et al 2018] [Chen and Sakurahara 2025] [Cheng et al 2025] [Christian et al 2023] [Coble et al 2020] [Corbetta 2020] [Cross and Vesely 2018] [Iverson et al 2009] [Dawaare et al 2026] [Decadi and Dias 2022] [Decker and Barbré 2015] [Der Kiureghian 2001] [Desmedt 2002] [Detar et al 2023] [Dong et al 2025] [Ebner and Koops 2022] [Ekimogloy et al 2026] [Energy losses, a resource indicator of the vehicle reliability 2025] [Erickson 1993] [Everline et al 2008] [Ezhilarasu et al 2019] [Farag et al 2025] [Fayssal and Weldon 2008] [Fei 2021] [Fernando 2017] [Fulton 1963] [Gao and Wang 2021] [Gaverina et al 2026] [Gee and Lawrence 2010] [Geisinger 1970] [Genet and Giugliarelli 2025] [Glaser 1996] [Goebel 2024] [Goebel and Rajamani 2021] [Goebel et al 2019] [Gomes and Beck 2016] [Gourab et al 2023] [Grile and Bettinger 2024] [Guikema and Pate-Cornell 2003] [Guikema and Paté-Cornell 2004] [Gujral and Emdee 2016] [Hamza et al 2023] [Harper 1988] [Harris et al 2022] [Ho et al 1998] [Hong et al 2025] [Ireland and Gonzales 2020] [Iverson et al 2010] [Johnson 1988] [Kahle 2000] [Khan et al 2015] [Kim 2026] [Kothakonda et al 2018] [Kouri et al 2022] [Lane et al 2026] [Lanzi and Simpson 2010] [Lechniak et al 2015] [Lee 2019] [Lee 2026] [Leong 2017] [Leuschen et al 1999] [Levine 1964] [Lewis 1985] [Lewis 1989] [Li et al 2016] [Li et al 2020] [Li et al 2025] [Liao 2017] [Liu et al 2017] [Liu et al 2023] [Manwatkar et al 2017] [Maul et al 2024] [McCoy et al 2021] [Meade 2004] [Merriam 2000] [Murthy 2016] [Mustafa et al 2025] [Najarkolaie et al 2023] [Lindsey 2016] [Nasiri et al 2025] [Newman et al 1961] [Nichols et al 2022] [Nick and Buchaillot 2024] [Nishino et al 2015] [Norris et al 2025] [O’Leary et al 2025] [Ofsthun 2002] [Pan et al 2022] [Pandit et al 2025] [PHM for aerospace 2017] [Poissant et al 2020] [Probabilistic Risk Assessment and Its Application in Complex Integrated Task Risk Assessment 2023] [Qing et al 2016] [Racicot 1973] [Randelovic et al 2023] [Rauzy 2018] [Reinhart 2001] [Reliability Analysis Center Griffiss Afb Ny 1981] [Richardson 2024] [Riley et al 2023] [Rosello et al 1996] [Roy et al 2024] [Sabán-Fosch et al 2025] [Safie et al 2015] [Safie and Fuller 2011] [Samson 2024] [Sanchez and Liscouët-Hanke 2020] [Sankararaman and Goebel 2020] [Sarotte et al 2019] [Satoh et al 2020] [Schreiner et al 2016] [Shang and Wang 2024] [Shishko and Matijevic 2000] [Shuo and Yi 2017] [Sindoni et al 2016] [Solanyk 1993] [Sonawane and Daniel Otero 2024] [Sood 2018] [Stenger et al 2020] [Suhir 2026] [Tak and Jung 2018] [Tatry et al 1997] [Thornton 1977] [Trevino et al 2016] [Tuckman 1965] [Turkmen et al 2023] [Uckun 2005] [Unal et al 2000] [Unal et al 2004] [Wang et al 2022] [Wangu and Mouyos 1998] [Weglian and Brinsfield 2023] [Weiss and Brundage 2021] [Welch 2023] [Werner et al 2018] [Wheeler et al 2021] [Wishart et al 2023] [Wood 2020] [Xiao et al 2023] [Xie et al 2015] [Xue et al 2017] [Yang 1981] [Yang et al 2022] [Yau et al 2002] [Yerkes and Scofield 2016] [Yu 2017] [Yusuf and Musa 2021] [Zemoura and Farago 2025] [Zhang and Ma 2020] [Zhang et al 2015] [Zhang et al 2017] [Zhang et al 2025] [Zhu et al 2023]

Design optimisation, uncertainty and computation

Design optimisation, uncertainty quantification, surrogate modelling and computational method.

117 records. [6 DoF Aircraft Simulation Model Capable of Handling Maneuver Events (WIP) 2016] [Abu El-Wafa et al 2022] [Adelmann 2019] [Alexanderian et al 2021] [Azis et al 2025] [Bahrami and Ommi 2022] [Beck and Guillas 2016] [Benek and Luckring 2017] [Benek and Luckring 2017] [Bennich and Lindsey 1967] [Bertoni et al 2018] [Bhattacharya and Jung 2020] [Blanchard and Sapsis 2021] [Branets 2020] [Brevault and Balesdent 2021] [Brevault et al 2017] [Brevault et al 2019] [Brevault et al 2020] [Chen 2025] [Chen et al 2018] [Coons and Huan 2025] [Cusick and Kontis 2019] [Cusick et al 2020] [Dababneh et al 2025] [Dalle et al 2016] [Dalle et al 2023] [Iverson et al 2012] [Davidson 2021] [Dpc 2016] [Dupont et al 2019] [Fajraoui et al 2017] [Fekhari et al 2021] [Findenig et al 2025] [Fohring and Haber 2016] [G J, et al 2019] [Garcia-Cardona et al 2021] [Gerling et al 2024] [Gettatelli et al 2023] [Gong and Pan 2024] [Gorodetsky and Marzouk 2016] [Graziani and Ngom 2024] [Gruhlke et al 2026] [Gu et al 2021] [Głębocki and Jacewicz 2020] [Han et al 2026] [Herold and Boelts 2025] [Hoang et al 2025] [Howe and Bowers 1991] [Hu and Ludkovski 2017] [Ifenna Okoli et al 2021] [Jiahe 2020] [Kamilis and Polydorides 2018] [Kim et al 2026] [Kitaygorsky 2020] [Lartaud et al 2023] [Lenggana et al 2025] [Li et al 2018] [Li et al 2024] [Liu et al 2015] [Luo and Strait 2024] [Marino 2001] [Matushin and Makhalov 2020] [Miller et al 2026] [Ming and Guillas 2021] [Mueller and Kochenderfer 2016] [Murashko and Tkachov 2025] [Nielsen et al 2015] [Noel et al 2003] [Novack et al 2016] [Oh et al 2015] [Oh et al 2017] [Prasad 2022] [Pronzato and Zhigljavsky 2020] [Qi et al 2024] [Rahn and Schottle 1996] [Rheaume and Lents 2018] [Romano et al 2024] [Rosić and Diekmann 2015] [Shahmirzaee Jeshvaghani et al 2015] [Shi et al 2025] [Shulkind et al 2018] [Sinsbeck and Nowak 2017] [Sinsbeck et al 2021] [Smith 1969] [Steffens et al 2016] [Steppert et al 2018] [Sun et al 2021] [Tekin et al 2026] [Tetlow et al 2000] [Thorbergsson and Hooker 2018] [Tobbe et al 2009] [Travelletti et al 2023] [Tuohy 1998] [Uma Sankari et al 2017] [Urschel and Cox 2003] [Villanueva 2022] [Wang et al 2020] [Xiangjun et al 2019] [Xie et al 2021] [Xiong et al 2021] [Xu et al 2020] [Xue et al 2018] [Yan et al 2025] [Yancosek et al 2025] [Yang et al 2016] [Yang Liu and Wanchun Chen 2016] [Yenigelen and Morris 2020] [Yin et al 2017] [Yu et al 2024] [Yu et al 2025] [Zeeshan et al 2021] [Zhang et al 2019] [Zhang et al 2024] [Zhao and Li 2025] [Zhao et al 2021] [Zheng et al 2020] [Zolla et al 2025]

Launch vehicle design, staging and operations

Launch vehicle and spacecraft design, staging and separation, recovery and reuse, and launch operations.

305 records. [Tharun et al 2025] [Aarnio et al 1991] [Abbott and Matzenauer 1990] [Abrahamm and Valsa 2018] [Adams 1968] [Advanced Transportation System Studies 1995] [Africano 1935] [Air Force Space Command Space Missile Sys Ctr 2013] [Allard 2024] [Allen et al 1994] [Antares A low cost 1991] [Ashish and Chandrasekaran 2026] [Argonne Nuclear Rocket Program 1967] [Bacchetti et al 2015] [Badia Rifà et al 2022] [Balaji and Jerry Alexander 2015] [Baumgartner et al 1979] [Bergman 1973] [Biertümpfel et al 2023] [Biliaiev et al 2024] [Birkeland and Meuser 1999] [Blanchet et al 2001] [Boliubash 2025] [Bolster 1967] [Bondar’ et al 2018] [Borello 2024] [Borio et al 2025] [Brinton et al 1994] [Broadfoot 2000] [Brooks 2022] [Buehrle et al 2010] [Buehrle et al 2010] [Buehrle et al 2010] [Burgess 1946] [Cai and Xu 2015] [Cai et al 2024] [Campbell and Thomas 2025] [Carson et al 1986] [Cenkci 1991] [Chalfant 1992] [Chamberlain 1979] [Chandramoul et al 2020] [Chase 1979] [Chelaru et al 2022] [China achieves first reusable rocket booster recovery with world’s first net-capture system 2026] [Cockrell 2008] [Cockrell et al 2007] [Cohen and Wasel 1969] [Coleman 2000] [Coley et al 2018] [Cook 1995] [Cook and Hueter 2003] [Cozzi et al 2024] [Cremaschi et al 2017] [Dahlem et al 1991] [Dalle and Rogers 2015] [Dandappanavar et al 2026] [Dannenberg 2024] [Davis and Greenberg 1988] [Dees and Stockard 2023] [Department Of The Air Force Washington Dc 1988] [Department Of The Air Force Washington Dc 1988] [Dorrington 1987] [Effect of design parameters on a two-stage launch vehicle performance 2018] [Elkins and Galati 1996] [Elvin 1996] [Endicott 1999] [Erickson 1984] [Escartí-Guillem et al 2022] [Faulkner and Lyles 2001] [Feng et al 2019] [Feng et al 2020] [Firsyuk et al 2025] [Fischer and Fasoulas 2024] [Fiske et al 2006] [Flittie and McFarlane 1991] [Flittie et al 1992] [Francine and Stewart 1995] [Freeman et al 1996] [Freeman et al 1997] [Freeman et al 1996] [French 1987] [Fuchs et al 2018] [Szatkowski and Levin 1991] [Gage and Vander Kam 2003] [Garegnani et al 2024] [General Dynamics Corp San Diego Ca 1992] [Godai 1986] [Godai 1987] [Golubek and Dron’ 2020] [Gong et al 2022] [Gonzalez and Marks 1977] [Guruprasad and Mayilvaganan 2023] [Gülgönül and Sözbir 2018] [Hadley 1963] [Hagopian 2002] [Hale 1963] [Hale 1997] [Hardy et al 1993] [Hattis 1981] [Hellman et al 2011] [Hendrickson et al 2020] [Herdy 2026] [Hinckel 1995] [Hoegenauer and Koelle 1989] [Hoerr 2005] [Holguin and Labbee 1988] [Hong and Ahn 2015] [Honkawa and Yoozbashizadeh 2019] [Hudson and Hunter 1987] [Huether and Otto 1995] [Hwang and Ahn 2024] [Hyland 1971] [Imoto 2016] [Integrated operations/payloads/fleet analysis. Volume 1971] [IPAD Integrated Programs for 1980] [Isaev 2025] [Ito et al 2020] [Jacobson 1952] [Jaffe 1988] [Jayan et al 2024] [Jeyakumar and Biswas 2023] [Jones 2024] [Jung et al 2023] [Kam and Gage 2004] [Kaplan 2002] [Karel 1967] [Karuntzos 2015] [Kawashima et al 2025] [Keba and Kulabukhov 2024] [Keith 1991] [Kendrick 1969] [Ketchum 1986] [Kim et al 2025] [Ko and Cho 2016] [Koelle 1986] [Koelle and Koelle 1979] [Kong 2025] [Kravchenko et al 2021] [Krishnaswamy and Mohandas 2025] [Kroncke 1985] [Kruger et al 2019] [Kumar et al 2025] [Kuznetsov 2023] [L. Johnson and W. Vaughan 2020] [Lanaman et al 1965] [Lane et al 1982] [Lang et al 2001] [Lang et al 2002] [Lang et al 2003] [Lee 1977] [Lee et al 2026] [Lewis and Donahoe 2023] [Li et al 2024] [Liao et al 2023] [Liever and Habchi 2004] [Lim et al 2024] [Logsdon and Williamson 1997] [Lohse and Lauler 1963] [Lou et al 2025] [Low-cost expendable launch vehicles 1992] [Low-Cost Satellites and Satellite 1990] [Lubert 2017] [Lyles and Griner 1998] [Macpherson 1962] [Madhavan Nair 2023] [Magistro et al 2025] [Makarenko et al 2015] [Malisuwan and Kanchanarat 2022] [Manwatkar et al 2024] [Martin Co Baltimore Md 1963] [Martin Co Denver Co 1966] [Martin et al 1998] [Martin et al 2024] [Martindale 2006] [Matsuo and Kawaguchi 1995] [Meyers 1991] [Mihaila-Andres et al 2015] [Mikhalev et al 2022] [Miller 1963] [Miller et al 1973] [Milliken 1963] [Mirzabayova and Rustamov 2024] [Mocio 2001] [Morgenthaler and Montoya 1991] [Mori and Maruyama 2016] [Mori et al 2016] [Moser 1965] [Mosley 1970] [Mueller 1964] [Mueser and Irvine 1950] [Murty et al 2016] [Naftel and Powell 1983] [Newman and Stahmann 1963] [Ngo et al 2017] [Nizhnik 2012] [Noneman 2002] [Obermann and Williamson 1998] [Obermann and Williamson 2003] [Oconnor 1966] [Oh et al 2018] [Otte et al 2008] [Peet 2021] [Perumal 2023] [Pinier 2024] [Polsgrove and Thomas 2016] [Portanova et al 1992] [Poston 1995] [Powell 1962] [Powell et al 1991] [Powell et al 1991] [Powell et al 1998] [Puzanov et al 2024] [Qiang Wu and Wei Wang 2016] [Quest and Waganer 1970] [Ragab and Cheatwood 2015] [Ralph 1965] [Ravindran et al 2024] [Raymer 2006] [Reed et al 2016] [Research on the Overall Design of Low Cost Launch Vehicle 2017] [Rey 2000] [Rhisat and Molki 2023] [Rice 1970] [Roback et al 1981] [Roback et al 1981] [Rocket on Rails 1948] [Rooney 2003] [Rucker 2015] [Ryan and Verderaime 1993] [Vinoth 2017] [Sackheim and Dergarabedian 1996] [Saha et al 2020] [Samokhvalova and Shlyakhtenkova 2019] [Sanford et al 2003] [Schumann et al 2011] [Scully 2015] [Sekula et al 2016] [Seltzer 1970] [Shaw and Womack 1984] [Shibato 1995] [Sholes et al 1994] [Shulepov and Popov 2018] [Shulga and Shcheglov 2021] [Silva Oliveira et al 2017] [Simon and Chudoba 2021] [Sinclair et al 2025] [Sithara and Shenil 2022] [Smith and Philips 2003] [Smith and Phillips 2002] [Spencer 1999] [Spiridonov et al 2022] [Staniszewski 2001] [Steffens and Mavris 2015] [Stower 2024] [Stower 2025] [Straub 2018] [Sudol et al 2018] [Swaim 1968] [Swan 2026] [Szatkowski and Schultz 1988] [Szedula 1996] [Takahashi et al 1997] [Tan et al 2024] [Tanck and Steadman 1998] [Taniguchi 2000] [Taylor et al 2008] [Tetik and Das 2017] [The Launch Loop 1985] [Thivent 2024] [Thomas et al 2002] [Timofeev 2020] [Trollheden and Streifinger 1993] [Tuma and Chenevert 2010] [Tumino 2025] [Vivekanand 2024] [Veracka et al 2005] [Von Chorus et al 2025] [Wang et al 2024] [Wente 1982] [White et al 1985] [Whitehead 1990] [Wilhite 1981] [Williams 1971] [Williams and Thompson 1967] [Winchell 1992] [Wolfe 1966] [Worlund 1992] [Wu and Zhang 2023] [Xiao et al 2019] [Yang 2023] [Yang et al 2022] [Yarimbatman and Cengiz 2024] [Yedhu U. Krishnan and Saidalavi P 2015] [Yu et al 2021] [Yuan et al 2025] [Yun et al 2023] [Yuwei et al 2021] [Zaidi and van Zyl 2017] [Zhang et al 2018] [Zhang et al 2022] [Zhao and Jiang 2018] [Zhiqiang et al 2015] [Zhou et al 2015] [Zhou et al 2015]

Flight test, instrumentation and range operations

Flight test management, instrumentation and range operations.

18 records. [Air Force Test Pilot School Edwards Afb Ca 1990] [Air Force Test Pilot School Edwards Afb Ca 1990] [Air Force Test Pilot School Edwards Afb Ca 1993] [American Institute of Aeronautics and Astronautics 1992] [Bowers and Pratt 1985] [Carico 1998] [Chappell 1984] [Development and implementation of a low-cost computer data acquisition system for structural analysis 1990] [General Dynamics/Astronautics San Diego Ca 1961] [General Dynamics/Astronautics San Diego Ca 1962] [General Dynamics/Astronautics San Diegoca 1961] [Lux-Baumann and Burkes 2005] [Jones 1970] [Lux and Burkes 2008] [Lux-Baumann and Burkes 2006] [Martin 1978] [Morelli 1994] [Vehicle performance monitoring system 1991]

Where the Framing Breaks Down

Cost Is Not an Engineering Quantity and This Article Treats It as One

The analysis above prices simplifications in seconds, kilograms and newtons, and then sets the result beside dollars. Those are not commensurable. A gas generator that costs at most 11.46 seconds of specific impulse, the upper bound the schematic’s flows give, is a fact. Whether that trade was worth making depends on a price never published for a chamber never built in quantity.

This article can compute what simplification cost in physics and cannot compute what it saved in money, and every conclusion about the trade is therefore one-sided.

The Cost Comparison Has a Denominator Problem

Dividing programme cost by vehicle mass is a crude instrument and the numbers move a great deal with the choice. Dividing by the number of airframes built gives a different answer. Dividing by flights achieved gives infinity for both. The mass denominator was chosen because both programmes published a mass, and no denominator would have made the comparison rigorous.

The Review Might Simply Have Been Right

This article has treated the 305 percent growth computed in The Review That Ended It as the price of restoring what low-cost planning removed. There is a less flattering reading and it deserves stating. The original estimate may have been wrong on its own terms rather than deliberately thin, and a programme that underestimates by a factor of four has a competence problem instead of a philosophy.

The record does not distinguish these, and the two readings differ in what they imply. Under the first, low-cost demonstration is a coherent strategy that must budget for eventual rigour. Under the second, the X-34 is a badly estimated project and there is no general lesson at all.

The Comparison With the X-33 Flatters the X-34

The two vehicles were not trying to do the same thing and the per-pound comparison quietly assumes they were. The X-33 was attempting a mass fraction no vehicle had achieved, with technologies never before built. The X-34 was attempting a flight profile within reach of existing practice. A programme attempting something harder should cost more, and some of the ratio is that rather than efficiency.

Behind that caution lies the cluster on cost estimation, cost growth and acquisition, which includes the estimation of weapon system cost growth in Asher and Maggelet 1980 and the evidence on acquisition policy and the cost growth of major programmes in McNicol and Wu 2014.

The Source Base

This article rests on 2,066 research records published through 2001, when the programme was cancelled, and 2,880 published from 2015 onward.

The research survey holds 5,367 research records drawn from the NASA Technical Reports Server, the Defense Technical Information Center and the journal literature indexed by Crossref, of which 965 are report primaries, being 18.0 percent, by the identifier rule set out under The Definition of Primary. The median publication year is 2015. Of the 5,362 dated records, 2,066 were published through 2001, being 38.5 percent, and 2,880 were published in 2015 or later, being 53.7 percent. The survey gathers the literature of the programme’s own period and the contemporary literature, so the 416 records dated 2002 to 2014 do not represent the literature of those years.

A second primary base sits well before 1996. Ablative chamber and nozzle materials were characterised from the late 1950s onward, largely for solid rocket motors, and a 1960s report on throat erosion is a primary source for this article’s recession estimate in a way that a 2020 planetary entry study is not.

The cost of a Fastrac combustion chamber in production is not in the public record, and it is the single number that would decide whether the ablative choice was economically right. The article computes everything around that hole and says where the hole is.

The Definition of Primary

Primacy is a property of the document, and this survey derives it from the identifier. A record is a report primary when its address is on the NASA Technical Reports Server or it carries a digital object identifier under the 10.21236 prefix, which Crossref registers for Defense Technical Information Center reports. The vehicle’s own record is primary almost entirely under that rule. Of the 39 titles that name the X-34, 34 are report primaries, and the other 5 are papers of the American Institute of Aeronautics and Astronautics. The rule does not reach the journal papers among the foundational sources, so 18.0 percent is a lower bound on how much of the survey is first-hand.

The programme window is 1996 to 2001 and it is short. Within it the primary record is the engine’s development literature, which is substantial because a government laboratory built the engine and published, and the airframe literature, which is thinner because a company built the airframe and did not.

That asymmetry is the same one the X-32 article found and it points the other way here. The engine is documented like a research project because it was one. The vehicle is documented like a contract deliverable because it was one. Two halves of a single programme, and the half a research agency owned is the half that left a literature.

Thin Subjects

Six subjects that this article’s derivations depend on have thin literatures. Each count below is the number of research records in this survey whose title carries at least one of the listed terms, with a hyphen read as a space. Where a row joins two groups of terms with the word together, a title must carry a term from each group.

Subject Title terms counted Records
the rocket equation and the ascent loss budget rocket equation, Tsiolkovsky, gravity loss, ascent loss, velocity budget, steering loss, drag loss 1
the effective heat of ablation heat of ablation 2
propellant bulk density bulk density, propellant density, propellant densities 2
the gas generator cycle by name gas generator cycle, turbine exhaust 5
the cost of an ablative chamber cost, price, affordable, affordability together with ablative, ablation, ablator 1
the turnaround of a reusable vehicle turnaround 1

No research record takes the rocket equation or the ascent loss budget as its subject. The one title that names the rocket equation describes a software tool built on it, and none names a gravity, drag or steering loss. Both are thin headings over subjects nobody writes papers about, because both live in every textbook and in no journal article.

The effective heat of ablation names two records, a 1964 study of graphite and a 1987 laser experiment on graphite, which is the same phenomenon in a milder form, since the quantity is discussed throughout the ablation literature under the vocabulary of char layers, blowing parameters and surface energy balances rather than under its own name.

Propellant density, on which the comparison with the X-33 turns, names two titles, a 1952 study of variable propellant density and a 2009 study of a microwave thermal rocket, so the ratio of 2.945 rests on tabulated densities rather than on a literature of its own.

The gas generator cycle is named in five titles, all of them design or operating studies of engines or of their components, and none names the turbine exhaust, so the identity between the cycle’s flow and impulse penalties rests on the derivation above.

The cost of an ablative chamber, the number the Epistemic State calls the hinge of the trade, appears in one title, a 1995 programme of ablative material testing for low-pressure, low-cost rocket engines, which names low cost as a design goal.

Turnaround, the one quantity that would have tested the cost argument, names one title, a 2004 turnaround time model for conceptual rocket engines.

A subject can be thin because the work was never done, because the heading is wrong, or because the knowledge is so settled that it stopped generating papers. The rocket equation and the heat of ablation are the third kind, and the third kind is invisible to a count. The cost of an ablative chamber and the turnaround of a reusable vehicle are the first, because no vehicle of the kind was built in quantity or flown often.

What the Survey Admits

A record is admitted only when a person reading its title finds it on this article’s subject. Its records come from the report servers and from the journal literature. Many words this subject depends on also name something else, and a record that shares only such a word is excluded. Tile also names the ceramic tile industry and the tiles of computer memory and maps, reusable also names the revenue management of reusable resources, ablation also names laser machining and laser deposition, recession also names the retreat of Niagara Falls and of glaciers, vehicle and landing also name road, rail, marine and underwater craft and ground robots, and kerosene and combustion also name the piston engine, including kerosene engines described between 1898 and 1905. The programme’s own names are homonyms too. Fastrac also names a tractor, a road traffic control system, a video rate control algorithm and a resin infusion process for composites, MC-1 also names a partial pressure suit, and Pegasus also names a spoken-language travel interface and an airborne assault concept. Faster, better, cheaper is also a slogan of genotyping, drug manufacture and car assembly. Air launch also names the release of missiles, sonobuoys, windsondes and balloons from aircraft, and carrier aircraft also names the aircraft of naval carriers, so weapons, oceanography and naval aviation are excluded. Correction, erratum, retraction and withdrawal notices, figure, table and supplementary-material records, editorials, conference welcomes, recordings, peer-review reports, journal front matter and news items, signed or unsigned, are excluded as well, because they are parts of works or editorial events and not research works. Reviews of books, dictionary and other reference entries of two pages or fewer, puzzles, and the abstracts of papers, patents and reports reprinted in the abstract sections of other journals are excluded on the same ground, while an authored encyclopedia article of more than two pages and a textbook chapter are research works and stay. A document deposited twice under two identifiers is counted once. No residual cluster remains. Every admitted record belongs to one of the named clusters, because a title that shares only a word with the subject, such as launch, vehicle or turnaround, or that belongs to a distant domain, such as satellite payloads, electric propulsion or gun-launched micro air vehicles, is excluded rather than gathered as other literature.

Some classes of doubtful relevance are kept rather than excluded. They are piston engine studies of combustion chamber wall heat transfer and wall coatings, kept because the article uses gas-side heat transfer, probabilistic risk assessment and health management outside aerospace, kept as method, generic heat transfer and gas turbine film cooling studies, whose physics is that of the rocket chamber, fire science on the charring of wood and of flame-retardant polymers, additive manufacturing process studies with no named product, Bayesian experimental design and uncertainty quantification on non-aerospace examples, autonomous landing of unmanned aircraft on moving platforms, and signed trade-press articles on rockets and launches. A reader who rules any of those classes out will find the survey that much smaller.

Every research title has been read for relevance, so the off-topic share that remains is a matter of reading judgement. A reading of titles cannot show that a work is relevant in substance, so this is a statement about titles only.

Epistemic State

Historical Fact

The X-34 contract was awarded to Orbital Sciences in August 1996 as a fixed-price award of 49.5 million dollars, and the vehicle and engine projects were budgeted at about 86 million dollars. The Fastrac engine, also designated MC-1, was developed by the agency’s Marshall centre, used a gas generator cycle and an ablatively cooled chamber and nozzle, and was fired for up to 159.03 seconds. The first airframe rolled out in 1999 and made three captive flights beneath the carrier aircraft that year, the first on 29 June. Two airframes of the three planned were completed. No free flight, powered or unpowered, was ever made. A joint review in 2000 identified inadequate system testing, single-string avionics and unvalidated automatic landing among the risks, and an estimate drawn from the restructure plan put the total requirement near 348 million dollars. The programme ended on 31 March 2001, after a funding decision announced together with the X-33’s. The two airframes passed through storage and a private yard and reached a scrapyard by April

  1. The spending of just under 112 million dollars rests on a secondary compilation alone.

Engineering Analysis

The 5.69 percent gap in the usually quoted engine figures is this article’s arithmetic, and its resolution as a pairing of the 15:1 nozzle’s thrust with the 30:1 nozzle’s impulse rests on the development status report’s schematic. The 91.90 kilogram per second flow, the gas generator fraction of 3.50 percent and the 11.46 second upper bound on the impulse the cycle costs are arithmetic on that schematic’s flows and thrust, and the identity that the fractional impulse penalty equals the fractional flow diversion is exact. The 148 second burn time and its 1.075 margin against the longest published test are arithmetic on published masses and flow. The throat diameter is published, and the characteristic velocity and thrust coefficient derived from it depend on taking the requirement table’s 652 pounds per square inch rather than the schematic’s 633 as the chamber pressure. The liner recession figures depend on an assumed recession rate and are presented as a range. The air-launch energy donation of 531.9 metres per second and the 29.3 percent thrust recovery depend on an approximate published release altitude, an assumed release Mach number and the published area ratio, and the thrust recovery overstates the sea-level case. The bulk densities and the 2.945 ratio are arithmetic on published densities, with the RP-1 density taken at the middle of a published range. The result that the gauge-limited tank fraction goes as one over the radius is derived here, and the finding that the ratio between two propellant systems is exactly the inverse of their bulk density ratio is an identity rather than a coincidence.

Inference

That the 305 percent growth measures the price of restoring what low-cost planning removed is an inference, and the competing reading, that the original estimate was simply wrong, is set out in the Where the Framing Breaks Down section and is not excluded by anything in the record.

That the X-34’s ablative chamber was a defensible economic choice is not asserted, because the number that would decide it was never published.

That a small demonstrator cannot stand in for a large vehicle’s tank fraction is an inference from the minimum gauge argument, and it assumes the X-34’s tanks were built to the same minimum gauge as the previous article’s, which the record does not state.

What the Record Does Not Settle

Whether the X-34 would have flown successfully is not settled. Nothing on the vehicle had failed. Nothing had been demonstrated either.

Whether rapid turnaround was achievable is not settled and could only have been settled by flying.

The production cost of the engine’s consumable chamber is not settled, and it is the hinge of the entire ablative trade.

The tank radius used in the scaling comparison is assumed rather than published, and the comparison moves with it, though the direction of the conclusion does not.

Out of Scope

The detailed thermochemistry of ablation. The carrier aircraft and its modification. The Pegasus booster from which the operating method descends. The X-33, treated in the previous article. The Space Launch Initiative that absorbed both programmes. The disposal history of the airframes beyond the fact of it. The commercial position of the contractor.

Conclusion

The X-34 was cancelled because somebody finally priced the risk.

Nothing on the vehicle broke. No structure failed a test, the engine’s development problems were found and corrected on the ground, and no aerodynamic surprise appeared. What happened is that a programme built to be cheap was asked what it would cost to fly safely, and the answer was four times what it had been given.

The things that made it cheap and the things that made it unflyable were the same things. Single-string avionics, thin system testing and an unvalidated automatic landing are exactly what a low-cost demonstrator deletes and what must be restored before anyone drops a rocket aeroplane over inhabited ground. The cost was never removed. It was deferred, and the deferral carried interest of 305 percent.

Set beside the previous article the pair is exact and inverted. The X-33’s binding quantity was mass, which obeys a conservation law, and its demonstrator returned a reading that did not close. The X-34’s binding quantity was cost, which obeys nothing, and its demonstrator returned a revised estimate. One programme was killed by a number it measured. The other was killed by a number it recalculated.

The physics the cost argument left behind does compute, and it mostly finds the choices sound. The gas generator costs 3.50 percent of the propellant and exactly 3.50 percent of the impulse. The kerosene the vehicle burned is 2.945 times denser than the hydrogen the X-33 carried, which rescues a small vehicle from the minimum-gauge penalty that its size imposes. Air launch donates under six percent of an orbital energy budget and recovers 29.3 percent of the engine’s thrust, so the benefit usually claimed for it is the smaller one. And the ablative chamber, the emblem of the whole approach, made a reusable vehicle that consumed a combustion chamber every flight.

This series has now met a designation marking an absence of demand in the X-27, an absence of knowledge in the X-30, an answer nobody wanted in the X-33, and here a vehicle that was finished, was never asked a question it could fail, and was scrapped. Of the four it is the only one that was ready.

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