X-Planes: Lockheed Martin X-55 ACCA

The register of designations allocated since August 1998, which Andreas Parsch compiles from data the Department of Defense has released, holds 539 rows in the copy the compiler last updated on 23 August 2026, and exactly one of their mission statements makes the way a vehicle would be manufactured the thing to be proved. It belongs to the X-55 [Parsch, DOD 4120.15-L Addendum, MDS Designators Allocated After 19 August 1998].

This is the fifty-sixth 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, the X-33, the X-34, the X-35, the X-36, the X-37, the X-38, the X-39, the X-40, the X-41, the X-42, the X-43, the X-44, the X-45, the X-46, the X-47, the X-48, the X-49, the X-50, the X-51, the X-52, the X-53, and the X-54.

The aeroplane flew before it had the number. Its first flight was on 2 June 2009 and the designation was approved on 19 October 2009, 139 days later [Lockheed Martin X-55] [Parsch, DOD 4120.15-L Addendum, MDS Designators Allocated After 19 August 1998]. That is the third article running in which the number and the flying have come apart, after an aeroplane designated more than a year after it stopped flying [X-Planes: Boeing X-53 Active Aeroelastic Wing] and a number allocated to an aeroplane that was never built at all [X-Planes: Gulfstream X-54].

This article is about a way of building things, and almost nothing in it is about flight.

The Research Question

On 19 October 2009 the joint designation registry recorded the following against X-55A, allocated to Lockheed Martin, powered by two Pratt and Whitney PW306B engines, and sponsored by the United States Air Force [Parsch, DOD 4120.15-L Addendum, MDS Designators Allocated After 19 August 1998].

Highly modified, experimental transport to validate extreme time and cost compression in airframe manufacture using large, unitized composite structures fabricated using low-temperature, out-of autoclave curing techniques.

Of the 539 allocation rows the addendum carries, the X-55A’s mission statement is the only one that names manufacture, the only one that names fabrication, the only one that names a unitized structure and the only one that mentions an autoclave. It shares the word composite with one other entry and the word cost with ten. Every one of those ten describes a vehicle that is itself cheap, being low-cost aerial targets, low-cost cruise missiles and a low-cost unmanned aircraft. In those entries cost is an adjective on the article. In this one it is the dependent variable.

The copy counted here is later than this article’s date. The version current on that date, the compiler’s update of 11 August 2025 as the Internet Archive captured it on 25 November 2025, held 526 rows [Parsch, DOD 4120.15-L Addendum, 11 August 2025]. In it the four distinctions of the X-55A row and its one shared use of composite are the same, and it shares cost with eight entries, because the two low-cost cruise missiles allocated on 17 September 2025 had not yet been entered. Each of those eight also describes a cheap vehicle.

One other entry in the register makes a claim about construction, and it invites comparison because it uses the same metric. The FA-18E was allocated on 12 April 2004 with a mission statement recording that the aircraft is approximately twenty-five percent larger than its predecessor and contains forty-two percent fewer structural parts [Parsch, DOD 4120.15-L Addendum, MDS Designators Allocated After 19 August 1998]. A part count is also the X-55’s measure.

The difference is what the sentence is for. The fighter’s part count is a property it already has, stated about an aeroplane in production. The X-55’s manufacture is the hypothesis, stated about an aeroplane that did not yet exist, in a register whose other entries describe what a vehicle will do.

Read as an engineering brief that sentence contains three claims and they do not all point the same way. Time is to be compressed. Cost is to be compressed. And the curing is to be done at low temperature and outside an autoclave. The last of those is a method, and this article’s central arithmetic is that the method makes the first one harder.

Programme Origin

The programme had two halves, an argument about cost assembled over a decade on the ground and an airframe cut from an existing aeroplane to carry that argument into the air. The two subsections below take them in that order.

The Programme It Came Out Of

The X-55 is the flight article of an argument that took eleven years to assemble. The Composites Affordability Initiative ran from the mid 1990s as a joint effort of the Air Force Research Laboratory, the Office of Naval Research, Bell, Boeing, Lockheed Martin and Northrop Grumman, at a reported 152 million dollars over eleven years [Market Trends, the Composites Affordability Initiative, Part I, CompositesWorld] [Air Force Research Laboratory].

Its central finding was not about materials. The initiative found that much of the cost of a composite airframe lies less in fabrication than in assembly, and that the way to attack assembly is to have fewer parts to assemble, by replacing assemblies of many parts with larger integrated structures joined by adhesive bonding in place of fasteners [Market Trends, Composites Affordability Initiative, Part II, CompositesWorld] [Butler 2000] [Baron and Leger 1998]. The initiative’s studies put a range on it. Bonding cut assembly time by 50 to 80 percent against typical fastened structure, depending on the article, which translated to cost savings of 20 to 50 percent [Market Trends, the Composites Affordability Initiative, Part I, CompositesWorld].

The estimate at the root of the argument was published in 1998. A companion paper to the initiative’s first phase estimated what more unitised aircraft structure is worth in cost and in weight, the quantity the X-55 was later built to test [Holzwarth 1998] [Affordable Composite Structures].

The idea is older than the composites. The Air Force ran the Primary Adhesively Bonded Structure Technology programme in the 1970s to establish that a metal airframe could be bonded rather than riveted, and its detail design report is the ancestor of every argument in this article about replacing fasteners with adhesive [Douglas Aircraft Co Long Beach Ca 1977]. The X-55 is the composites answer to a question the Air Force had already asked about aluminium.

The registry entry compresses that conclusion into one sentence and then asks for an aeroplane to test it.

What Was Built

The airframe began as a Fairchild Dornier 328JET, a regional jet of thirty to thirty-three seats with a high wing and two Pratt and Whitney Canada PW306B turbofans [Fairchild Dornier 328JET] [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld] [Lockheed Martin X-55] [Pratt and Whitney Canada PW300]. The fuselage behind the cockpit was cut off and replaced together with the vertical tail, and the existing horizontal tail was joined to the new structure [Out-of-Autoclave Prepregs, Hype or Revolution, CompositesWorld] [The Carbon Comet, Lockheed Martin]. The wing, the engines, the landing gear, the avionics and the forward fuselage stayed as they were [The Carbon Comet, Lockheed Martin].

The replacement was a composite mid and aft fuselage with the vertical tail integrated into it. The fuselage was made as an upper and a lower half, each roughly 65 feet long, bonded to circular frames and to each other along a longitudinal seam with adhesive and ply overlays [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld] [Lockheed Martin X-55]. The skins were a sandwich, with facesheets of out-of-autoclave carbon epoxy prepreg over a nonmetallic honeycomb core [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld] [Honeycomb Structure] [Prepreg]. That choice is not incidental to the process. A sandwich takes its bending stiffness from the separation of its faces rather than from their thickness,

\[D \approx \frac{E_{f}\,t_{\text{face}}\,h_{c}^{2}}{2} \tag{1}\]

so a 1.5 millimetre facesheet across a 25 millimetre core is stiffer in bending, by a factor of about 208, than the same two facesheets would be laid solid against each other. A process with one atmosphere of consolidation makes a thin facesheet well, and the arrangement therefore suits the method. It also makes the method harder, because the air under a facesheet must find its way out past a core that is trying to seal it in, a difficulty the literature documents [Levy et al. 2015]. The vertical tail was fibre placed from a conventional prepreg tape, its skins precured in an autoclave [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld]. The work was done at the Advanced Development Programs facility at Air Force Plant 42 in Palmdale [Skunk Works] [United States Air Force Plant 42].

The manufacturer gives two figures for the result, and the argument depends on both. Approximately 300 structural parts against approximately 3,000 for a metallic design of the same size, and approximately 4,000 mechanical fasteners against approximately 40,000 [The Carbon Comet, Lockheed Martin]. Both are a factor of ten, or ninety percent fewer fasteners.

The trade press states that figure as ninety-eight percent and the manufacturer’s numbers give ninety. The discrepancy is recorded here and left unresolved, because the two sources may be counting different structures, and this article uses the manufacturer’s pair throughout since it supplies both halves of each comparison [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld].

Sizing From First Principles

The thing to be sized here is a process rather than an aeroplane, because the aerodynamics were the Dornier’s and the registry entry names manufacture as the thing to be proved. This section therefore sizes the pressure vessel a conventional cure needs, the consolidation pressure a vacuum bag can supply at Air Force Plant 42, what that pressure has to accomplish inside a laminate, the dwell a low-temperature cure costs, and the assembly labour that unitisation removes. Every figure in it is computed from published constants and none was measured on this aeroplane, as the Epistemic State section records.

An Autoclave Is a Pressure Vessel

A conventional aerospace laminate is cured in an autoclave, a heated pressure vessel that raises the gas around the bagged part to something near 85 pounds per square inch while the bag itself is evacuated [Autoclave, Industrial] [Out-of-Autoclave Prepregs, Hype or Revolution, CompositesWorld] [Campbell, Manufacturing processes for advanced composites]. The datasheet’s autoclave cure for the X-55’s prepreg specifies 90, and this article works with the typical 85 throughout [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. The pressure is not there to shape the part. It is there to close the voids.

An autoclave is therefore a pressure vessel, and a pressure vessel scales badly. Hoop stress fixes the wall thickness as the pressure times the radius over the allowable stress [Pressure Vessel].

\[t_{w} = \frac{p\,r}{\sigma_{\text{allow}}} \tag{2}\]

The shell mass is the density times the shell area times that thickness, and the shell area is itself proportional to the radius times the length.

\[m_{\text{shell}} = 2 \pi \rho \, r \, L \, t_{w} = \frac{2 \pi \rho \, p \, r^{2} L}{\sigma_{\text{allow}}} \tag{3}\]

For a vessel whose length keeps pace with its diameter the steel therefore goes as the cube of the diameter. Doubling every dimension multiplies the shell by eight, as the arithmetic below confirms.

Vessel	Shell steel
One able to take a 65 foot fuselage half	18.4 tonnes
The same vessel with every dimension doubled	147.5 tonnes
One able to take a heavy-lift launch vehicle barrel, 40 by 80 feet	190 tonnes

Here the obvious argument, the first one a reader is likely to reach for, fails. The usual case for out-of-autoclave processing is that no autoclave is large enough. That case is real for a launch vehicle, where the barrel sections are nine to ten metres in diameter and the vessel that would take them has been estimated at around 100 million dollars to build and install [Out-of-Autoclave Prepregs, Hype or Revolution, CompositesWorld] [Sutter et al. 2010].

It is not the case here. A vessel able to take a 65 foot fuselage half has a shell of roughly 18.4 tonnes, about a tenth of the launch vehicle case. The X-55’s reason for leaving the autoclave was therefore not that it could not fit. The reasons the trade press gives for leaving it are the capital and operating cost of the vessel, low-cost tooling on short lead times, and a factory in which large parts no longer queue for a single autoclave, and the same account warns that cycle times may be longer [Out-of-Autoclave Prepregs, Hype or Revolution, CompositesWorld] [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld].

The Pressure a Vacuum Bag Cannot Supply

A vacuum bag has one source of pressure, the atmosphere. The bag is evacuated and the air outside presses the laminate against the tool [Vacuum Bag Moulding]. Writing the consolidation pressure as the differential across the bag puts the argument of this section in one line.

\[\Delta p_{\text{bag}} = p_{\text{amb}} - p_{\text{in}} \qquad\qquad \Delta p_{\text{autoclave}} = p_{\text{gauge}} + p_{\text{amb}} - p_{\text{in}} \tag{4}\]

The gauge pressure in the autoclave term is the only difference between the two processes. Setting the bag pressure to zero in both gives the ratio the rest of this article turns on.

\[\frac{\Delta p_{\text{autoclave}}}{\Delta p_{\text{bag}}} = 1 + \frac{p_{\text{gauge}}}{p_{\text{amb}}} \tag{5}\]

A vacuum bag can never press harder than the weather allows, and the ceiling falls with the elevation of the factory floor. The autoclave’s ratio, by contrast, rises with elevation, because the denominator falls while the gauge pressure does not.

The standard atmosphere gives the ambient pressure as a function of geopotential altitude, with the troposphere’s constant lapse rate [U.S. Standard Atmosphere] [Barometric Formula].

\[p(h) = p_{0}\left(1 - \frac{\lambda h}{T_{0}}\right)^{\frac{g}{R_{\text{air}}\lambda}} \tag{6}\]

Here $R_{\text{air}}$ is the specific gas constant of air, a different quantity from the molar gas constant $R$ that appears in the cure kinetics below. With the sea level values and a lapse rate of 0.0065 kelvin per metre the exponent is 5.256. Air Force Plant 42 stands at 2,542.5 feet in the Federal Aviation Administration’s airport record, which is 775.0 metres, and the encyclopaedia entry rounds it to 2,542 feet [Palmdale USAF Plant 42 Airport, Airport Data, Federal Aviation Administration] [United States Air Force Plant 42]. The relation gives 92.36 kilopascals there against 101.33 at sea level.

The maximum consolidation pressure available in that building is therefore 13.39 pounds per square inch, against 14.7 at sea level. The elevation alone costs 8.85 percent of it, and no pump can recover any part of that, because the pressure is not being generated inside the bag. It is being withheld from outside.

Reduced consolidation pressure is not a curiosity invented for this article. Consolidation under pressure lower than nominal is a studied subject, because a bag that leaks, a site that is high, or a vacuum system that underperforms all present the laminate with the same deficit, and the measured consequence is porosity [Centea and Hubert 2013] [Serrano et al. 2017].

This has a consequence in the material specification that is easy to miss. The datasheet for the prepreg the fuselage was made from calls for a minimum vacuum of 980 millibar, which it also writes as 29 inches of mercury, and calls that the ideal level while recognising that it is not always possible to attain [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. The entire atmosphere at Plant 42 is 27.27 inches of mercury. Read as a gauge vacuum, meaning inches below ambient, that specification is unattainable there by 1.73 inches, not because of any deficiency in the equipment but because the air on that site does not contain that much pressure to remove.

The reading that makes the specification attainable is the absolute one, meaning that the bag is to be pumped down to about thirty millibar absolute, being 1,013 less 980, which a pump does without reference to ambient. The two readings are not interchangeable, and the difference between them grows by roughly one inch of mercury for every thousand feet of elevation. That round figure is no separate fact but the derivative of the relation above. Differentiating the hydrostatic balance at sea level gives

\[\left.\frac{\mathrm{d}p}{\mathrm{d}h}\right|_{0} = -\frac{p_{0}\,g}{R_{\text{air}} T_{0}} = -\frac{p_{0}}{H} \qquad\qquad H = \frac{R_{\text{air}} T_{0}}{g} \tag{7}\]

with a scale height $H$ of 8,435 metres, which works out at 1.081 inches of mercury per thousand feet. The round figure of one inch is 7.5 percent low against that derivative.

The physically meaningful quantity is the differential across the bag, and that quantity is capped by ambient under either reading.

What Has to Replace the Pressure

Since an out-of-autoclave process gives up a factor of 7.35 in pressure, the question is what the pressure was doing. For an entrapped gas at constant temperature, Boyle’s law gives the volume as inversely proportional to pressure [Boyle’s Law].

\[V_{1} = V_{0}\,\frac{p_{0}}{p_{1}} \tag{8}\]

The void fraction is not the void volume, because compressing the gas shrinks the laminate as well. With the solid taken as incompressible beside a gas, an initial void fraction $\phi_{0}$ becomes

\[\phi_{1} = \frac{\phi_{0}\,p_{0}/p_{1}}{\left(1-\phi_{0}\right) + \phi_{0}\,p_{0}/p_{1}} \tag{9}\]

A process engineer asks the inverse question. The concern is not what a given pressure achieves but what pressure a given specification demands, and solving the relation for the pressure ratio answers it.

\[\frac{p_{1}}{p_{0}} = \frac{\phi_{0}}{\phi_{1}}\cdot\frac{1-\phi_{1}}{1-\phi_{0}} \tag{10}\]

Now put a real number through it. A government and industry team cured the same prepreg family the X-55 used, after it had been left out of the freezer for thirty-five days, and measured 8.3 percent voids by acid digestion against 0.1 percent for the fresh material [Sutter et al. 2010]. Taking that laminate into a full autoclave and squeezing it would leave 1.22 percent. Primary structure requires less than 1 percent [Out-of-Autoclave Prepregs, Hype or Revolution, CompositesWorld], and reaching that from 8.3 percent by compression alone needs a pressure ratio of 8.96, which is more than an autoclave supplies.

A void resists more than compression. A void is a bubble, and its surface holds a pressure difference across it that grows as the bubble shrinks [Laplace Pressure].

\[p_{\text{void}} - p_{\text{resin}} = \frac{2\gamma}{r} \tag{11}\]

That relation decides where each process runs out. Setting the excess equal to the available consolidation pressure gives the radius below which a void cannot be closed by pressure at all.

\[r_{\text{min}} = \frac{2\gamma}{\Delta p} \tag{12}\]

With a surface tension of 0.035 newtons per metre for an uncured epoxy, a vacuum bag at Air Force Plant 42 stops at 0.758 micrometres and a full autoclave at 0.103. The autoclave’s real advantage is not that it squeezes harder in bulk. It is that it reaches voids 7.35 times smaller, and the factor is the pressure ratio exactly, because the radius is inversely proportional to it. A one micrometre void sustains 10.15 pounds per square inch on its own account, which is 76 percent of everything a bag can bring to bear.

So the pressure was never mainly compressing the voids. It was helping to remove them, by dissolving gas into the resin, which Henry’s law makes proportional to the pressure applied [Henry’s Law],

\[c = k_{H}\,p \tag{13}\]

and by driving resin into places air had been. An out-of-autoclave prepreg does the same job by architecture instead. The tows are only partially impregnated, so dry fibre bundles form a connected network of channels through which air and volatiles can be drawn out under vacuum before the resin flows and seals them [Grunenfelder et al. 2013] [Helmus et al. 2015a]. Flow through that network is a Darcy problem, with the volumetric flux set by the permeability, the viscosity and the pressure gradient [Darcy’s Law].

\[q = -\frac{k}{\mu}\,\nabla p \tag{14}\]

The permeability of a bed of fibres is set by their diameter and by how tightly they are packed, in the form the composites literature writes as the Kozeny-Carman relation.

\[k = \frac{d_{f}^{2}\,\left(1 - V_{f}\right)^{3}}{\kappa\,V_{f}^{2}} \tag{15}\]

For seven micrometre carbon fibre at a fibre volume fraction of 0.55 that is about $9.23 \times 10^{-13}$ square metres. Taking a linear gradient over a path of length $L$ and a porosity $\varphi$, the time for the flow to sweep that path is

\[t_{\text{sweep}} = \frac{\mu\,\varphi\,L^{2}}{k\,\Delta p} \tag{16}\]

Working that relation shows which fluid governs the process. Two different fluids move through those channels. Air leaves them, and resin closes them, and their viscosities differ by a factor of 540,541.

\[\frac{t_{\text{resin}}}{t_{\text{air}}} = \frac{\mu_{\text{resin}}}{\mu_{\text{air}}} \tag{17}\]

Gas escape is not the bottleneck and was never going to be. At 13.39 pounds per square inch, air crosses ten millimetres of dry tow in 0.01 seconds, and four hours of vacuum would clear 12.1 metres of it. The same path takes resin 1.47 hours to fill. The length of the path is not the constraint on a part this size, and since the time goes as the square of the length, a permeability a hundred times worse would still clear more than a metre.

What the process races is whether the channels are still open when the air needs them. That is a question about the resin’s viscosity history, and therefore about how long the material has been out of the freezer. The void mechanism and the out-life argument meet here, and the subsection on the material’s clock below puts a price on that meeting.

It is also why debulking, the practice of applying vacuum at intervals during layup as well as at the end, matters far more without an autoclave than with one [Hu and Nutt 2020] [Liu and Hubert 2021].

Low Temperature and Time Compression Pull Against Each Other

The registry entry asks for extreme time compression and for low-temperature curing in the same sentence, and the material datasheet prices the second against the first.

A thermoset cure is a chemical reaction whose progress is measured as the fraction of the total reaction heat already released, and that fraction is what a calorimeter reports [Thermosetting Polymer].

\[\alpha(t) = \frac{H(t)}{H_{\text{ult}}} \tag{18}\]

Epoxy amine cure is autocatalytic, its rate rising from zero before it falls, and the calorimetric literature fits it with a two-constant model of the following form [Vyazovkin and Sbirrazzuoli 1996] [Keenan 1987].

\[\frac{\mathrm{d}\alpha}{\mathrm{d}t} = \left(k_{1} + k_{2}\,\alpha^{m}\right)\left(1 - \alpha\right)^{n} \tag{19}\]

Both rate constants follow an Arrhenius law, so the time to reach a given degree of cure rises exponentially as the temperature falls [Arrhenius Equation] [Kratz et al. 2012].

\[t \;=\; A_{0} \exp\!\left(\frac{E_{a}}{R\,T}\right) \tag{20}\]

The datasheet supplies two points on that curve and does not divide them. It offers twenty hours at 80 degrees Celsius and two hours at 130, both as oven vacuum bag cures [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. A factor of ten in time across fifty kelvin is an activation energy.

\[E_{a} \;=\; R\,\frac{\ln\!\left(t_{1}/t_{2}\right)}{1/T_{1} - 1/T_{2}} \tag{21}\]

With the dwells in hours, the temperatures in kelvin and the molar gas constant at 8.314 joules per mole per kelvin, the two datasheet points give

\[E_{a} = 8.314 \times \frac{\ln\left(20/2\right)}{1/353.15 - 1/403.15} = \frac{19.14}{3.512 \times 10^{-4}} \approx 54{,}510 \tag{22}\]

joules per mole. That gives 54.5 kilojoules per mole, which sits within the 50 to 60 kilojoules per mole normally observed for epoxy amine systems, so the two-point fit is not an artefact [Zhang and Vyazovkin 2007] [Kratz et al. 2012] [Strong, Fundamentals of composites manufacturing]. With it, the price of any temperature reduction follows directly.

\[\frac{t_{\text{lo}}}{t_{\text{hi}}} = \exp\!\left[\frac{E_{a}}{R}\left(\frac{1}{T_{\text{lo}}} - \frac{1}{T_{\text{hi}}}\right)\right] \tag{23}\]

Ten degrees, from 120 to 130, costs 1.51 times the dwell and sixty degrees, from 120 to 180, costs 9.1.

One caveat bounds what the fit means, so it is stated here in the text. The datasheet’s cure options are not iso-conversional. Each reaches the state that temperature can reach, and the post-cure subsection below shows those states are different. The fitted figure is therefore an apparent activation energy for reaching the manufacturer’s specification rather than for a fixed chemical conversion, and the reason to trust it anyway is that it predicts the third entry in the same table.

The fit can be tested against a third point the datasheet also gives. Extrapolating from two hours at 130 degrees to 120 degrees with the dwell ratio above predicts a dwell of 3.02 hours, where 6,556 kelvin is $E_{a}/R$.

\[t_{\text{lo}} = 2 \exp\left[6{,}556 \left(\frac{1}{393.15} - \frac{1}{403.15}\right)\right] \approx 3.025, \qquad \frac{4}{3.025} - 1 \approx 0.322 \tag{24}\]

The datasheet recommends four [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. The recommendation is 32.2 percent longer than the kinetics require, and that difference is not an error in either. A cure schedule is not a kinetics prediction. It carries margin, and the question is where that margin goes.

For a facesheet the margin does not cover laminate thickness. Conduction across a laminate takes a Fourier time set by its thickness and its through-thickness diffusivity,

\[\tau = \frac{L^{2}}{\alpha_{\text{th}}} \tag{25}\]

and at an assumed through-thickness diffusivity of $3 \times 10^{-7}$ square metres a second, a representative value for a carbon epoxy laminate, even a six millimetre laminate equilibrates in two minutes, set against the four hour dwell of 14,400 seconds,

\[\tau = \frac{\left(6 \times 10^{-3}\right)^{2}}{3 \times 10^{-7}} = 120, \qquad \frac{\tau}{t} = \frac{120}{14{,}400} \approx 0.0083 \tag{26}\]

with $\tau$ in seconds [Thermal Diffusivity] [Krach and Advani 1996]. The same is not true of a thick laminate, where the cure cycle has to be designed around the conduction and sometimes around a cooling step in the middle of it [Kim and Lee 1997]. That is 0.83 percent of a four hour dwell, too small to count as a margin, and a diffusivity ten times smaller would still make it only 8.3 percent.

Where the margin does go is the oven. Convective heat transfer in forced turbulent flow follows a Dittus-Boelter form, and the Reynolds number is proportional to gas density at a fixed velocity and geometry, so the coefficient scales with pressure [Nusselt Number].

\[\mathrm{Nu} = C_{Nu}\,\mathrm{Re}^{0.8}\,\mathrm{Pr}^{1/3} \qquad\Longrightarrow\qquad \frac{h_{\text{autoclave}}}{h_{\text{oven}}} \sim \left(\frac{p_{\text{autoclave}}}{p_{\text{oven}}}\right)^{0.8} \tag{27}\]

At the same pressure ratio that governs consolidation, the coefficient rises by a factor of 4.93, falling to 3.31 if the exponent is taken as 0.6, an assumed lower end of the range correlations give.

\[\frac{h_{\text{autoclave}}}{h_{\text{oven}}} \sim 7.35^{0.8} \approx 4.93, \qquad 7.35^{0.6} \approx 3.31 \tag{28}\]

The experimental literature supports the direction if not the coefficient, autoclave pressure, temperature and the timing of vacuum application all showing up in measured laminate quality [Koushyar et al. 2011]. The autoclave’s pressure does two jobs at once. It closes voids and it moves heat, and a shop that gives up the first gives up the second in the same transaction.

Why the Post-Cure Is Not a Convenience

The datasheet requires that any part cured below 180 degrees be given a free-standing post-cure of two hours at that temperature [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials], and the reason is not that the low-temperature cure is merely slow. It is that the low-temperature cure cannot finish at all.

The glass transition of a curing thermoset rises as it reacts, and the DiBenedetto relation gives that rise in terms of the degree of cure [Glass Transition].

\[\frac{T_{g} - T_{g0}}{T_{g\infty} - T_{g0}} = \frac{\lambda_{D}\,\alpha}{1 - \left(1 - \lambda_{D}\right)\alpha} \tag{29}\]

When that glass transition overtakes the cure temperature the resin vitrifies, the molecules stop moving far enough to find each other, and the reaction slows by orders of magnitude. The cure stops at whatever conversion the temperature can hold. Setting $T_{g}$ equal to the cure temperature and inverting for the conversion gives the ceiling. The table below takes the fully cured glass transition at the datasheet’s 180 degrees, and takes an uncured glass transition of minus 20 degrees and a curvature parameter $\lambda_{D}$ of 0.5 as assumptions, because neither is published for this resin [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials].

\[\alpha_{\text{vit}} = \frac{f}{\lambda_{D} + \left(1 - \lambda_{D}\right) f} \qquad\qquad f = \frac{T_{\text{cure}} - T_{g0}}{T_{g\infty} - T_{g0}} \tag{30}\]

Cure temperature	Conversion it can reach	Glass transition there
80 C	0.667	80 C
120 C	0.824	120 C
130 C	0.857	130 C
180 C	1.000	180 C

A cure at 120 degrees can therefore reach 0.824 and no further, and a cure at 130 can reach 0.857. Only a cure at 180 reaches the end. The post-cure does more than develop the last few percent of a property, because it is the only step in which the reaction is thermodynamically permitted to complete, and the datasheet’s wet glass transition of 160 degrees after the post-cure demands a conversion of 0.947, which no lower temperature can supply [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. The 120 degree row and the wet glass transition work out as follows.

\[f = \frac{120 - \left(-20\right)}{180 - \left(-20\right)} = 0.70, \qquad \alpha_{\text{vit}} = \frac{0.70}{0.5 + 0.5 \times 0.70} \approx 0.824, \qquad \frac{0.90}{0.5 + 0.5 \times 0.90} \approx 0.947 \tag{31}\]

where 0.90 is the reduced value $f$ for 160 degrees.

Two of the three parameters in that relation are assumptions, so the sensitivity was computed. The fully cured glass transition is the datasheet’s 180 degrees [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. The uncured value and the curvature parameter are not published for this resin. Varying the uncured value over minus 40, minus 20 and zero degrees and $\lambda_{D}$ over 0.3, 0.5 and 0.7, a grid assumed here to be representative of such systems, moves the 120 degree ceiling between 0.741 and 0.899. The ceiling falls as either parameter rises, so the extremes sit at opposite corners of the grid.

\[\alpha_{\text{vit}} = \frac{120/180}{0.7 + 0.3 \times 120/180} \approx 0.741, \qquad \alpha_{\text{vit}} = \frac{160/220}{0.3 + 0.7 \times 160/220} \approx 0.899 \tag{32}\]

The first is an uncured value of zero with $\lambda_{D}$ of 0.7, and the second an uncured value of minus 40 degrees with $\lambda_{D}$ of 0.3. The number is assumption-dependent and the conclusion is not. At the post-cure temperature the conversion is exactly one for every combination in that grid, and every lower temperature is strictly below it, because vitrification is defined by the glass transition meeting the cure temperature and nothing else enters that definition.

This sharpens the article’s central tension into a mechanism. The phrase low-temperature curing in the registry entry does not describe a complete process. It describes the first half of a two-stage one, and the second stage runs at the temperature the first stage was chosen to avoid.

Now count the full cycle, post-cure included. The autoclave-only cure at 180 degrees needs no second stage, because it never vitrifies short of completion. Every dwell in the table below is the datasheet’s [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. For an initial cure $t_{\text{init}}$, a post-cure $t_{\text{post}}$ and the autoclave-only dwell $t_{\text{ac}}$, the last column is

\[\frac{t_{\text{init}} + t_{\text{post}}}{t_{\text{ac}}}, \qquad \frac{4 + 2}{2} = 3, \qquad \frac{20 + 2}{2} = 11 \tag{33}\]

for the 120 degree and 80 degree routes, with every dwell in hours.

Route	Initial cure	Post-cure	Total dwell	Against the autoclave
80 C vacuum bag oven	20 h at 80 C	2 h at 180 C	22 h	11 times
120 C vacuum bag oven	4 h at 120 C	2 h at 180 C	6 h	3 times
130 C vacuum bag oven	2 h at 130 C	2 h at 180 C	4 h	2 times
180 C autoclave only	2 h at 180 C	none	2 h	1 time

The low-temperature route the registry entry names costs three times the oven dwell of the route it replaces, and the lowest-temperature option costs eleven times. Whatever the time compression came from, it did not come from the cure.

Where the Compression Comes From

It came from not having to put the parts together, the conclusion the Composites Affordability Initiative had reached before the aeroplane existed [Market Trends, the Composites Affordability Initiative, Part I, CompositesWorld].

But the arithmetic of that saving, on this aeroplane, is smaller than it sounds. Thirty-six thousand fasteners were not installed [The Carbon Comet, Lockheed Martin]. Installing one in an airframe means drilling, reaming, deburring, cleaning, sealing, setting and inspecting, and drilling holes and installing fasteners is a major source of labour and rework in aircraft structure [Market Trends, the Composites Affordability Initiative, Part I, CompositesWorld]. No published touch time for that sequence on this airframe was found, so the table brackets it from two to ten minutes and the burdened rate from 100 to 200 dollars an hour.

Minutes a fastener	Burdened rate	Hours saved	Value	Share of the contract
2	100 dollars an hour	1,200	120,000 dollars	0.24 percent
5	150 dollars an hour	3,000	450,000 dollars	0.92 percent
10	200 dollars an hour	6,000	1,200,000 dollars	2.44 percent

Against a contract of 49,097,981 dollars, the fasteners that were never installed are worth between a quarter of one percent and two and a half percent. The contract is the cooperative agreement the Air Force Research Laboratory awarded Lockheed Martin on 20 April 2007, whose first phase covered the design and whose second covered fabrication and flight demonstration [X-55 Advanced Composite Cargo Aircraft, Program, GlobalSecurity.org]. The assumptions are stated openly, and the conclusion holds across their range, because the range spans a factor of ten and the answer stays small.

None of this suggests the saving is illusory. The question is where the saving lives. A fastener eliminated is worth its installation cost every time an aeroplane is built, so the saving is recurring and the demonstration is not.

Recurring cost falls with cumulative production under a progress ratio, in the form Wright wrote down for airframes in the 1930s [Experience Curve Effects] [Military Airframe Costs: The Effects of Advanced Materials and Manufacturing Processes].

\[C_{i} = C_{1}\,i^{b} \qquad\qquad b = \frac{\ln \varrho}{\ln 2} \tag{34}\]

At a progress ratio $\varrho$ of 0.90 the hundredth unit costs 0.497 of the first, and at 0.85 it costs 0.34. A simpler assembly costs less per aeroplane and also has fewer things left to learn about, a second-order effect the part-count literature reports and this article does not attempt to size [Apostolopoulos and Kassapoglou* 2002].

Solving for the length of the run turns the argument into a number. Asking how many aeroplanes the recurring saving must accumulate over before it repays what the demonstration cost gives

\[n_{\text{break-even}} = \frac{C_{\text{programme}}}{\Delta C_{\text{per aircraft}}} \tag{35}\]

Assumption	Saving an aeroplane	Aeroplanes to repay the programme
two minutes at 100 dollars	120,000 dollars	409
five minutes at 150 dollars	450,000 dollars	109
ten minutes at 200 dollars	1,200,000 dollars	41

Somewhere between forty and four hundred aeroplanes, and about a hundred on the middle assumption. Charging the saving against a declining learning curve rather than a flat one pushes the middle case to 210 aeroplanes, because the saving itself shrinks as the assembly gets cheaper to perform.

That is not the industrial break-even and is not offered as one. A production programme would weigh the saving against the non-recurring cost of its own tooling, qualification and facilities rather than against what a demonstrator cost, and this article has no figure for that. What the calculation gives is the scale of run over which a saving of this size becomes comparable to a cost of this size, the question that the registry entry’s word validate raises and cannot answer on one aeroplane.

Two hundred and seventy-nine C-17s were built before the line closed, and C-130J deliveries had passed five hundred by March 2022 [Boeing C-17 Globemaster III] [Lockheed Martin C-130J Super Hercules], so a run of that length is not a fanciful comparison for a military transport. But the X-55 was a run of one, and the tooling, the qualification and the first-article learning all fall on that single article [Lockheed Martin X-55]. The demonstrator is the worst possible case for the economics it was built to demonstrate, and the arithmetic puts the gap at roughly two orders of magnitude.

Dependent Systems

A unitised bonded structure depends on two things beyond the cure, the joint that replaces the fastener and the material that has to be laid before it expires. The first is the bondline, whose certification has in practice brought mechanical fasteners back as a second load path and a disbond arrest [AC 20-107B, Composite Aircraft Structure, Federal Aviation Administration] [Cheung and Lin 2009]. The second is the prepreg’s out life, which the datasheet fixes at twenty-one days and which bounds how large a part can be made in one piece [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. The donor airframe the new structure was grafted onto, with its wing, engines, landing gear, avionics and forward fuselage left as they were, is described under Programme Origin.

Some of the Fasteners Come Back

The arithmetic above assumed the eliminated fasteners stay eliminated, and the certification literature finds that they do not.

The trouble with a bonded joint is not weakness but the impossibility of demonstrating its strength by looking at it. A fastener can be counted, torqued and inspected. A bondline can be perfect and a bondline can be a kissing bond, in which the surfaces touch and do not adhere, and the two can be difficult to tell apart by any method that does not load the joint [Jonas and Aldag 1987] [Tsai et al. 1999] [Kan et al. 1997].

The regulator’s answer is to make the joint carry limit load with the largest disbond it can tolerate, and to require that anything larger be stopped by a design feature, for any bonded joint whose failure would be catastrophic, unless every production article is proof tested or a repeatable and reliable inspection of joint strength exists [AC 20-107B, Composite Aircraft Structure, Federal Aviation Administration]. In practice the design feature of choice has been mechanical fasteners driven through the bondline, which act both as a second load path and as a means of stopping a disbond once it starts [Cheung and Lin 2009] [Cheung and Lin 2012] [Baker 2010].

That is a fastener put back into a structure whose justification was taking fasteners out, and it costs more than the fastener, because it also gives up the joint stiffness and the fatigue performance that made bonding attractive.

The size of the giveback is not something this article can compute, since the number of arrest fasteners a certification basis demands depends on the structure, the load path and the authority. What can be said is the direction, and that the research effort aimed at avoiding the giveback is substantial and current. An Air Force Research Laboratory programme with Northrop Grumman has been working since at least 2021 on fail-safe features for bonded unitised structure that are not fasteners, and a parallel effort has pursued joints with inherent disbond arrest capability [Clay et al. 2021] [Bartley-Cho and Muraliraj 2022] [Action and Goyal 2022] [Bartley-Cho and Nickerson 2019].

A research programme is evidence that a problem is unsolved. The X-55 flew in 2009 and that laboratory effort was still publishing in 2023 [Bartley-Cho et al. 2023], so the certification of a bonded unitised airframe remained open fourteen years later, a fact about the technology the demonstrator could not have established and did not claim to.

The Clock That Runs on the Material

A prepreg is a reacting system from the moment it leaves the freezer, and the datasheet gives it twenty-one days of out life and ten days of tack life at room temperature [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials]. Out life is cumulative and nothing resets it.

The consequence for a large unitised part is direct, and this article judges it the strongest argument available. Unitisation means making parts bigger. A bigger part takes longer to lay up. The material degrades throughout.

The tests already quoted make that concrete. The same prepreg family at thirty-five days out of the freezer had lost so much tack that its plies no longer held to a vertical tool, showed 8.3 percent voids where the fresh material showed 0.1 percent, and returned short beam shear strengths at about four fifths of its peers [Sutter et al. 2010]. That is a rise from a tenth of one percent to more than eight percent for one interval of shop-floor time, and every one of the four fresh systems in that study measured below 2 percent, and the effect on the resin’s viscosity and gel behaviour is measurable long before that [Kim et al. 2014b] [Kim et al. 2014a].

Computing the rate the out-life demands attaches a margin to the claim, where comparing areas would not. One fuselage half is half a cylinder, so its surface follows from the two dimensions the record gives.

\[A_{\text{skin}} = \frac{\pi D L}{2} \tag{36}\]

For skins 19.8 metres long over a nine foot diameter that is 85 square metres [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld] [Lockheed Martin X-55]. Laying $N$ plies over it inside the out-life demands a sustained rate of

\[\dot{A} = \frac{N\,A_{\text{skin}}}{t_{\text{out}}\,h_{\text{day}}} \tag{37}\]

Facesheet plies	Working hours a day	Ply area	Rate needed inside the out-life
12	8	1,024 square metres	6.09 square metres an hour
12	16	1,024 square metres	3.05 square metres an hour
24	16	2,048 square metres	6.09 square metres an hour

A twelve-ply facesheet on one half-shell is roughly 1,024 square metres of ply to place, and fitting that inside the out-life window at one shift a day requires 6.09 square metres an hour sustained, every working hour, for three weeks. That is a crew size rather than a schedule, and the crew size is being set by chemistry.

Turned around to give the part instead of the rate, the same relation states the constraint more sharply. A shop that can sustain a given rate can lay at most

\[N_{\text{max}} = \frac{\dot{A}\,t_{\text{out}}\,h_{\text{day}}}{A_{\text{skin}}} \tag{38}\]

plies on a shell of that size before the material is out of time.

Sustained rate	Working hours a day	Plies the out-life permits
2 square metres an hour	8	4
5 square metres an hour	8	10
5 square metres an hour	16	20
10 square metres an hour	16	39

A ceiling of ten to twenty plies is not a comfortable margin over what a fuselage skin needs, and it falls in direct proportion to the area of whatever the shop decides to make in one piece. This number bounds unitisation from above, and unlike tooling or handling it cannot be bought around.

A programme whose whole argument was fewer and larger parts still built its fuselage in eight pieces [Out-of-Autoclave Prepregs, Hype or Revolution, CompositesWorld]. The record does not say why, and a large structure is subdivided for tooling, for handling, for the tail and for the frames as readily as for anything else. What can be said is that unitisation has an optimum and it is not infinity, and that out-life is one of the bounds on it, and the only one of them that no tooling change can relax. The programme’s own manufacturing engineer recorded the same bound as a lesson, that longer prepreg out-time would be desirable and that fibre placement of slit prepreg had become necessary to make large structures within the out-time the material allows [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld].

The Flight Test Record

The public flight test record of the X-55 is short, and most of what it holds is a pair of dates. The aeroplane first flew on 2 June 2009, against a first flight the broad agency announcement had required for October 2008 [Lockheed Martin Conducts Successful Flight of AFRL’s Advanced Composite Cargo Aircraft] [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld]. Phase III, awarded on 17 September 2009, was to expand the flight envelope and characterise the structure [X-55 Advanced Composite Cargo Aircraft, Program, GlobalSecurity.org], and 15 to 20 flights were expected over the programme [Lockheed Martin X-55]. No primary record consulted gives the number of flights completed, and no public dataset of the loads the instrumented structure measured turned up. The record therefore establishes that the structure flew and carried its loads, and says nothing numerical about how it behaved while doing so.

The Half of the Charter That Failed

The programme’s dates are the measurement.

Event	Date
Broad agency announcement issued	January 2007
Cooperative agreement awarded to Lockheed Martin	20 April 2007
Flight demonstrator due under Phase 2	30 September 2008
First flight required by the announcement	October 2008
First flight achieved	2 June 2009

Twelve months were asked for the build and about twenty were taken, an overrun of roughly two thirds. The announcement gave the second phase, fabrication and flight, a twelve month period of performance, and the manufacturer records the aeroplane as built and flown twenty months after the go-ahead [X-55 Advanced Composite Cargo Aircraft, Program, GlobalSecurity.org] [The Carbon Comet, Lockheed Martin]. The sources do not agree on the size of the overrun, and both are stated here. By the dates, the first flight came eight months after the 30 September 2008 deadline for the demonstrator and seven to eight months after the October 2008 date in the announcement [X-55 Advanced Composite Cargo Aircraft, Program, GlobalSecurity.org] [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld] [Lockheed Martin Conducts Successful Flight of AFRL’s Advanced Composite Cargo Aircraft]. The programme’s manufacturing engineer gives the first flight as May 2009, nine months later than planned, and a second trade-press account records it as seven months past the deadline and on budget [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld] [Out-of-Autoclave Prepregs, Hype or Revolution, CompositesWorld]. The overrun is therefore between seven and nine months, by source, and the manufacturer’s press release fixes the date of the flight itself as 2 June.

The cause is the part that matters. The first flight was expected in the winter of 2008 and 2009, and the schedule slipped because the skin on the lower fuselage did not bond satisfactorily. A second fuselage had to be built [Lockheed Martin X-55].

An aeroplane designated to validate extreme time compression in airframe manufacture lost the better part of a year to a defect in the manufacturing process it existed to validate. That is no criticism of the programme, since finding such defects is what a demonstrator is for. It is an observation about what the demonstrator demonstrated, and the observation is that the cost half of the charter survived and the time half did not.

Which half survived needs stating precisely. The cost claim is that the aeroplane was built at half the estimated cost of a conventional design of the same size [The Carbon Comet, Lockheed Martin]. That is a comparison against an estimate. No metallic aft fuselage for this aeroplane was ever built to compare it with, and no such aeroplane existed to be estimated except on paper. The schedule, by contrast, was compared against a date, and a date is an observation.

What Followed

Phase III was awarded on 17 September 2009 to expand the envelope and characterise the structure, with the aeroplane carrying more than 600 sensors and accelerometers to measure the stresses on it [X-55 Advanced Composite Cargo Aircraft, Program, GlobalSecurity.org], and 15 to 20 flights were expected [Lockheed Martin X-55]. The aeroplane is now on display at the Joe Davies Heritage Airpark in Palmdale, a few miles from the building it was made in [Joe Davies Heritage Airpark].

No second X-55 was built and none was intended [Lockheed Martin X-55]. The technology went where a technology goes when it works, which is into other people’s programmes and out of the public record.

Comparison With Ground Prediction

Three predictions were made on the ground before the X-55 flew, and only one of them can be set beside an observation.

The schedule is the one that can. The broad agency announcement of January 2007 required a first flight in October 2008, and the aeroplane first flew on 2 June 2009, an overrun of between seven and nine months by source after the skin on the lower fuselage did not bond satisfactorily and a second fuselage had to be built [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld] [Lockheed Martin X-55]. The Flight Test Record argues that comparison under The Half of the Charter That Failed. It is a ground prediction tested on the ground, because the defect that moved the date was found in manufacture and not in flight.

The cost is the one that cannot. The claim that the aeroplane was built at half the estimated cost of a conventional design of the same size sets the aeroplane beside an estimate [The Carbon Comet, Lockheed Martin]. No metallic aft fuselage for this aeroplane was ever built, so there is no outcome to set beside the prediction, and the recurring saving the registry entry names exists only across a production run that never took place.

The structure is the one flight should have answered, and the answer is not public. The aeroplane carried more than 600 sensors and accelerometers to measure the stresses on its structure, and its later flights were to validate its predicted structural performance, the comparison between structural prediction and flight that a demonstrator of this kind is equipped to make [X-55 Advanced Composite Cargo Aircraft, Program, GlobalSecurity.org] [Lockheed Martin Conducts Successful Flight of AFRL’s Advanced Composite Cargo Aircraft]. This article found no public dataset of those loads, so whether the bonded fuselage behaved as predicted cannot be stated here beyond the fact that it flew. The predictions this article makes, from the consolidation pressure at Air Force Plant 42 to the vitrification ceiling and the break-even run, are computed from published constants and are not tested against any measurement of this aeroplane.

What the Data Changed

The usual argument for leaving the autoclave does not hold at this scale. That argument holds that an aeroplane leaves the autoclave because no autoclave is large enough. The pressure vessel scaling gives a shell of 18.4 tonnes for a vessel that would take the part, about a tenth of the launch vehicle case. The size argument is real at launch vehicle scale and false at this one, and the reasons the trade press gives are capital and operating cost, tooling and a factory without a single autoclave queue, with cycle time cited as a risk rather than a gain.

A void fraction does not fall in simple proportion to the pressure. Dividing a void fraction by a pressure ratio ignores that the laminate shrinks along with the void, and the full relation leaves 1.22 percent after a full autoclave and needs a pressure ratio of 8.96 to reach 1 percent, as derived under What Has to Replace the Pressure. Both numbers put the target beyond what an autoclave can reach by squeezing.

The activation energy was not looked up. It was fitted to two lines of a datasheet table, and the value it returns agrees with the published range for this chemistry, and predicts a third entry in the same table to within the margin a process specification would be expected to carry.

Nor was the schedule read from a narrative. Both the plan and the outcome are dates in the public record.

The datasheet’s cure margin is not about laminate thickness, and the Fourier time shows it. A six millimetre facesheet equilibrates in two minutes, which is 0.83 percent of a four hour dwell. The margin is about the oven and the tool, and putting a number on the oven shows the autoclave’s pressure buying a factor of 4.93 in convective heat transfer as well as its factor of 7.35 in consolidation, both worked in the sizing above. A comparison that counts only the consolidation undercounts what the autoclave supplies.

Gas transport through the dry tows is a contest between two fluids. Air and resin move through the same channels with viscosities a factor of 540,541 apart, so evacuation is fast and sealing is slow, and four hours of vacuum would clear 12.1 metres of dry tow, by the Darcy sweep time derived earlier. Path length does not constrain the process. The race is whether the channels are still open, a question about out-time, so the void mechanism and the out-life argument form a single argument.

The certification literature supplies a documented counter-argument to this article’s cost claim. The fastener arithmetic assumes the eliminated fasteners stay eliminated. Certifying a bonded primary structure has in practice meant putting mechanical fasteners back through the bondline as a second load path that also arrests a disbond, a giveback the public record does not size. It bears on the article’s central number, so it receives a full subsection, Some of the Fasteners Come Back.

The recurring saving also has a length of run attached to it. Dividing the programme cost by the recurring saving puts the break-even between 41 and 409 aeroplanes and at 109 on the middle assumption, which turns the claim that the saving exists only on a long production run into a number.

The Contemporary Literature

Cluster	Records
The structure itself, and the qualification it has to pass	1,050
Bonding, which is how a unitised structure is joined	910
Curing a thermoset, which is where the time actually goes	765
Laying the material down, and the clock that runs while you do	527
Seeing inside, because the acceptance criterion is an inspection	340
The cost of building it, which is the thing being validated	324
Consolidating without a pressure vessel, which is the whole premise	276
The tool, and why a cured part is not the shape it was cured on	233
Voids, gas transport and the pressure that is not there	219
The laminate as a material, its strength, impact and durability	73
Drilling, machining and fastening a laminate	24
The atmosphere, which bounds what a vacuum bag can do	19
The aeroplane and the programmes around it	13
Other work on composite materials, processing and structures	30
Total	4,803

The structure itself, and the qualification it has to pass

The largest cluster, and it is the one an X-Planes reader expects. Composite fuselages, wing boxes, stiffened panels, sandwich construction, damage tolerance, compression after impact and the building-block approach by which such a structure is qualified. The X-55’s aft fuselage belongs here and contributed almost nothing to it, because a demonstrator expected to fly fifteen to twenty times generates a designation and not a literature [Flansburg and Engelstad 2013].

1,050 records. 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Bonding, which is how a unitised structure is joined

The second largest cluster, and its size is the argument. Adhesive joints, co-curing and co-bonding, bondline quality, disbond, the double cantilever beam and interlaminar fracture. A unitised structure is one whose parts have been replaced by joints that cannot be inspected by looking at them, so the discipline that decides whether unitisation is safe is adhesion science rather than structural analysis [Kinloch, Adhesion and adhesives].

910 records. 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Curing a thermoset, which is where the time actually goes

The third largest cluster and the one this article computes in. Cure kinetics, activation energy, the degree of cure, the glass transition, vitrification, calorimetry and the cycle design built on them. The registry entry’s phrase low-temperature is a claim about this shelf, and this shelf is where the price of that choice is set [Kratz et al. 2012].

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A], [Kim and Lee 1997], [Thomas et al. 1997], [Thomas et al], [Thostenson and Chou 2001], [Tifkitsis et al. 2023], [Timmerman et al. 2003], [Tollens and Lee 1993], [Tong and Appleby-Hougham 1986], [Toughened Thermoset Resin Matrix 2015], [Tracy and Totaro 1992], [Trends in Thermoset Resin 1993], [Tucci et al. 2024], [Tungare et al. 1988], [Tye 1994], [Tyler et al. 2009], [Hudson et al], [Um et al. 2002b], [Um et al. 2002a], [Ungarish et al. 1990], [Urbaczewski et al. 1990], [Urbaniak 2011], [Urbaniak 2018], [Urbaniak and Grudzinski 2007a], [Urbaniak and Grudzinski 2007b], [Vafayan et al. 2013], [Van Assche et al. 1995], [Van Assche et al. 1996], [Van Assche et al. 1997], [Van Assche et al. 2000], [Van Dijk et al. 1992], [Varley et al. 1996], [Vázquez-Torres 2014], [Verchere et al. 1990], [Vergnaud and Bouzon 1992b], [Vergnaud and Bouzon 1992a], [Vergnaud and Bouzon 1992d], [Vergnaud and Bouzon 1992c], [Vinnik and Roznyatovsky 2003], [Vinnik and Roznyatovsky 2006], [Vlassopoulos et al. 1998], [Vo et al. 2013], [Vora et al. 1996], [Voß and Haupt 2021], [Voß and Vallée 2023], [Voto et al. 2021], [Vroon and van Hoorn 2023], [Vyazovkin and Sbirrazzuoli 1996], [Waenawae et al. 2016], [Waller et al. 2022], [Wang et al. 2022b], [Wang et al. 2026g], [Wang and Ediger 2000], [Wang et al. 2023b], [Wang et al. 1997a], [Wang and Kwag 2006], [Wang et al. 2024c], [Wang et al. 2021a], [Wang et al. 2020d], [Wang and Storm 2003], [Wang et al. 2022e], [Watkins et al. 1995], [Wazalwar and Raichur 2021], [White and Hahn 1990], [White and Hahn 1993], [Wiedemann et al. 2025], [Willard 1972], [Williams et al. 1984], [Wingard and Beatty 1990], [Winter 2017], [Wisanrakkit and Gillham 1990], [Witman and Wang 2006], [Wu et al. 2014], [Wu et al. 2020], [Wu et al. 2025], [Wu et al. 2016], [Xiao-jing et al. 2013], [Xie et al. 2020], [Xie et al. 2004], [Xie et al. 2009], [Xu et al. 2003], [Xu and Schlup 1996], [Xu and Schlup 1998], [Xu et al. 2021], [Xu and Zhang 2012], [Xue and Zhang 2014], [Yamanaka et al. 2023], [Yamini et al. 2019], [Yan 2006], [Yang et al. 2009], [Yang et al. 2024a], [Yang et al. 2024b], [Yang et al. 2021c], [Yang et al. 2018b], [Yang et al. 2023a], [Yangyang et al. 2020], [Yi et al. 1995], [Yi et al. 1996], [Yi and Hilton 1998], [Alpha Technologies et al. 2025], [Yoon et al. 2019], [Yoozbashizadeh et al. 2018], [Young 1995a], [Young 1996a], [Yousefi et al. 1997], [Yu et al. 2005], [Yu et al. 2006], [Yuan et al. 2021a], [Zade et al. 2023], [Zade et al. 2021], [Zappino et al. 2024], [Zeng et al. 2010], [Zhang et al. 2018b], [Zhang et al. 2012], [Zhang et al. 2026b], [Zhang and Vyazovkin 2007], [Zhang et al. 2010a], [Zhang et al. 2021a], [Zhang et al. 2022b], [Zhang et al. 2022a], [Zhao et al. 2001], [Zhao and Hu 2010], [Zhao et al. 2020b], [Zhong and Guo 1998], [Zhou and Sancaktar], [Zhou et al. 2011], [Zhu et al. 2025a], [Zhu et al. 2026a], [Zukas 1994], [Zvetkov et al. 2008].

Laying the material down, and the clock that runs while you do

Placement, and the material’s own clock. Automated fibre placement, tape laying, hand layup, infusion, resin transfer moulding, and the out-life and tack life that bound how long any of it may take. The clock is the half that gets forgotten, and it is the constraint this article argues actually limits how large a unitised part can be [Grunenfelder et al. 2013].

527 records. [Aaboud et al. 2017], [Abdou et al. 2016], [Adali 1995], [Advanced Composites Prepreg], [Advanced Composites Prepreg], [Advanced Composites Prepreg], [Advanced Composites Prepreg], [Aerospace Material Specification Glass], [Air et al. 2022], [Air et al. 2023], [Akbar et al. 2008], [Jonathan et al. 2021], [Al-Hamdan et al. 1995], [Ali and Yasko 2024], [Al Mahmood 2017], [Alms and Brown 2017], [Alotaibi et al. 2022], [Alotaibi et al. 2024], [Al-saadi et al. 2019], [Amaoui and Hattabi 2023], [An et al. 2017], [Anderson and Grant 1991], [Anderson and Grant 1992], [Andre et al. 2016], [Antonelli and Farina 1999], [Archodoulaki et al. 2015], [Aretxabaleta et al. 2022], [Arian Nik et al. 2014], [Ariyatum et al. 2006], [Aromatic Polyamide Fiber-Based Composite 1988], [Arsenyeva et al. 2024], [Automated Preform Manufacture 1990], [Aveiga García], [Bahar 2022d], [Bahar 2022b], [Bahar 2022a], [Bahar 2022c], [Bakhshi and Hojjati 2018], [Balaga et al. 2023], [Balokas et al. 2023], [Banks-Sills et al. 2023], [Barcenas et al. 2025], [Barcenas et al. 2023], [Bard et al. 2018], [Barjasteh et al. 2018], [Béchet et al. 2003], [BÉChet et al. 2020], [Belhaj et al. 2021], [Bhatt et al. 2021], [Bickerton et al. 2013], [Bickerton and Kelly 2012], [Björnsson 2017], [Björnsson et al. 2013], [Bloechle 1982], [Brasington et al. 2020], [Budelmann et al. 2020], [Buhagiar et al. 2026], [Bur and Joyot 2017], [Bur et al. 2018], [D30 Committee 2008a], [Carbon Fiber Fabric Repair], [Carbon Fiber Fabric Repair], [Carbon Fiber and Fiberglass], [Carbon Fiber Fabric Repair], [Carbon Fiber Fabric Repair], [Carbon Fiber Fabric Repair], [Carbon Fiber Fabric Repair], [Carbon Fiber Fabric and], [Carbon Fiber Fabric and], [Carbon Fiber Fabric and], [Carbon Fiber Fabric and], [Carbon Fiber Fabric and], [Castro et al. 2021], [Cha and Yoon 2023], [Chadwick et al. 2019], [Chakraborty et al. 2026], [Chan and Morgan 1993], [Chang 2003], [Chang 2015], [Chang 2019], [Chen et al. 2014b], [Chen et al. 2021e], [Chen et al. 2021b], [Chen et al. 2023a], [Chen et al. 2024], [Cheng et al. 2026], [Chmielewski et al. 1993], [Comas-Cardona et al. 2005], [Composite Fuselage Frames Manufactured 2004], [Compression Molding Prepreg 2020], [Connell et al. 2005], [Corman and Luthra 2018], [William et al. 2025], [Dalla Libera Junior et al. 2020], [Jegley et al], [Deignan et al. 2017], [Deng 2025], [Denos et al. 2018], [Derakhshani Dastjerdi et al. 2023], [Desplentere et al. 2009], [Developments in Resin Transfer 1991], [Dickson and Dowling 2019], [Dillon 2005], [Dimitrovová], [Di Pietro and Compston 2010], [Dong 2008], [Donough et al. 2022], [Duann et al. 2005], [Endruweit 2023], [Epoxy Prepreg Solution 2019], [Epoxy Resin Composition 1992], [Fang et al. 2020], [Fauster et al. 2018], [Ferguson et al. 2019], [Fernández-León et al. 2026], [Luz et al. 2012], [Fierro et al. 2019], [Fink et al. 1998], [Fire Retardant Prepreg Resin 2015], [Flanagan et al. 2025], [Flemming et al. 1999], [Foley and Gillespie 2005], [Fong et al. 2015], [Frishfelds and Lundström 2011], [Ikonomopoulos and Marchetti 1999], [Gaikwad et al. 2025], [Gain et al. 2022], [Galvez-Hernandez et al. 2021], [Gangas et al. 2026], [Garate et al. 2022], [Garofalo and Walczyk 2021], [Gascons et al. 2011], [Gawryluk and Teter 2023], [Ghamisi et al. 2024], [Ghayour et al. 2023], [Ghayour et al. 2020], [Ghose et al. 2011], [Gintert 1995], [Goodman and Loos 1990], [Grant et al. 2025], [Graphite Fiber Tape And], [Gu and Liang 2004], [Gu et al. 2015], [Gupta and Kelly 2013], [Gutiérrez and Morales 2000], [Halpin et al. 1983], [Hanzlik and Yilmazoglu 2024], [Hawley 1993], [Hayes 1985], [Hayes et al. 2000], [Hayes et al. 1996], [Hayes and Seferis 1997], [Hayes and Seferis 1998], [Hayes and Seferis 1999], [Hayward and Harris 1990], [He et al. 2024b], [Heller et al. 2022], [Henne et al. 2004], [Henz et al. 2002], [Hickman and Williams 1989], [Hill 1990], [Holmes and Larry R. 2013], [Hong et al. 2026], [Hongquan et al. 2025], [Hopmann et al. 2017], [Hosseini et al. 2026], [Hot-Melt Prepreg Tow Apparatus 1993], [Houen], [Hsiao et al. 2022], [Hu 2008], [Huang et al. 2026a], [Humphry], [Hutchinson et al. 2014], [Ikari and Tanaka 2019], [Imbert 2015], [Improved Resin Transfer Moulding 1998], [Ishida et al. 2024], [Jamora et al. 2026], [Jiang and Huang 2011], [Joesbury et al. 2026], [Johnson et al. 1998], [Kadiyala et al. 2022], [Kadiyala et al. 2021], [Kang et al. 2000], [Karbuz et al. 2024], [Kärger and Kling 2013], [Kavitha and Vijayan 2024], [Kaynak and Kas 2006], [Kazmi et al. 2018], [Kelkar et al. 1999], [Keller et al. 2018], [Kendall et al. 1992], [Keramati et al. 2021], [Kermenov et al. 2025], [Khan et al. 2011], [Khosravi 2002], [Kim and Chang 2019], [Kim and Daniel 2003], [Kim et al. 1995a], [King et al. 2025], [Kirk et al. 2026], [Kiuna et al. 2002], [Kobayashi and Tanaka 2012], [Kondo and Matsumoto 2017], [Kong and Zhang 2022], [Kosgi et al. 2023], [Kratz et al. 2023], [Kravchenko et al. 2019], [Kruse et al. 2025], [Kumar and Kumar 2022], [Kumar and Shukla 2014], [Kuo and Chen 2020], [Kuppusamy 2018a], [Kuppusamy 2018b], [Kuppusamy and Neogi 2017], [Kuppusamy et al. 2021], [Lam et al. 2000], [Laminate and Prepreg Selection 2002], [Larson and Drzal 1994], [Laurenzi and Marchetti 2012], [Lee et al. 2022], [Lee et al. 2023a], [Lee et al. 2023b], [Lei 2018], [Lekakou and Bader 1998], [Lekakou et al. 2007], [Li et al. 2022a], [Li et al. 2015], [Li et al. 2025d], [Li et al. 2022b], [Li et al. 2022e], [Li et al. 2026c], [Lim et al. 2022], [Liquid Composite Molding Simulation 2002], [Liu and Devarajan 2022], [Liu et al. 2023], [Liu and Wang 2026], [Lomov and Abaimov 2022], [Long et al. 1998], [Loos et al. 1996], [Lovejoy et al. 2023], [Luinge et al. 2019], [Lukaszewicz and Potter 2011], [Lukaszewicz et al. 2012], [Luthy and Ermanni 2001], [Luthy and Ermanni 2002], [Maenz et al. 2014], [Maffezzoli et al. 1990], [Mal et al. 1998], [Malhan et al. 2020], [Malhan et al. 2018], [Malhan et al. 2019], [Malhan et al. 2021], [Mannino et al. 2017], [Marioli-Riga 2003], [Markus 1992], [Markus and Palmer 1991], [Markus et al. 1993], [Marsh 2012], [Martin et al. 1997], [Mather 2005], [Matsuzaki and Shiota 2017], [May 1995], [McArthur et al. 2024a], [McArthur et al. 2025], [McArthur et al. 2024b], [McHugh and Stark 2016], [Meister et al. 2021], [Mendikute et al. 2021], [Method for the preparation 1996], [Method of Fabricating Fibre 1990], [Method of Fabricating Fibre 1992], [Method of Resin Transfer 1993], [Method of Making Composite 1994], [Meyer et al. 2023], [Milenkovic et al. 2021], [Mills 2026], [Mills et al. 1974], [Mills and Dauksys 1973], [Minakuchi et al. 2020], [Mishra et al. 2019], [Mohamad et al. 2015], [Möllers et al. 2023], [Moradi et al. 2024], [Mori et al. 2026], [Muralidharan and Summerscales 2011], [Murray et al. 2020], [Mussatayev et al. 2025], [Naffakh et al. 2006], [Nakagawa et al. 2022], [Nakata et al. 2018], [Nana et al. 2025], [Nancarrow et al. 2024], [Nash et al. 1980], [Neft et al. 2002], [Newcomb 2019], [Ngo et al. 2017], [Ngo et al. 2018], [Nguyen et al. 2019], [Nguyen-Thuc and Maazouz 2004], [Nhuapeng et al. 2008], [Nilakantan and Nutt 2015], [Noevere et al. 2019], [Ntourmas et al. 2023], [null], [null], [null], [Obertscheider and Fauster 2023], [Odagiri et al. 1996], [Odiyi et al. 2022], [Oksman 2001], [O’Leary et al. 2022], [Xiang et al. 2024], [Oromiehie et al. 2021], [Oromiehie et al. 2022], [Ortiz de Mendibil et al. 2016], [Owen et al. 1990], [Ozaydin Ince et al. 2024], [Palardy et al. 2012], [Pansart 2013], [Park et al. 2003a], [Park et al. 2017], [Patz 1981], [Peltonen and Järvelä 1992], [Peltonen et al. 1992], [Peng et al. 2023], [Pereira et al. 2026], [Perret et al. 2011b], [Pillai and Advani 1998], [Pitchumani 2000], [Polnikorn 2024], [Polowick], [Poly amide-Imide Prepreg 1991], [Polyimide Composition and Prepreg 1991], [Popham 2019], [Potter 1997a], [Potter 1997e], [Potter 1997g], [Potter 1997d], [Potter 1997i], [Potter 1997j], [Potter 1997c], [Potter 1997h], [Potter 1999], [Potter 2023], [Prakash et al. 2025], [Preforms for Resin Transfer 1989], [Prepreg for Making 1985], [Prepreg Material Having Increased 1984], [Prince and Zhao 2026], [Process for Producing Inorganic 1995], [Processing of High-Reactivity Epoxy 1975], [Property and Processing Performance 1989], [Prototype Aircraft Access Door 1987], [Qian 2024], [Qin et al. 2022], [Qu et al. 2021], [Quadrini et al. 2025], [Quagliato et al. 2019], [Quintana et al. 2023], [Räckers 1998], [Harik et al], [Harik et al], [Raps et al. 2022], [Raqibul Hasan Prince and Zhao 2026], [Ratle et al. 2009], [Rempe 1996], [Resin Technology Can Cure 2017], [Resin Transfer Moulding Process 1993], [Resin Transfer Moulding 1994], [Resin Transfer Molding 1995], [Kruckenberg and Paton 1998], [朱 2022], [Robertson 1988], [Robinson and Kosmatka 2008], [Rudd 2001], [Rudd et al. 1995], [Rudd et al. 1997a], [Rudd et al. 1997b], [Rudd et al. 1990], [Rudd et al. 1999], [Rutt et al. 2019], [Rydarowski and Koziol 2014], [Saad et al. 2011b], [Saha et al. 2026], [Sandberg et al. 2019], [Sanjana et al. 1981], [Scarponi et al. 2009], [Scheirer], [Schenke and Ehlers 2016], [Schubert 2009], [Schuster et al. 2014], [Schuster et al. 2020], [Sebastian et al. 2019], [Sebastian et al. 2021], [Selyugin 2021], [Seong et al. 2017], [Sevkat and Brahimi 2011], [Shah and Schubel 2015], [Shahid et al. 1995], [Shembekar et al. 2020], [Shevtsov et al. 2017], [Shevtsov et al. 2021b], [Shevtsov et al. 2021a], [Shiino et al. 2021], [Shimamoto et al. 2016], [Shojaei 2006b], [Shuvo 2019], [Simacek et al. 2008], [Simulating Liquid Moulding 2002], [Single Tow Prepreg 1990], [Sirtautas et al. 2014], [Slavnov et al. 2024], [Smith et al. 2020], [Smith and Mattavi 2001], [Smith et al. 2016], [Spurgeon 2005], [Stark 2013], [Stratton 1998], [Su et al. 2025], [Suemasu et al. 2021], [Suemasu et al. 2023], [Summerscales 1993], [Summerscales and Searle 2005], [Sun], [Sun et al. 2017], [Sun et al. 2021], [Sun et al. 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1996b], [Yu et al. 2020], [Zacherl et al. 2024], [Zade and Kuppusamy 2019], [Zade and Kuppusamy 2020], [Zade and Kuppusamy 2021], [Zenker and Schön 2019], [Zhang and Kim 2022], [Zhang et al. 2020d], [Zhao et al. 2021a], [Zhao et al. 2023], [Zhao et al. 2021b], [Zhao et al. 2025b], [Zhao et al. 2016], [Zhu et al. 2022], [Zhu et al. 2023a], [Zingraff et al. 2005].

Seeing inside, because the acceptance criterion is an inspection

What a bonded structure is accepted on. Ultrasonic inspection, thermography, tomography, cure monitoring and structural health monitoring. A fastener can be counted and a bondline cannot, so removing thirty-six thousand fasteners moves the burden of proof from an assembly record onto an inspection.

340 records. [A Model of Passive 1982], [A real-time ultrasonic imaging 1990], [A Real-Time Ultrasonic Imaging 1994], [Abdel-Latif 2009], [Abraham and McIlhagger 1998], [Acoustographic nondestructive evaluation of 1990], [Aerospace series. Qualification and], [Afromowitz and Lam 1989], [Ahmed et al. 2025], [Aldrin 2002], [An et al. 2021], [An Experimental Study 1998], [An ultrasonic system for 1994], [Anderson et al. 1988], [Aranguren et al. 2020], [Attenuation in Ultrasonic Inspection 1967], [Awad Hallosh Khidhir and Qussay Younis Hamid 2015], [Bahadori et al. 2021], [Bahr and Rosengreen 1985], [Bail 2008], [Bakis and Reifsnider 1988], [Banerjee et al. 2007], [Bangalore], [Bar-Cohen and Chimenti 1987], [Beere 2010], [Benammar et al. 2010], [Blue 1988], [Boateng et al. 2019], [Boll et al. 2014], [Bond 2019], [Bond 2021], [Bond 2022], [Bond 2025], [Bornemann et al. 2024], [Boyd et al. 1982], [Breede et al. 2015], [Brown and Pears 1974], [Buchinger and Sharif Khodaei 2021], [Buddala et al. 2024], [Bunget et al. 2014], [Capitani et al. 2011], [Chailleux et al. 1999], [Chang and Ihn 2003], [Chang et al. 1974], [Chattopadhyay 2016], [Chen et al. 1998b], [Chen et al. 2022b], [Chimenti 1991], [Chimenti and Fortunko 1994], [Choi et al. 2003], [Composite Honeycomb NDI Reference], [Composite Repair Ndt/Ndi Handbook], [Condon and Cook 1983], [Copley 1987], [Crosby and Fernando 1999], [Cusano et al. 2000], [Dahmen 2025], [Dahmen 2026], [Datta et al. 2026], [Datta et al. 1996], [Day et al. 1989], [De Rosset 2003], [Desgrosseilliers et al. 2014], [Development of an Automated 1994], [Dielectric Cure Monitoring 1990], [Dielectric Cure Monitoring 2008], [Dielectric measurements for cure 1990], [Djiauw 1981], [Dorbath et al. 2023], [Druy et al. 1989], [Dugmore et al. 2002], [Duke 1983], [Duke et al. 1996], [Dvořák et al. 2013], [Eddazi and Belattar 2017], [Eder and Rose 1994], [Elburn and Toonen 2012], [Elenchezhian et al. 2022], [Ensminger and Bond 2011], [Ensminger and Bond 2023], [Ermolenko 2025], [Ermolenko et al. 2024], [Evaluation of Nondestructive Evaluation 1989], [Evaluation of bond testing 1990], [Evaluation of Bond Testing 1994], [Fein 1998], [Feith and Lawrie 1963], [Fomitchov et al. 1999], [Franieck et al. 2021b], [Frey et al. 1996], [Gammell 1993], [Giordano et al. 2000], [Glushkov et al. 2015], [Godı́nez 2001], [Gomes and Kota 1992], [Green 1995], [Gregory and Juarez 2018], [Groh et al. 2018], [Groh et al. 2017], [Gros 1997], [Grosskopf and Duke 1992], [Guo et al. 2024], [Gupta et al. 2025], [Hall et al. 2024a], [Hamstad 1983], [Harizi and Tuloup 2026], [Harrigan 2017], [Harris 1963], [Hay et al. 2003], [Hayford and Henneke], [Hayford et al. 1977], [Henneke 1992], [Henneke and Jones 1979], [Herath et al. 2022], [Hirota et al. 2019], [Hofmann and Glasser 1990], [Hosten 1991], [Hsu and Fischer 1996], [Huang et al. 2001], [Huang and Lanza di Scalea 2023], [Hudson and Yuan 2018], [Hutchins et al. 1993], [Iervolino and Meo 2017], [In Situ Infrared Spectroscopy 1998], [In-Situ Composite Cure Monitoring 1990], [Investigation of acoustic pressure 1990], [Investigation of acoustic pressure 1990], [Investigation of Acoustic Pressure 1994], [Ito et al. 2012], [Jang and Rao 1987], [Jang and Shih 1990], [Jin Soo Kim and Dai Gil Lee 1996], [Jiroutova 2016], [Juarez et al. 2016], [Jung and Jin Kang 2007], [Kahali Moghaddam et al. 2017], [Kang et al. 2001], [Karlsson et al. 2024], [Katunin et al. 2015], [Kautz 1992], [Kautz 1996], [Kazilas and Partridge 2004], [Kennedy and Woodmansee 1970], [Kennedy and Woodmansee 1971], [Khalifa et al. 2024], [Khalifa et al. 2025], [Kim and Lee 2002b], [Kim et al. 2024b], [Kim et al. 2024c], [Kinra 1985], [Kinra 1987], [Kovaleva and Savotchenko 2021], [Kranbuehl 2008], [Kranbuehl et al. 1987], [Kranbuehl et al. 1989], [Kumar et al. 2011], [Lawless 1980], [Lee et al. 2020], [Lee and Kim 2004], [Lee and Lee 2024], [Lenhart et al. 1999], [Lettera and Natale 2024], [Lhermitte et al], [Lid 2001], [Lionetto et al. 2007], [Liping et al. 2012], [Liu 2000], [Liu 2001], [Liu et al. 1997], [Lopato and Chady 2013], [Lott et al. 1991], [Lovejoy 2004], [Lucht], [Mahoon 1983], [Mahoon 1988], [Maistros and Partridge 1995], [Mal et al. 1991], [Martin 1963], [Marzani et al. 2019], [Matzkanin and Yolken 2001], [May and Claus 1996], [McGovern 1979], [McIlhagger et al. 2000], [Meola et al. 2017], [Meyer zu Westerhausen et al 2024], [Miakisheva et al. 2020], [Michaels et al. 2009a], [Michaels et al. 2009b], [Mizukami et al. 2020], [Monitoring the Composite Cure 1991], [Murayama et al. 2002], [Na 2007], [Nam et al. 1999], [Nayeb-Hashemi et al. 1999], [Nayeb-Hashemi and Zheng 1990], [Nazarchuk et al. 2022], [Neural Network Nondestructive Evaluation 2013], [Nishi et al. 2024], [Nondestructive Evaluation Methods 2013b], [Nondestructive Evaluation Methods 2013a], [Ahmad and Bond 2018], [O’Dwyer et al. 1998], [Ogilvy 1995], [Ogisu et al. 2006], [Oromiehie et al. 2016], [Oromiehie et al. 2019a], [Oshima et al. 2001], [Oshima et al. 2003b], [Oshima et al. 2003a], [Oshima et al. 2003c], [Packman 1973], [Panda et al. 2018], [Park 2017], [Partridge and Maistros 2000], [Paul], [Perry et al. 1992], [Pipes et al. 1979], [Pommer and Sinapius 2018], [Posarac et al. 2010], [Pouchias et al. 2019], [Prozorovska et al. 2017], [Qing et al. 2020], [Quate 1979], [Quate 1981], [Quattrocchi et al. 2019], [Quinn et al. 2023], [Ramakrishnan et al. 2014], [Ramos et al. 2006], [Rempt 2003], [Robinson 1984a], [Robinson 1984b], [Roth et al. 1997], [Rufai et al. 2020], [Sacco et al. 2020], [Saikrishna et al. 2014], [Santosa 1992], [Sarjeant et al], [Scheerer et al. 2025], [Schmachtenberg et al. 2005], [Scholle and Sinapius 2018], [Sebastian 2001], [Segreto et al. 2019], [Sen et al. 2020], [Sendeckyj et al. 1982], [Shan and Heng 2011], [Shannon et al. 1993], [Shepard 2018], [Shepard et al. 1988], [Shepard et al. 1998], [Shepard and Smith 1999], [Shtrauss et al. 1996], [Skordos et al. 1999], [Skordos and Partridge 2000], [Slattery et al. 1998], [Smith et al. 2024], [Sockol et al. 2017], [Solid Composite Laminate NDI], [Solodov et al. 2008], [Solodov et al. 2018], [Sorrentino et al. 2019], [Spencer et al. 2021], [Sreeshan et al. 2020], [Staszewski et al. 2000], [Sullivan and Davis 1979], [Sun 2003], [Sutin 2000], [Swiderski and Vavilov 2015], [Taheri and Hassen 2019], [Takeda et al. 2007], [Tang et al. 2022], [Test Method for Measurement], [Tifkitsis and Skordos 2019], [Tittmann 2018], [Tittmann and Crane 2000], [Tracked Changes. Aerospace series], [Tracy 2009], [Tracy 2011], [Training Guidance for Solid], [Trenton et al. 2021], [Triollet et al. 2011], [Tříska et al. 2023], [Tserpes et al. 2014], [Udd 2004], [Ultrasonic Inspection], [Ultrasonic Inspection 1971], [Ultrasonic Inspection Devices 1971], [Ultrasonic Inspection 1972], [Ultrasonic Inspection of Composite 1985], [Ultrasonic inspection of graphite 1994], [Ultrasonic inspection of graphite 1994], [Ultrasonic inspection of impact 1994], [Ultrasonic Inspection 2013], [Ultrasonic Nondestructive Evaluation 2003], [Ultrasonic Probes 1971], [Ultrasonic Probes 1972], [Ultrasonic system for in 1990], [Ultrasonic System 1994], [Unwin 2002], [Unwin 2004], [Vacher et al. 2004], [Van Otterloo], [Vary and Bowles 1979], [Wang et al. 1998b], [Wang et al. 1997b], [Wang et al. 2025a], [Ward and Parrish 1970], [Weissberg and Baruch 1981], [Wetton et al. 1990], [Wikswo 2000], [Woerdeman et al. 1997], [Wong], [Woodmansee 1992], [Wu et al. 2001], [Wu et al. 2015b], [Wu et al. 2026b], [Wüstenberg and Mundry 1971], [高 and Xu 2026], [Xu et al. 2014], [Yang et al. 2014], [Yassene et al. 2017], [Yee et al. 1975], [Yolken and Matzkanin 2001], [Yurov V.M. 2019], [Zalameda et al. 2017], [Zellouf et al. 2001], [Zhang et al. 2017e], [Zhang et al. 2022c], [Zhang et al. 1999], [Zhang et al. 2000], [zhaoxuan and kaiyu 2024], [Zhiying et al. 2024], [Zhong and Nsengiyumva 2022d], [Zhong and Nsengiyumva 2022a], [Zhong and Nsengiyumva 2022b], [Zhong and Nsengiyumva 2022c], [Zhu et al. 2025b], [Zhu et al. 2026b], [Zoughi and Ganchev 1995], [Zukas et al. 1982], [Zukas and Wentworth 1987].

The cost of building it, which is the thing being validated

The sixth largest cluster, and the registry entry names it directly. Manufacturing cost models, cost-estimating relationships, learning curves, design for manufacture and assembly, part count and producibility. This is the shelf the X-55 was designated to add a point to [Military Airframe Costs The Effects of Advanced Materials and Manufacturing Processes] [Apostolopoulos and Kassapoglou* 2002].

324 records. [A Comparison of Cost 1977], [A Preliminary Estimate 1970], [Abraham and Prasad 1969], [Adams 1974], [Adler et al. 1985], [Aircraft Cost Considerations 2010], [Stekler 1982], [Badiru et al. 2013], [Alaziz et al. 2024], [Anderson 2001], [Anderson et al. 2025], [Apgar 1993], [Appleton 2008], [Asadayoobi et al. 2021], [Noevere and Von Jamora], [Noevere and Collier 2020], [Automated Laser Repair 2009], [Badiru 1991], [Badiru 1992], [Badiru and Jaber 2026], [Bain 1952], [Ballistic Missile Office Norton AFB CA 1990], [Balut et al. 1991], [Bao and Chen 2023], [Barlow et al. 2002], [Bayoumi 2000], [Benchekchou and White 1995], [Berry 2002], [Björnsson et al. 2015], [Blackwell and Eastlake], [Bogue 2012], [Boothroyd 1987], [Boothroyd 1994], [Boothroyd 1996], [Boothroyd 1997], [Boothroyd et al. 2001], [Boothroyd et al. 2010], [Boushab et al. 2024], [Brookhart 2021], [Bush 1965], [Cabrera-Ríos and Castro 2007], [Butler 2000], [Baron and Leger 1998], [Calkins et al. 1989], [Çalmaşur et al. 2021], [Camacho et al. 2019], [Camin and McKenzie 1980], [Cao et al. 2022], [Castagne et al. 2004], [Cavalcanti Hernandes et al. 2025], [Chai et al. 2023], [Chan et al. 2018], [Chapman et al. 1975], [Chen 1983], [Chen et al. 2022a], [Chen and Storch 2013], [Cherrington and Towill 1983], [Choi et al. 2005], [Claussen 1999], [Colley 2009], [Comey et al. 1978], [Cortes et al. 2019], [Cost-Estimating Relationships for Aircraft 1972], [Chen et al. 2020a], [Cost of Composites 2010], [Cost of Composites 2013], [Crosby et al. 2003], [Cunningham 1980], [Curran et al. 2007], [Dawei and Xuefeng 2012], [de Cos et al. 2008], [Delionback 1979], [Deng and Yeh 2009], [Deng and Yeh 2010], [Deng and Yeh 2011], [Design for manufacture, assembly], [Design for Manufacture 1998], [Design for Manufacture 2001], [Design for Manufacturing 2007], [Detweiler 1995], [Dhavale 1990], [Di Pasquale Davide et al. 2017], [Domanski 2020], [Donath et al. 1981], [Eakin 2010], [Edwards 2002], [Eggert], [Factors that influence Manufacturing], [Ferreira et al. 2019], [Ferreira et al. 2021], [Finchum 1974], [Franceschini and Galetto 2004], [Fraser and Williams 2005], [Friction Stir Superplasticity 2014], [Friot et al. 2017], [Fung and Popplewell 1994], [Gamweger et al. 2009], [Gauthier et al. 2000], [George et al. 2019], [Gill et al. 2016], [Globerson 1980], [Globerson 1984], [Globerson and Gold 1997], [Goddard 1982], [Gould et al. 2015], [Grosse et al. 2015], [Gudmundsson 2014], [Gudmundsson 2022], [Gupta and Mahendran 2025], [Gurumurthy 2024], [Gutowski et al. 1994], [Haifeng et al. 2014], [Hällgren et al. 2016], [Hartley 1965], [Harvey 2002], [Harvey 2005], [Harvey 2015], [Haynes et al. 2025], [Hazbany et al], [Heimbs et al. 2013], [Hennessey et al. 2023], [Herrera 1998], [Hill 1996], [Hinrichsen and Bautista 2001], [Hogan et al. 2020], [Hogan et al. 2022], [Hou and Lai 2015], [Hoult and Meador 1997], [Hoult and Meador 2010], [Hove et al. 1989], [Huang and Mak 1999], [Huang and Mak 2003], [Huang et al. 2026c], [Hueber et al. 2016], [Hueber et al. 2019], [Hunt and Sturges 1993], [Ilcewicz et al. 1991], [Improved Lightweight Unitized Barrier/flow 2001], [Ipkovich et al. 2025], [Ito et al. 2004], [Jaber and Bonney 1999], [Jackson 1998], [Jared 1997], [Jegley and Velicki 2013], [Jia et al. 2013], [Johnson 1969], [Jones 2018], [Joshi et al. 2008], [Jung 2002], [Kamrani and Nasr 2009], [Kamrani and Salhieh 2002], [Karpiuk 2015], [Kasai 2006], [Keel 1988], [Killingsworth 2006], [Kim et al. 2001], [Kim and Kim 2026], [Kiritsis and Xirouchakis 1998], [Kosztowny and Waas 2014], [Kosztowny and Waas 2015], [Kosztowny and Waas 2021a], [Kosztowny and Waas 2021b], [Kulkarni and Rosen 1977], [Kumar and Saha 2025], [Kundu et al. 2003], [Laurenzi et al. 2014], [Learning Curves 2015a], [Learning Curves 2015b], [Learning Curves 2026a], [Learning Curves 2026b], [Lee 1965], [Letaief et al. 2020], [Lin et al. 2011], [Liu et al. 2025a], [Locascio 2001], [Lovejoy 2022], [Lovelace 1998], [Low Cost PEI Prepreg 2001], [Low-Cost Composite Primary Structure 1978], [Lueck and Schenewerk 1996], [Lundberg 1956], [Maffezzoli et al. 2012], [Mahadik and Masel 2018], [Mahieux 2001], [Majd and Pindyck 1987], [Maksud and Yusof 2013], [Maley], [Malstrom and Collins 2000], [Manufacturing Cost Estimation 1993], [Manufacturing Cost and Product 2017], [Markryun et al. 2025], [Marsh 2001], [Mårtensson et al. 2015], [Martin and Evans 2000], [Martinez and Revilla 2015], [Martins et al. 2022], [Maukar et al. 2019], [Mazumdar and Hoa 1995], [Mazzola and McCardle 1997], [McAnally 1974], [Measom and Sewell 1996], [Military Airframe Acquisition Costs 2001], [Mills and Jones 2010], [Molloy et al. 1998a], [Molloy et al. 1998b], [Morimoto et al. 2015], [Morse 1972], [Morse et al. 2022], [Morse and Mallardo 2023], [Moses 1990], [Moses 1991b], [Moses 1991a], [Moses 1992], [Moses 1995], [Mowins 2006], [Mulani et al. 2010], [Nettles 1991], [Newport News Shipbuilding Va 1993], [Nguyen 2025], [Ning et al. 2020a], [Ning et al. 2020b], [Ning et al. 2023], [Ninio 2006], [Noton 1984], [Noton and Preston 1981], [Nussbaum 1994], [Nyemba 2025], [Ostwald and Sathyamoorthy 1992], [Pananiswami and Bishop 1991], [Park et al. 2004], [Parks 1985], [Patwardhan and Ramani 2004], [Pedersen and Slepniov 2016], [Perry et al], [Phillips 1986a], [Phillips 1986b], [Pochiraju et al. 1998], [Posteucă and Sakamoto 2017a], [Posteucă and Sakamoto 2017c], [Posteucă and Sakamoto 2017b], [Practical Cost Estimating 2005], [Pritz et al. 2016], [Product Manufacturing and Cost 2013], [Rachowitz et al. 1979], [Military Airframe Costs The Effects of Advanced Materials and Manufacturing Processes], [Apostolopoulos and Kassapoglou* 2002], [Retz 2019], [Richardson and Stewart 2012], [Riedesel 1977], [Rigelsford 2004], [Cabrera-Ríos and Castro 2003], [Rorsted 1999], [Rosenthal 1982], [Rotheiser 2009], [Roy and Palacio 2000], [Sakinc and Smith 2023], [Sang-bong 2007], [Sarka 2017], [Sarker and Coates 1997], [Scanlan et al. 2006], [Sehdev et al. 1995], [Selvaraj et al. 2008], [Sheahen et al. 2000], [Shiue 1991], [Shivajee et al. 2019], [Shu 2004], [Shukla and Bayha 1993], [Singh Gill et al. 2016], [Skelly 1989], [Smunt 1999], [Smunt 2000], [Smunt 2011], [Soares et al. 2018], [Son 1991], [Stahl et al. 1984], [Stinson 2006], [Sun 2026], [Teng et al. 2014], [The Application of Computer 1994], [The Learning Curve 2011], [Tierney et al. 2021], [Tihansky 1976], [Tirovolis and Serghides 2005], [Tlija et al. 2018], [Tokucoglu et al. 2022], [Torres et al. 2019], [Towill 1977], [Towill 1985], [Holzwarth 1998], [Using the Learning Curve 2010], [van Hattum et al. 2011], [Vincent 2009], [Walls and Crawford 1995], [Wang 2025], [Wang et al. 2014], [Warman 1996], [Weeks 2001], [Wei and Egbelu 2000], [Why do Aircraft Cost], [Why Do Aircraft Cost 1999], [Wilkinson and Ruggles-Wrenn 2016b], [Wilkinson and Ruggles-Wrenn 2016a], [Williams and Ambler], [Wit 2001], [Womer and Marcotte 1986], [Wong et al. 1992], [Woo and Ditto 1985], [Wu and Baur 2024], [Wu et al. 2023a], [Xu Xinsheng et al. 2006], [Yamashina and Mizuyama 1997], [Yang and Zhao 2018], [Yao and Wei], [Yates 1964], [Yazid et al. 2024], [Ye et al. 2009], [Yi et al. 2023], [Yin and Hou 2019], [Younossi et al. 2001], [Zaloom and Miller 1982], [Zarei et al. 2026], [Zhao and Kapania 2016a], [Zhao and Kapania 2016b], [Zhao Xiaojia et al. 2014].

Consolidating without a pressure vessel, which is the whole premise

The premise, stated as a shelf. Out-of-autoclave and vacuum-bag-only processing, the autoclave it is measured against, debulking, bagging and the consolidation pressure each route supplies. This cluster is smaller than the cure cluster and that ordering is itself a finding, because the difficulty of the method turns out to live in the chemistry rather than in the bag [Sutter et al. 2010].

276 records. [A Rapid Design System 2011], [Agius and Fox 2015], [Levy et al. 2015], [Starwin/ETI Tech et al. 2025], [Alshahrani and Hojjati 2017], [Amirkhosravi et al. 2017], [Analysis of Vbo Governing 2021], [Anandan et al. 2016], [Anandan et al. 2013], [Anandan et al. 2014], [Anders et al. 2022], [Arikan et al. 2022], [Arquier], [Autoclave Cures Composite Aircraft 2000], [Koushyar et al. 2011], [Barzoki et al. 2019], [Bellisario 2023], [Bellisario et al. 2019], [Bilitsis and Melquist 2011], [Blackwell et al. 2023], [Bloom et al. 2014], [Boey 1988], [Boey and Lye 1992], [Bregman et al. 2024], [Liu and Hubert 2021], [Butukuri et al. 2012], [Canaroli et al. 2025], [Centea et al. 2015], [Centea and Hubert 2012], [Centea and Nutt 2015], [Chang and Young 2023], [Chang et al. 2016], [Chang et al. 2017], [Chava and Namilae 2022], [Ciriscioli et al. 1992], [Ciriscioli and Springer 2021b], [Ciriscioli and Springer 2021a], [Jin et al. 2019], [Cloth, Type “e” Glass], [Cloth, Type “E” Glass], [Comer et al. 2019], [Serrano et al. 2017], [Continuous Monitoring System 1990], [Coulehan 1984], [Helmus et al. 2015a], [Crawford et al. 2022], [Cuenot], [Czajkowska et al. 2014], [Czarnocki and Czajkowska 2015], [Dai et al. 2023], [Dai et al. 2024], [Dang et al. 2011], [de Andrade Raponi et al. 2020], [Hu and Nutt 2020], [Centea and Hubert 2013], [Degraff et al. 2022], [Degraff et al. 2025], [de Lumley et al. 2019], [Dewangan and Chakladar 2024], [Dimoka et al. 2019a], [Diukov 2021], [Domínguez and Madsen 2014], [Donetskiy et al. 2022], [Drakonakis et al. 2013], [Dufour et al. 2004], [Ekuase et al. 2022], [Engelhardt et al. 2019], [°F Autoclave Cure, Low], [Lai et al. 2023], [Fanteria et al. 2023], [Fernández et al. 2003], [Fernlund et al. 2018], [Fernlund et al. 2003], [Filippov et al. 2026], [Fukuda 2001], [Gackowski et al. 2023], [Galiana 2022], [Galvez-Hernandez et al. 2024], [Gangloff et al. 2016], [Gleason 1983], [Greber 2022], [Guilherme et al. 2017], [Hamill et al. 2015], [Hank et al. 2022], [Haschenburger 2021], [Helmus et al. 2015b], [Hernandez Caraballa et al. 2022], [Hidayat 2018], [Holmes et al. 2012], [Holmes and Larry R. 2012], [Holt 1987], [Hong et al. 2016], [Hou et al. 2013], [Howell and Hines 2024], [Hu et al. 2019], [Hubert 2023], [Hubert et al. 2018], [Hubert et al. 2012], [Hudson et al. 2021], [Hudson et al. 2026], [Iorio et al. 2023], [Janzen and May 2023], [Jayasree et al. 2020], [Jiang et al. 2021], [Jinno et al. 2003], [Joven and Minaie 2018], [Joven et al. 2013], [Kaur et al. 2016], [Kaushik and Raghavan 2010], [Keith and Navid 2021], [Khan et al. 2017a], [Khan et al. 2017b], [Kim et al. 2024a], [Kim et al. 2004a], [Kim et al. 1997], [Kim and Lee 2012], [Kim et al. 2020b], [Knuuttila 2006], [Kratz and Hubert 2011], [Kratz and Hubert 2015a], [Kratz and Hubert 2015b], [Krogh et al. 2020], [Kubiś et al. 2018], [Kunc et al. 2017], [Laboratory Production of Discontinuous-Aligned 1986], [Lachana Dora and Mishra 2022], [Lane et al. 2011], [Lee et al. 2018], [LeMay 2019], [LeMay and Askari 2018], [Leone 2015], [Levy and Hubert 2019], [Li et al. 2012a], [Li et al. 2024], [Li et al. 2009], [Liapi et al. 2025], [Liu et al. 2024b], [Louis and Ermanni 2012], [Lu et al. 2023], [Lystrup and Andersen 1998], [Ma et al. 2015], [Maffezzoli and Grieco 2012], [Maguire et al. 2020], [Mahdavi et al. 2017], [Mahdi et al. 2003], [Maji et al. 2020], [Mallow and Campbell 2000], [Manson and Seferis 1989], [Martins et al. 2018], [McDonald et al. 2014], [Md Hanafiah and Othman 2024], [Hanafiah and Othman 2024], [Md Masum Billah et al. 2021], [Medium Temperature, Out-of-Autoclave, Oven-Vacuum-Bag], [Mehndiratta 2017], [Method and Apparatus 1994], [Method for Debulking Precured 1992], [Mezeix et al. 2014], [Mezeix et al. 2015], [Michel Avila et al. 2026], [Centea and Hubert 2011], [Minamisawa 2017], [Mohan et al. 2016], [Moretti et al. 2021], [Mujahid et al. 2020], [Müller et al. 2017b], [Narayana Swamy], [Nassar et al. 2017], [Netzel et al. 2021a], [Netzel et al. 2021b], [Nguyen et al. 2018], [Nieto-León et al. 2022], [Nilakantan and Nutt 2017], [Niu et al. 2026], [Njionhou et al. 2012], [Hanafiah et al. 2024a], [Hanafiah et al. 2024b], [Oliveri et al. 2021], [Olivier and Serrano 2023], [Out of autoclave manufacturing], [Grunenfelder et al. 2013], [Páez et al. 2022], [Park et al. 2018a], [Patou], [Paul et al. 2021a], [Pineda et al. 2014], [Pishvar et al. 2017], [Pishvar et al. 2018], [Dimoka et al. 2019b], [Popineau et al. 2021], [Pourahmadi et al. 2024], [Préau and Hubert 2018], [Grunenfelder et al. 2017], [Prepreg Requires No Autoclaving 1998], [Maes et al. 2022], [Quadrini et al. 2021], [Quinlan et al. 2014], [Rajmohan and Arunachalam 2022], [Razali et al. 2021], [Ren and Zhang 2025a], [Ren and Zhang 2025b], [Ridgard 2006], [Rusnáková et al. 2023], [Ryan et al. 2023], [Saenz-Castillo et al. 2020], [Saffar et al. 2022], [Saffar et al. 2020], [Samaratunga et al. 2021], [Santoro et al. 2020], [Schechter et al. 2018], [Schechter et al. 2020], [Zebrine et al. 2022], [Seon et al. 2019], [Seon et al. 2020], [Shaik et al. 2021b], [Shaik et al. 2021a], [Sherwin 1999], [Sheu and Young 2023], [Shorts Uprate Composites Curing 1992], [Soltani et al. 2014], [Staal et al. 2022], [Stark et al. 2013a], [Steiner and Sandor 1991], [Steiner and Sandor 1992], [Stroe et al. 2025], [Strong 2026], [Subawi 2011], [Sudarisman and Davies 2008], [Sukia et al. 2022], [Sun et al. 2011], [Sunilpete and Cadambi 2020], [Surjoseputro et al. 2018a], [Surjoseputro et al. 2018b], [Sussmann et al. 2018], [Sutter et al. 2010], [Swamy et al. 2023b], [Swamy et al. 2024], [Swamy et al. 2023a], [Takagaki et al. 2016], [Tavares et al. 2010], [Taylor and Yanagimoto 2019], [Taylor et al. 2019], [Torres et al. 2022a], [Torres et al. 2022b], [Torres López], [Tubular Autoclave for Curing 1992], [Tuttle 1987], [Unitary vacuum bag for 1996], [der Werff et al. 2025], [Villareal et al. 2019], [Vora et al. 2014], [Wang et al. 2026c], [Wang et al. 2016b], [Wang et al. 2018], [Weber et al. 2019], [Westergaard 2005], [Wiggers et al. 2018], [Wilson et al. 2016], [de Faria Gonzales Leal et al. 2024], [Wu and Xu 2025], [Wu and Young 2022c], [Wu and Young 2022b], [Wu and Young 2022a], [Xin et al. 2010], [Xin et al. 2011], [Xu et al. 2026], [Xu and Xie 2025], [Yang et al. 2013], [Yue et al. 2022], [Yun et al. 2026], [Zeng and Raghavan 2010], [Zervos et al. 2024], [Zhang et al. 2017f], [Zhang et al. 2020a], [Zhang et al. 2007], [Zou et al. 2026].

The tool, and why a cured part is not the shape it was cured on

Tooling, and the shape that comes off it. Tool materials, thermal expansion, spring-in, cure-induced distortion, residual stress and the shimming that absorbs what is left. A unitised part is a large part, and a large part carries its distortion over a long baseline, so this cluster grows in importance exactly as the part count falls.

233 records. [Abitz and Pety 2024], [Abouhamzeh et al. 2014], [Adams and Monib 1980], [Advanced Composite Prepreg Tooling 1992], [Ahmad et al. 2026], [Ahmed and Jones 1988], [Albert et al. 2020], [Al-Dhaheri et al. 2020b], [Al-Dhaheri et al. 2020a], [Antonucci et al. 2006a], [Arafath et al. 2008], [Arafath et al. 2009], [Backmann et al. 2024], [Balaji et al. 2024], [Bao et al. 2002], [Bellini and Sorrentino 2018], [Benazzo and Pellegrino 2026], [Bickerton and Kelly 2007], [Blanchard 2020], [Bondarchuk and Fedulov 2019], [Bosi et al. 2018], [Brauner et al. 2014a], [Brauner et al. 2013], [°C cure epoxy tooling 2020], [Cai et al. 2023], [Cameron et al. 2023], [Cameron et al. 2021], [Campbell 2004], [Camponeschi et al. 1994], [Chang et al. 2019], [Chava et al. 2022], [Chen et al. 2020d], [Chen et al. 2021a], [Chen et al. 1998c], [Chen and Zhang 2018], [Chen and Zhang 2019], [Chou and Penn 1992], [Çiçek et al. 2016], [Çınar and Ersoy 2015], [Cinar et al. 2020], [Clifford et al. 2006], [Composite Tooling 1990], [Corrado and Polini 2019], [Crasto et al. 2002], [Cui et al. 2025], [D’Angelo et al. 2018], [Dassios et al. 2013], [Delsol et al. 2026], [Ding et al. 2022], [Ding et al. 2015], [Ding et al. 2020], [Dippenaar and Schreve 2012], [Djokic et al. 2002], [Dong 2009], [Dong 2010b], [Dong 2010a], [Dorworth 2001], [Ehmke et al. 2017], [Eijpe and Powell 1997], [Ekom 2021], [Feldman 1986], [Fenn and Jones 1989], [Feuchtgruber et al. 2023], [Feuchtgruber et al. 2024], [Franciosa et al. 2020], [Freeman and Campbell 1972], [Gao et al. 2017], [Gibbons et al. 2009], [Goncalves et al. 2023], [Gopal et al. 2000], [Griffiths and Leigh 2019], [Guan et al. 2026], [Gupta et al. 2012], [Gutman et al. 1994], [Han et al. 2013], [Hao and Zhang 2019], [Hartmann and Loy 2026], [Hasselman 1999], [Henriksen et al. 1983], [Ho-Nguyen-Tan et al. 2024], [Hu et al. 2026b], [Huang et al. 2000], [Hui et al. 2024], [Hui et al. 2026], [Huitink and Montazeri 2021], [Irving et al. 2014], [Ito et al. 2014], [Jabarulla Khan et al. 2022], [Jain et al. 1997], [Jamora et al. 2020], [Ji 2017], [Ji and Xia 2015], [Jiang et al. 2023], [Jo et al. 2023], [Johnston et al. 2001], [Joseph and Namilae 2024], [Kappel 2016], [Kappel 2018], [Kappel 2019], [Kappel et al. 2015], [Karalekas et al. 2008], [Khoun and Hubert 2010], [Kim 2004], [Kim and Choi 2001], [Kim and Kim 2024], [Kim and Lee 2026], [Kim and White 1998], [Kiyani et al. 2026], [Kravchenko et al. 2017], [Kress and Winkler 2009], [Kroupa and Bartsch 1998], [Lacoste et al. 2011], [Lee et al. 2026a], [Lee et al. 2025b], [Li et al. 2025e], [Li and Jia 2013], [Li et al. 2017c], [Li et al. 2022f], [Li et al. 2020a], [Lin et al. 2022], [Liu et al. 2013b], [Liu et al. 2021c], [Liu et al. 2024a], [Liu et al. 2021a], [Low Temperature Moulding LTM 1990], [Mahto et al. 2022], [Maravola et al. 2018], [McCallum et al. 2017], [Meuwissen et al. 2004], [Minakuchi 2014], [Minakuchi et al. 2019], [Mirone et al. 2025], [Mohanta and Neogi 2026], [Moisture and Thermal Expansion 1984], [Montés and Sánchez 2010], [Nawab and Jacquemin 2016], [Ochinero and Hyer 2002], [Ouyang et al. 2026], [Parambil et al. 2022], [Park et al. 1994], [Patel and Dodge 2026], [Patil et al. 2019b], [Peng et al. 2022], [Pereira et al. 2019], [Perreux and Lazuardi 2001b], [Perreux and Lazuardi 2001a], [Phansalkar and Han 2026], [Poorzeinolabedin et al. 2014], [Potter 1997b], [Potter 1997f], [Prasad et al. 1987], [Prime and Hill 2004], [Process induced distortions of], [Process-Induced Stress and Deformation 1992], [Qiao and Yao 2020], [Rai et al. 1991], [Residual Stress in Metal-Matrix 2016], [Robert and Dusserre 2013], [Rocha et al. 2021], [Russo et al. 2021], [Saadat and Cretin 2002], [Sandberg et al. 2021], [Schoenholz et al. 2022], [Sfar Zbed], [Sherif El-Gizawy and Kuan 2003], [Shojiro et al. 1997], [Shrotriya et al. 2001], [Sicot et al. 2005], [Sinkler et al. 2025], [Skinner and Chattopadhyay 2021], [Skordos and Partridge 2007], [Somalwar], [Spray Metal Composite Tooling 1982], [Spring-in Simulation Example 2020], [Sreekantamurthy et al. 2016], [Steinzig and Broetto 2014], [Struzziero et al. 2020], [Sun and Zhang 2020], [The Transverse Coefficient 1992], [Thermal Diffusivity and Coefficient 2014], [Thermal Residual Stress 1987], [Thiede-Smet and Wadsworth 1998], [Onyia 2025], [Tooling Study 2014], [Toyoda et al. 2024], [Türk et al. 2019], [Tzeng 1995], [Vangerko 1988], [Vermes and Czigany 2022], [Vermeulen and van Tooren 2007], [Vo et al. 2019], [Von Jamora et al], [Wadsworth 1998], [Wang 2022], [Wang et al. 1992], [Wang et al. 2017b], [Wang et al. 2020c], [Wang et al. 2022d], [Wang et al. 2024b], [Wang et al. 2026d], [Weitsman 1985], [Wen et al. 2019], [White and Hahn 1992], [Wise 2000], [Wolff 1987], [Wu et al], [Wu et al. 2026a], [Xiaojun Wang and Chung 1997], [Xu et al. 2022], [Yan et al. 2025b], [yang et al 2021], [Yang et al. 2021b], [Yang et al. 2018a], [Yang et al. 2019a], [Yi and Lam 2012], [Yi et al. 2005], [Yoo et al. 2025], [Yoon and Kim 2001], [Yuan et al. 2016], [Yuan et al. 2024], [Yuan et al. 2021b], [Yue et al. 2025], [Yue and Shi 2018], [Zarrelli et al. 2006], [Zeng et al. 2025], [Zeng et al. 2016], [Zhang et al. 2018a], [Zhang et al. 2019a], [Zhang et al. 2019b], [Zhang et al. 2026a], [Zhang et al. 2026e], [Zhao et al. 2020a], [Zok et al. 2010].

Voids, gas transport and the pressure that is not there

The keystone physics, and it is not a large cluster. Void content, porosity, entrapped air, volatiles, permeability, resin flow and consolidation. Everything an autoclave does with pressure, an out-of-autoclave process must do with transport [Helmus et al. 2015a].

219 records. [Allsop et al. 2025], [Amico and Lekakou 2001], [Anderson and Altan 2014], [Anderson and Altan 2015], [Anjali et al. 2013], [Antonucci et al. 2003], [Ashbee 1986], [Awenlimobor et al. 2025], [Awenlimobor et al. 2026], [Ayanoglu et al. 2022], [Bahar et al. 2021], [Bai et al. 2025], [Bai et al. 2026], [Bakhshi and Hojjati 2019], [Bandaru et al. 2019], [Barzegar et al. 2021], [Bilyeu et al. 2001], [Binetruy et al. 1998], [Briard et al. 2026], [Caballero et al. 2021], [Caballero Garzón], [Cai 1992], [Cai et al. 1992], [Castro Arias], [Chadwick et al. 2023], [Chang 2025], [Chang et al. 2004], [Chen et al. 2021c], [Chen et al. 2004a], [Chenlong Yang 2011], [Cirino and Byron Pipes 1991], [Composites. Prepregs. Determination of], [D30 Committee 2008b], [Daniel et al. 1992], [Danzi et al. 2016], [Davé 1990], [Dave et al. 1987b], [Dave et al. 1987a], [Dehghani et al. 2025], [DeValve and Pitchumani 2013], [Duong et al. 2015], [Eldeeb et al. 2026], [Endruweit et al. 2022], [Etchegaray Bello et al. 2022], [Eum et al. 2007], [Feng et al. 2019], [Flora et al. 2022], [Fuller and Gammell 1987], [Ganapathi et al. 2016], [Gangloff et al. 2014], [Garrett et al. 2025], [Gayot et al. 2022], [George et al. 2020], [Gorthala et al. 1994], [Grelsson 1992], [Grunenfelder and Nutt 2010], [Gu et al. 2006], [Gu et al. 2008], [Guemes 2001], [Gueroult et al. 2013], [Guochang et al. 2007], [Haghshenas et al. 2018], [Hamada et al. 1995], [Hanafiah and Othman 2022], [Handley et al. 1987], [He et al. 2020], [He et al. 2017], [Helmus et al. 2016], [Hojjati and Kheradpisheh 2023], [Hsu and Jeong 1989], [Hsu and Nair 1987], [Huang and Yung 2010], [Hubert and Poursartip 2001], [Hughes et al. 1988], [Iannone et al. 2018], [Improved Preimpregnated Material Comprising 1992], [Ishida et al. 2020], [Ishii et al. 2016], [Islam et al. 2022], [Jeong 1997], [Jeong and Hsu 1995], [Johnson and Pitchumani 2008], [Kanetoh and Yokoi 2012], [Kang et al. 2018], [Kardos et al. 1983], [Karumbaiah et al. 2019], [Kedari et al. 2011], [Kermani et al. 2018], [Kim et al. 2023], [Klosterman et al. 2020], [Kotomin and Avdeev 2003], [Kratz et al. 2021], [Kratz et al. 2017], [Lai et al. 2015], [Larimore et al. 2012], [Lay et al. 1998], [LeBel et al. 2017], [Lebel-Lavacry et al. 2012], [Lee et al. 2025a], [Lee et al. 2026b], [Lee and Lee 2003], [Liang et al. 2024], [Liang et al. 2023], [Lin et al. 2007], [Liu and Wu 2010], [Liu et al. 2026a], [Lukaszewicz et al. 2013], [Lundström 1997], [Mandell and Tsai 1990], [Matsuzaki et al. 2013], [McGovern and Jar 1999], [Mendikute et al. 2022], [Merotte et al. 2020], [Method for Producing 1978], [Michaels et al. 1993], [Michaud 2016], [Mignolet 1994], [Mori and Minakuchi 2026], [Morrison and Bader 1989], [Mulye], [Mulye et al. 2023], [Muser 1968], [Nagy et al. 1987a], [Nagy et al. 1987b], [Nair et al. 1989], [Naito et al. 2015], [Naskar and Edie 2006], [Newaz and Majumdar 1994], [Nixon-Pearson et al. 2016], [Okereke et al. 2017], [Oromiehie et al. 2019b], [Paithankar et al. 1990], [Pang et al. 2014], [Pantaloni et al. 2020], [Parham 1971b], [Park et al. 2010], [Parnas 1998], [Patel et al. 2020], [Patel and Lee 1995], [Patel and Lee 1996], [Peng et al. 2024], [Podymova and Karabutov 2013], [Porosity characterization in thin 1994], [Precup 2025], [Process for the Production 1988], [Qureshi et al. 2014], [Rahatekar and Roux 2003], [Reed et al. 1993], [Rizzolo and Walczyk 2014], [Rizzolo and Walczyk 2016], [Roychowdhury et al. 1992], [Roychowdhury et al. 2001], [Sarthak Mahapatra et al. 2021], [Schell et al. 2007], [Sebaey et al. 2021], [Seferis 2006], [Seferis 2009], [Shah and Clifford 2015], [Shanthar et al. 2026], [Shen et al. 2019], [Shen et al. 2026], [Shi et al. 2016], [Shi et al. 2023], [Shi et al. 2024], [Shim and Seferis 1997], [Shokrollahi et al. 2020], [Shoukroun et al. 2021], [Simacek et al. 2025], [Slange et al. 2017], [Smith and Poursartip 1993], [Sommer et al. 2020], [Song 2006], [Stamopoulos et al. 2015], [Standard Test Method for], [Suarez and Dastin 1992], [Tahani and Yousefsani 2015], [Tahir et al. 2024], [Tang et al. 1987], [Tang and Postle 2000], [Test Method for Volatiles], [D30 Committee 1900c], [D30 Committee 2008d], [Test Method for Determination], [Test Method for Resin], [Test methods for the], [Thomas and Nutt 2009], [Timms et al. 2012], [Tittmann et al. 1986], [Traouli 2025], [Um et al. 2009], [van den Nieuwenhuizen and Miller 1994], [Vaxman et al. 2011], [Verheus and Peeters 1993], [Vivian Silveira et al. 2025], [Vo et al. 2022], [Vogl et al. 2024], [Krach and Advani 1996], [Walbran et al. 2012a], [j-waves Ultrasonic Solutions et al. 2026], [Wang et al. 2022f], [Wang et al. 2026h], [Wang et al. 2024f], [Wymer and Engel 1994], [Xiong et al. 2017], [Yalcinkaya et al. 2019], [Yan et al. 2024], [Yan et al. 2025a], [Yang et al. 2019b], [Yas and Hojjati 2026], [Ye et al. 1995], [Yeager et al. 2015], [Yoon et al. 2004], [Young 1995b], [Yu et al. 2026], [Zalameda and Smith 1994], [Zhang et al. 2017a], [Zhang et al. 2026d], [Zhou et al. 2013], [Zhu et al. 2015c].

The laminate as a material, its strength, impact and durability

Coupon and material evidence, split out of the residual. The strength and stiffness of the laminate, its impact and residual strength, fatigue and creep, fibre metal laminates, and the effect of moisture, temperature and service environment on all of these. This is the level a building-block qualification starts from, and the thirty-five day out-life test quoted above records its short beam shear deficit at exactly this level before it is a fact about any fuselage [Sutter et al. 2010].

73 records. [Adams 1982], [Akkala and Daggumati 2023], [Aminanda 2012], [Behera et al. 2020], [Boller 1965], [Bouvet 2016], [Broutman 1977], [Broutman and Rotem 1972], [Cadieu et al. 2019], [Carpier et al. 2018], [Carrillo and Cantwell 2009], [Ding et al. 2007], [Effect of Layering 2016], [Fahem et al. 2023], [Fantuzzi et al. 2024], [Fard et al. 2011], [Forsman 1983], [Fracture Characterisation of Random 1987], [Gama and Gillespie 2008], [Ganesan and Vasudevan 2023], [Gigliotti et al. 2015], [Gonzalez-Canche et al. 2017], [Hamada et al. 1996], [Hickey and Campagna 1990], [Hoa 1981], [황규완 and Jae Ung Cho 2016], [Justusson et al. 2020], [Kabbani and El Kadi 2018], [Kamiyama et al. 2019], [Kang and Lee 1994], [Karpouzian and Librescu 1994], [Karthik et al. 2023], [Kaware et al. 2022], [Kaware and Kotambkar 2023], [Khalili et al. 2010], [Kim et al. 2020a], [Klasztorny et al. 2018], [Kumar 2018], [Lim and Kim 2024], [Liu et al. 2025b], [Lopez et al. 2020], [Luo et al. 2020], [Matadi Boumbimba et al. 2014], [Medjahed et al. 2019], [Miyano and Nakada 2020], [Miyase et al. 1993], [Morgan 2007], [Nowak and Schmidt 2015], [Ochelski and Gotowicki 2009], [Olusanya], [Philippidis et al. 1999], [Portanova 1994], [Prabhakar 2020], [Randall and van der Zwaag 2003], [Rashedi et al. 2016], [Sachse et al. 2020], [Shang 2023], [Shimokawa et al. 2007], [Sikarwar et al. 2017], [Sreenivasa and Joshi 2013], [Su et al. 1999], [Sugiman and Crocombe 2012], [Sun and Huang 2016], [Tennyson et al. 1992], [Vaidya and Hosur 2003], [Vyhnal 1993], [Walrath and Adams 1980], [Wang and Blum 1994], [Ward 1974], [Yokozeki et al. 2002], [Zhang et al. 2016], [Zhang and Zhang 2015], [Zhao et al. 2022].

Drilling, machining and fastening a laminate

The hole every fastener starts as. Drilling, milling and cutting of laminates, metal and composite stacks and honeycomb core, and the riveted and bolted fastening that follows the hole. Every fastener the subsection headed Where the Compression Comes From counts begins as a hole drilled through a laminate or a stack, and these titles measure what the drilling does to it, in thrust force, delamination and hole quality [Park et al. 2018b].

24 records. [Ambekar et al. 2026], [Bai et al. 2021], [Boughdiri et al. 2021], [Boutrih et al. 2022], [Dong Wang et al. 2019], [Eneyew and Ramulu 2014], [Gerendt et al. 2019], [Jiang et al. 2026], [Kumar et al. 2020b], [Kuo et al. 2017], [Li et al. 2022d], [Li et al. 2017b], [Ma et al. 2022], [Mi et al. 2026], [Mohan et al. 2005], [Park et al. 2018b], [Qiu et al. 2017b], [Song et al. 2022], [Van de Velde et al. 2023], [Wang et al. 2020b], [Wang et al. 2022c], [Wu et al. 2023c], [Zhang et al. 2019c], [Zu et al. 2017].

The atmosphere, which bounds what a vacuum bag can do

Small, and load-bearing in exactly one place. The standard atmosphere, pressure altitude and the barometric relation. A vacuum bag cannot press harder than the air outside it, so the elevation of the factory floor enters a manufacturing specification, and this shelf is what that computation stands on [U.S. Standard Atmosphere].

19 records. [Air Force Test Pilot School Edwards Afb Ca 1962], [Appendix a. the Standard 2011], [Appendix a Standard Atmosphere 2021], [Brown 2012], [Essenhigh 2006], [Kang et al. 2023b], [Kang et al. 2023a], [Kaushik 2018], [Space environment natural and], [National Bureau of Standards 1927a], [National Bureau of Standards 1927b], [Standard Atmosphere 2005], [Standard Atmosphere 2024], [The Flight Environment 2021], [The International Standard Atmosphere 2017], [The International Standard Atmosphere 2026], [U.S.Committee on Extension to the Standard Atmosphere 1966], [1976 US Standard Atmosphere 2014], [Vaughan 2003].

The aeroplane and the programmes around it

Thirteen records, and the smallest cluster in the survey. The Advanced Composite Cargo Aircraft, the studies of composite structure for transport aircraft around it, and other flight and ground demonstrators. The X-55 produced a designation, a first flight and almost no documentary trace, which is the third kind of thin this series has catalogued rather than the first, because the work was done and was not published, a contractor’s manufacturing hours being a competitive asset [Ilcewicz et al. 1997].

13 records. [Advanced Composite Cargo Aircraft makes first flight], [Flansburg and Engelstad 2013], [Howdyshell et al. 1998], [Deaton et al. 1995], [Fielding 1983], [Gardner et al. 2014], [Halpin 2011], [Lange and Moore 1982], [Molent and Jones 2018b], [Quinlivan and Fenbert 1995], [Raja 2009], [Smillie 1983], [Smith et al. 1987].

Other work on composite materials, processing and structures

The residual, at 0.6 percent. Work on fibre-reinforced composites as materials whose titles name none of the subjects of the thirteen clusters above, being general accounts of the material family, the fibre and its surface, and functional properties such as thermal and electrical conduction, electromagnetic shielding, fire and ablation. It describes the material the airframe is made of and none of the operations performed on it, which is why it is small, and its admission rule is set out in the subsection headed What the Survey Admits.

30 records. [Aerospace series. Polyetheretherketone with], [Aerospace series - Polyetheretherketone], [Alkoc et al. 2024], [Bascom 1964], [Conductive Thermoset Composites 2018], [Dagli and Sung 1983], [Dauksys et al. 1968], [Epoxy Resin Moulding Material 2002], [Fang et al. 2019], [Friedman 1961], [Groves and Stocks 1991], [Gul et al. 2026], [Kaiser 1994], [Kale 2021], [Lin et al. 2013], [McAllister and Hill 1984], [Ndiaye and Asl Sharhani 2026], [Noah Martimfold 2025], [Petersson et al. 2013], [Polyester Fibreglass-Reinforced Composite Laminate 1978], [Ratna 2022c], [Sathishkumar and Kaliyannan 2020], [Shibata 2013], [Tasaka and Matsuzaki 2025], [Wang et al. 2016a], [Wilson et al. 2017], [Xu et al. 2024], [Yokeswaran et al. 2026], [Yu and Wan 2012], [Zhang et al. 2022d].

Where the Framing Breaks Down

The X-55’s central quantity has no instrument. This is the second article in this series whose binding number is an estimate rather than a reading, after a vehicle whose entire argument turned on a launch price [X-Planes: Orbital Sciences X-34].

A flying demonstrator can settle several things and cannot settle the one it was named for. It can settle whether a bonded composite fuselage with skins twenty metres long will carry flight loads, whether it can be built at all, whether the tooling closes, and whether the structure behaves as predicted once instrumented. It cannot settle a recurring cost, because a recurring cost is a property of a production run and the demonstrator is a run of one.

What it can do is retire a manufacturing risk, and that is a real thing to retire. Before June 2009 the proposition that a fuselage of this size could be laid up, bonded, closed and flown without an autoclave was an assertion, and afterwards it was not [The Carbon Comet, Lockheed Martin].

But a manufacturing risk is not the whole of the technical risk, as the fastener giveback shows. The certification of a bonded unitised primary structure was an open problem before the X-55 flew and remained one long afterwards [Market Trends, the Composites Affordability Initiative, Part I, CompositesWorld] [Clay et al. 2021], and no single flying article could have closed it, because what a certification basis wants is not a demonstration but a body of evidence about how the structure fails.

The registry entry claims more than a demonstrator can deliver, and the gap between the two is the subject of this article.

The Source Base

The research survey holds 4,803 records, and every one of them is cited in the survey in the section headed The Contemporary Literature. They are drawn from NASA’s Technical Reports Server, the Defense Technical Information Center and the journal literature indexed by Crossref. The reference list holds 4,909 definitions in total, being the research records together with forty-four reference sources, seven books and fifty-five links to earlier articles in this series.

The Definition of Primary

Primacy is a property of the document, and this survey derives it from the identifier. A research record is a report primary when its address is on the NASA Technical Reports Server or its digital object identifier carries the 10.21236 prefix under which Crossref registers Defense Technical Information Center reports.

284 of the 4,803 research records are report primaries, being 5.9 percent, counted by that rule. 197 of those are defence-registry reports and 87 are report-server documents, which is the reverse of the balance in the previous article in this series and is simply a fact about who paid. Sonic boom research was a civil agency’s and this was the Air Force’s.

A report share of 5.9 percent is small, and it is a fact about who did the work. Composite manufacturing was done by contractors, and a contractor’s process hours, cure schedules and scrap rates are a competitive asset rather than a publication. What the registries do hold is the government’s own share of the work, which is the certification question and the predecessor programmes.

Both kinds of primary are reported, because the measure cannot see most of this article’s. The article names and argues from 29 primary documents, and 23 of them carry no identifier the corpus measure recognises. The designation registry [Parsch, DOD 4120.15-L Addendum, MDS Designators Allocated After 19 August 1998], the material datasheet [MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials], the manufacturer’s own account of the build [The Carbon Comet, Lockheed Martin] and the programme’s own conference papers [Butler 2000] are every one of them primary, and every one is invisible to a count that looks for a report-server prefix. The fraction and the count are reported side by side and the measure is not adjusted to flatter either.

The report primaries remain a generation older than the survey. Their median year is 1993 against 2011 for the corpus, a gap of 18 years.

The Age of the Literature

4,421 of the research records carry a year at or before this article’s own dateline, and their median is 2011, with the range running from 1927 to 2025. Publication rate by decade, in records a year, is set out below. The 2020s are counted over six years rather than ten, so the figures are rates and not counts.

A further 148 records carry a later year and are excluded from every statistic in this section, being 3.1 percent of the corpus. They remain in the reference list, which cites later work as well as earlier. A statistic is a different thing from a citation. A rate computed over papers that had not been written when this article is dated would be a claim about the future wearing the clothes of a measurement. A further 234 records carry no year at all, and some fraction of those is certainly later than the dateline too, which no filter can reach.

Decade	Records a year
1950s	0.8
1960s	3.9
1970s	12.9
1980s	35.9
1990s	74.8
2000s	77.8
2010s	126.6
2020s	182.0

This literature has grown in every decade since the 1950s and has never once contracted, which is worth setting beside the previous article in this series. The sonic boom corpus fell by more than forty percent through the 1980s, in the decade after the American supersonic transport was cancelled and overland supersonic flight was prohibited. Composite manufacturing was never prohibited and its curve shows it. A literature records what was permitted as faithfully as it records what was discovered.

Thin Subjects

Seven 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 elevation of the shop floor and the vacuum it allows	altitude, elevation, barometric, ambient pressure, atmospheric pressure together with vacuum bag, vacuum bagging, out of autoclave, vacuum bag only, consolidation, prepreg, debulk, debulking, compaction	0
the surface tension that holds a small void open	surface tension, capillary pressure, laplace pressure, interfacial tension	3
the DiBenedetto relation behind the vitrification ceiling	dibenedetto, di benedetto	0
the time to install a fastener	fastener, fasteners, rivet, rivets, riveting together with installation, install, installing, touch time, assembly time, labour, labor, hours, cost, costs	6
fasteners as disbond arrest in a bonded structure	fastener, fasteners, bolt, bolts, rivet, rivets together with disbond, delamination arrest, crack arrest, fail safe, arrest	4
the X-55 and the Advanced Composite Cargo Aircraft	x 55, x55, x 55a, advanced composite cargo aircraft	2
the out-life of a prepreg	out life, out time, outlife, outtime, tack life, working life, shelf life, storage life, prepreg ageing, prepreg aging, room temperature ageing, room temperature aging, ambient temperature storable	12

No title in the survey ties consolidation to the elevation of the shop floor. The result that a vacuum bag at Air Force Plant 42 can apply only 13.39 pounds per square inch, and that the datasheet’s gauge vacuum is unattainable there, therefore stands on the standard atmosphere and the datasheet alone.

The capillary literature is about filling, not about closing voids. All three titles that name surface tension or capillary pressure concern the impregnation of a dry preform, so the radius below which a bag cannot close a void rests on the Laplace relation and an assumed surface tension rather than on a measured one.

Vitrification is well studied and the relation this article inverts is not named once. Vitrification appears in 28 titles and none of them names the DiBenedetto relation, two of whose three parameters are taken here as assumptions because neither is published for this resin.

The labour a fastener costs has almost no literature in this survey. Six titles name the installation of a fastener, and every one of them concerns the equipment, the automation or the ergonomics of installation and none names the time or the cost per fastener, so the touch times in the fastener arithmetic are the article’s assumptions and are stated as a range.

The fastener given back to a bonded structure has a small and specific literature. Four titles name fasteners as a disbond or delamination arrest, and two of them are the ones the subsection headed Some of the Fasteners Come Back cites.

The designation itself is not a research subject. Two titles name the Advanced Composite Cargo Aircraft and none names the X-55, so the claim in this article’s closing sentence rests on two dates in the register and not on any body of research.

Out-life is the constraint this article argues binds the whole method, and its literature is 12 titles under several names, being out-time, ageing, working life, storage life and ambient storability.

The documents the argument rests on are identified by the programme’s own citation chain and not by the survey. Following the Composites Affordability Initiative and the certification literature it leads to gives the papers the programme’s own engineers treated as the point. A survey cannot do that, because its admission rule decides whether a record belongs to a subject and not which record carries the argument. The survey says what exists, and the citation chain says which of the 4,803 records the argument needs.

What the Survey Admits

A record is admitted only when a person reading its title finds it on this article’s subject, the subject being the composite airframe and its qualification, bonding, thermoset cure, placement and out-life, manufacturing cost, inspection, out-of-autoclave consolidation, voids, tooling and distortion, the laminate as a material, drilling and fastening, the aeroplane, and the standard atmosphere. The atmosphere is admitted for one reason, which is that the consolidation pressure computation above needs it. The residual admits a title on a fibre-reinforced composite as a material when it names none of those subjects, being a general account of the material family, the fibre and its surface, or a functional property such as conduction, shielding, fire or ablation.

Two adjacent literatures are excluded deliberately. Wind turbine blade manufacture is the largest infused composite structure anybody builds and shares most of this article’s process vocabulary. Marine composites share the rest. Both are adjacent rather than contaminating, and both are left out because the subject is an airframe, which means the count in the survey in the section headed The Contemporary Literature is smaller than the technology’s full literature and is not offered as that. The cost and schedule literature of defence acquisition is excluded for the same reason, so the claim that the programme was built cheaper and slower stands on two published dates rather than on the survey. Civil engineering is excluded as well, including fibre-reinforced polymer bonded to concrete, masonry, timber or steel to strengthen a building or a bridge, and so are pipes and risers, and the structural design of cars, boats, wheels, gears and sports goods.

Many words this subject depends on also name something else, and a record that shares only such a word is excluded. Nondestructive inspection shares an abbreviation with dam safety inspection. Entrapped air and the name Darcy also belong to hydraulic, soil and petroleum reservoir studies, and consolidation also names the settlement of soils and dredged slurry. Ultrasonic attenuation is also studied in metals and superconductors, and chemical reactors and hydrometallurgy have autoclaves of their own. Adhesive bonding also names timber and wood-panel construction and the die attach of electronics, shimming also names the shimming of magnets for magnetic resonance imaging, and a void also names the diffusion and casting voids of metallurgy. The glass transition is also a property of every amorphous polymer, rubber and inorganic glass, and cure also names the vulcanisation of rubber. Restorative dentistry uses bond strength, cure kinetics, resin composite and degree of conversion as its own terms of art, the textile and paper industries have their own standards for conditioning atmospheres, and a short learning curve is an idiom. A cost model or a design-for-assembly study of an unrelated product, such as a solar cell, a circuit board or a kitchen appliance, and the operating and maintenance cost of aircraft, are excluded because the argument prices manufacture and assembly.

Editorial notices are excluded, because a notice is not a research work. That is every record whose title opens with Correction, Erratum, Errata, Corrigendum, Withdrawn, Withdrawal or Retraction, or whose identifier carries the numbered notice suffix, such as .c1, that the American Institute of Aeronautics and Astronautics gives a correction, and every record whose title declares itself a withdrawal notice. A title that names a correction as its technical method, such as a correction response surface design, is a research work and is kept. A book’s preface or other front matter, a review of a book, a reference or definition entry of two pages or fewer, a table of standard values of two pages or fewer printed as a textbook appendix, a journal’s listing of a newly issued publication, the resolution of a standards conference and a second deposit of a document already in the survey are not admitted either, while an authored encyclopedia article of more than two pages and a textbook chapter are research works and are kept.

Some records of doubtful relevance are kept. Thermoset cure and warpage in microelectronic packages are kept as thermoset cure, and so are epoxy cure kinetics for art restoration and the low-temperature cure of powder coatings, because the chemistry is the subject. Learning-curve and cost-method titles that name no product are kept as cost-method literature. Process studies whose part is a car body, a boat or an offshore structure are kept as process literature, because the process is the subject. Each shares a method with this subject rather than only a word, and a reader may weigh it accordingly.

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

What is documented. The registry entry, the donor airframe, the structural arrangement, the material family, the part and fastener counts, the contract value, the required and achieved first flight dates, the cause of the delay, and the aeroplane’s disposition.

What is computed here and stated as such. The pressure at Plant 42 and the consolidation pressures that follow from it. The pressure vessel scaling. The Boyle’s law void arithmetic and the surface-tension threshold beneath it. The activation energy fitted to the datasheet, and the dwell comparison built on it. The vitrification ceiling. The Darcy transport times. The convective scaling. The fastener labour and the break-even run. The layup rate implied by the out-life and the ply ceiling implied by that. None of those is a measurement of this aeroplane. They are what the published constants imply, and where an assumption drives an answer the assumption is named beside it.

Four assumptions carry more weight than the rest and are collected here. The surface tension of the uncured resin is taken at 0.035 newtons per metre, a representative value and not a measurement of this material. The Kozeny constant, the fibre volume fraction and the two viscosities in the transport calculation are representative in the same way, and the transport conclusion survives a hundredfold error in the permeability because the length goes as its square root. Two of the three DiBenedetto parameters are assumptions, and the vitrification ceiling moves between 0.741 and 0.899 across the range they plausibly occupy, while the conclusion drawn from them does not move at all. The minutes and the burdened rate in the fastener arithmetic are assumptions spanning a factor of ten, and the break-even run spans the same factor in consequence.

What is uncertain. The ninety against ninety-eight percent fastener discrepancy is unresolved. The trade press calls the fuselage sixty feet long in one account and its skins sixty-five feet long in another, and the encyclopaedia entry gives fifty-five feet for the fuselage with the nose attached [Out-of-Autoclave Prepregs, Hype or Revolution, CompositesWorld] [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld] [Lockheed Martin X-55]. This article uses the skin length throughout, which makes the skin area and every rate derived from it an upper estimate. The number of flights was expected in advance to be 15 to 20, and no primary record of the total has come to light. The cure schedule used on the fuselage is not published, and the trade press reports an oven cure at 177 degrees, 350 Fahrenheit, with vacuum pressure [Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld], where the datasheet’s vacuum bag cure is 120 degrees with a post-cure at 180, which is most likely a description of the post-cure rather than a contradiction. The article does not assume which.

What could not be verified. No Air Force Research Laboratory final report on this programme was located in the public report registries, and the absence is reported rather than treated as evidence of absence. The number of arrest fasteners a certification basis would demand of a structure like this one is not published and is not estimated here. The claim that the bond failure was caused by out-life is not made, because no source states it. The out-life argument here is a mechanism the literature supports and not a diagnosis of this event.

What the corpus excludes. 148 records carry a year later than this article’s dateline and are excluded from every statistic while remaining in the reference list. A further 234 carry no year at all and cannot be filtered either way.

Out of Scope

The aerodynamics of the aeroplane, which were the Dornier’s and were not modified. The flight test instrumentation and the loads it measured, for which no public dataset was found. Thermoplastic composites, which answer the same question a different way and would double the article. The certification of bonded primary structure, which is named because the survey covers it and is not argued here. And the aeroplane’s contribution to any later programme, information a contractor does not publish.

Conclusion

The X-55 was given a number to validate that an airframe could be built faster and cheaper, and the record shows it was built cheaper and slower.

The two halves of the registry entry were never symmetric. The cost claim is a comparison against an estimate of an aeroplane nobody built. The schedule claim is a comparison against a date, and the date was missed by seven to nine months, by source, because the skin on the lower fuselage did not bond and a second fuselage had to be made. The demonstration was delayed by the thing being demonstrated.

The arithmetic shows that this should have been expected, and why. Low-temperature curing costs three times the oven dwell of the cure it replaces, so the time saving cannot come from the chemistry. It has to come from part count, and part count is a recurring saving that a run of one cannot collect. Meanwhile the same technology that lets a part be large enough to be worth unitising puts a chemical clock on how long its layup may take, and a programme built on the case for fewer and larger parts still assembled its fuselage from eight of them.

Nor is the part-count saving wholly the programme’s to keep. Certifying a bonded primary structure has meant putting mechanical fasteners back through the bondline as a second load path and a disbond arrest, and those take back some of what unitisation removed while giving up the stiffness and the fatigue performance that motivated bonding. How much is given back is not published and this article does not guess.

None of that makes the aeroplane a failure. It flew, it carried its loads, and it did so on a cooperative agreement of 49,097,981 dollars for its design and build. It retired a manufacturing risk. A bonded composite fuselage with skins 19.8 metres long could be built outside an autoclave, tooled, closed and flown, and before June 2009 that was an assertion.

What it did not retire, and could not have, is the certification risk. An Air Force Research Laboratory programme was still publishing on fail-safe features for bonded unitised structure in 2023, fourteen years later, so the question of whether such a structure can be certified without putting the fasteners back was open before the X-55 flew and remained open long after.

And what it could not do was measure the quantity in its own mission statement, because that quantity only exists across a production run. The arithmetic puts that run at between forty and four hundred aeroplanes and at about a hundred on the middle assumption, and there was never going to be a second.

One number in this article deserves to be kept for its own sake. The pressure a vacuum bag can apply is the pressure of the air outside it, so the consolidation available to an out-of-autoclave process at Air Force Plant 42 is 13.39 pounds per square inch against the 14.7 of sea level, and the material datasheet asks for a vacuum the site’s entire atmosphere cannot supply. A manufacturing specification for an aeroplane turns out to depend on the elevation of the floor it is built on.

The number arrived 139 days after the first flight, which is the right order for a designation that was recognising a result rather than authorising an attempt.

Equations

This section collects the 38 display equations of the article in the order they appear, each under its number and reproduced exactly as it stands in the text. A title in bold names an established result, and a title in italics beginning with the word Bespoke names a construction made for this analysis. Of the 38, 28 are established and 10 are bespoke. Consolidation pressures are in pounds per square inch, cure dwells in hours, temperatures in kelvin in the Arrhenius relations but in degrees Celsius in the glass transition relations, where only differences enter, and lengths and areas in metres, while several letters are reused, so $D$ is the sandwich bending stiffness and then the fuselage diameter, $L$ a vessel, flow path, laminate or skin length, $H$ the scale height and $H(t)$ the reaction heat released, $h$ an altitude, a heat transfer coefficient or working hours a day, $\alpha$ the degree of cure and $\alpha_{\text{th}}$ a thermal diffusivity, and $R$ the molar gas constant while $R_{\text{air}}$ is the specific gas constant of air.

Equation 1, Bending Stiffness of a Sandwich Panel. A sandwich takes its bending stiffness almost wholly from two facesheets held apart by the core, approximately half the facesheet modulus times the facesheet thickness times the square of the core depth.

\[D \approx \frac{E_{f}\,t_{\text{face}}\,h_{c}^{2}}{2} \tag{1}\]

Equation 2, Thin-Walled Pressure Vessel Wall Thickness. Hoop stress fixes the wall thickness of a cylindrical vessel as the pressure times the radius over the allowable stress. Pressure Vessel

\[t_{w} = \frac{p\,r}{\sigma_{\text{allow}}} \tag{2}\]

Equation 3, Shell Mass of a Cylindrical Pressure Vessel. The shell mass is the density times the shell area times the wall thickness, so it rises with the square of the radius times the length. Pressure Vessel

\[m_{\text{shell}} = 2 \pi \rho \, r \, L \, t_{w} = \frac{2 \pi \rho \, p \, r^{2} L}{\sigma_{\text{allow}}} \tag{3}\]

Equation 4, Consolidation Pressure Under a Bag and in an Autoclave. A vacuum bag consolidates with the ambient pressure less the pressure inside the bag, and an autoclave adds its gauge pressure to that differential. Vacuum Bag Moulding

\[\Delta p_{\text{bag}} = p_{\text{amb}} - p_{\text{in}} \qquad\qquad \Delta p_{\text{autoclave}} = p_{\text{gauge}} + p_{\text{amb}} - p_{\text{in}} \tag{4}\]

Equation 5, Ratio of Autoclave to Vacuum Bag Consolidation Pressure. With the bag fully evacuated the ratio of autoclave to bag consolidation pressure is one plus the gauge pressure over the ambient pressure.

\[\frac{\Delta p_{\text{autoclave}}}{\Delta p_{\text{bag}}} = 1 + \frac{p_{\text{gauge}}}{p_{\text{amb}}} \tag{5}\]

Equation 6, Pressure in the Standard Troposphere. The standard atmosphere gives the ambient pressure below the tropopause as a power of the linearly falling temperature ratio. U.S. Standard Atmosphere Barometric Formula

\[p(h) = p_{0}\left(1 - \frac{\lambda h}{T_{0}}\right)^{\frac{g}{R_{\text{air}}\lambda}} \tag{6}\]

Equation 7, Sea-Level Pressure Gradient and Scale Height. Differentiating the hydrostatic balance at sea level gives a pressure gradient equal to the sea-level pressure over the scale height.

\[\left.\frac{\mathrm{d}p}{\mathrm{d}h}\right|_{0} = -\frac{p_{0}\,g}{R_{\text{air}} T_{0}} = -\frac{p_{0}}{H} \qquad\qquad H = \frac{R_{\text{air}} T_{0}}{g} \tag{7}\]

Equation 8, Boyle’s Law for an Entrapped Gas. At constant temperature the volume of an entrapped gas is inversely proportional to its pressure. Boyle’s Law

\[V_{1} = V_{0}\,\frac{p_{0}}{p_{1}} \tag{8}\]

Equation 9, Void Fraction After Isothermal Compression. With the solid taken as incompressible beside the gas, compressing the voids by Boyle’s law changes the void fraction as the compressed void volume over the new total volume. Boyle’s Law

\[\phi_{1} = \frac{\phi_{0}\,p_{0}/p_{1}}{\left(1-\phi_{0}\right) + \phi_{0}\,p_{0}/p_{1}} \tag{9}\]

Equation 10, Pressure Ratio Required for a Target Void Fraction. Inverting the void fraction relation gives the pressure ratio that a specified final void fraction demands.

\[\frac{p_{1}}{p_{0}} = \frac{\phi_{0}}{\phi_{1}}\cdot\frac{1-\phi_{1}}{1-\phi_{0}} \tag{10}\]

Equation 11, Laplace Pressure of a Void. The gas in a spherical void exceeds the resin pressure by twice the surface tension over the void radius. Laplace Pressure

\[p_{\text{void}} - p_{\text{resin}} = \frac{2\gamma}{r} \tag{11}\]

Equation 12, Smallest Void Radius Closed by a Given Pressure. Setting the Laplace excess equal to the available consolidation pressure gives the radius below which pressure cannot close a void. Laplace Pressure

\[r_{\text{min}} = \frac{2\gamma}{\Delta p} \tag{12}\]

Equation 13, Henry’s Law. The concentration of gas dissolved in the resin is proportional to the pressure applied. Henry’s Law

\[c = k_{H}\,p \tag{13}\]

Equation 14, Darcy’s Law. The volumetric flux through a porous medium is the permeability over the viscosity times the pressure gradient. Darcy’s Law

\[q = -\frac{k}{\mu}\,\nabla p \tag{14}\]

Equation 15, Kozeny-Carman Permeability of a Fibre Bed. The Kozeny-Carman relation sets the permeability of a fibre bed by the square of the fibre diameter and the cube of the open fraction over the square of the fibre volume fraction and the Kozeny constant.

\[k = \frac{d_{f}^{2}\,\left(1 - V_{f}\right)^{3}}{\kappa\,V_{f}^{2}} \tag{15}\]

Equation 16, Bespoke Sweep Time Through a Dry Tow Network. The article takes a linear pressure gradient over the path to estimate the time a fluid needs to sweep the channel network as viscosity times porosity times the square of the path length over permeability times pressure difference.

\[t_{\text{sweep}} = \frac{\mu\,\varphi\,L^{2}}{k\,\Delta p} \tag{16}\]

Equation 17, Ratio of Resin to Air Sweep Times. For the same path, permeability and pressure difference the two sweep times stand in the ratio of the two viscosities.

\[\frac{t_{\text{resin}}}{t_{\text{air}}} = \frac{\mu_{\text{resin}}}{\mu_{\text{air}}} \tag{17}\]

Equation 18, Degree of Cure. The degree of cure is the reaction heat released so far as a fraction of the ultimate heat of reaction, as a calorimeter reports it. Thermosetting Polymer

\[\alpha(t) = \frac{H(t)}{H_{\text{ult}}} \tag{18}\]

Equation 19, Autocatalytic Cure Rate Model. The two-constant autocatalytic model fits epoxy amine cure with a rate that rises from zero before it falls. Vyazovkin and Sbirrazzuoli 1996 Keenan 1987

\[\frac{\mathrm{d}\alpha}{\mathrm{d}t} = \left(k_{1} + k_{2}\,\alpha^{m}\right)\left(1 - \alpha\right)^{n} \tag{19}\]

Equation 20, Arrhenius Dependence of Cure Time on Temperature. Because both rate constants follow an Arrhenius law, the time to reach a given degree of cure rises exponentially as the temperature falls. Arrhenius Equation Kratz et al. 2012

\[t \;=\; A_{0} \exp\!\left(\frac{E_{a}}{R\,T}\right) \tag{20}\]

Equation 21, Activation Energy From Two Isothermal Dwells. Two dwells at two temperatures that reach the same state fix an activation energy through the logarithm of their ratio over the difference of reciprocal temperatures. Arrhenius Equation

\[E_{a} \;=\; R\,\frac{\ln\!\left(t_{1}/t_{2}\right)}{1/T_{1} - 1/T_{2}} \tag{21}\]

Equation 22, Bespoke Apparent Activation Energy From the Datasheet Cures. The datasheet’s twenty hours at 80 degrees Celsius and two hours at 130 are treated as reaching a common state, an assumption the article adopts although the cures are not iso-conversional, giving an apparent activation energy of about 54.5 kilojoules per mole. MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials

\[E_{a} = 8.314 \times \frac{\ln\left(20/2\right)}{1/353.15 - 1/403.15} = \frac{19.14}{3.512 \times 10^{-4}} \approx 54{,}510 \tag{22}\]

Equation 23, Arrhenius Ratio of Dwell Times. The ratio of dwell times at two temperatures is the exponential of the activation energy over the gas constant times the difference of reciprocal temperatures.

\[\frac{t_{\text{lo}}}{t_{\text{hi}}} = \exp\!\left[\frac{E_{a}}{R}\left(\frac{1}{T_{\text{lo}}} - \frac{1}{T_{\text{hi}}}\right)\right] \tag{23}\]

Equation 24, Bespoke Predicted Dwell at 120 Degrees and the Datasheet Margin. Extrapolating from two hours at 130 degrees with the fitted apparent activation energy predicts about three hours at 120, so the datasheet’s four hours carries a margin of about 32 percent. MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials

\[t_{\text{lo}} = 2 \exp\left[6{,}556 \left(\frac{1}{393.15} - \frac{1}{403.15}\right)\right] \approx 3.025, \qquad \frac{4}{3.025} - 1 \approx 0.322 \tag{24}\]

Equation 25, Fourier Conduction Time of a Laminate. The time for heat to equilibrate across a laminate is the square of its thickness over its through-thickness diffusivity.

\[\tau = \frac{L^{2}}{\alpha_{\text{th}}} \tag{25}\]

Equation 26, Bespoke Conduction Time of a Six Millimetre Laminate. At a through-thickness diffusivity of three ten-millionths of a square metre per second, a representative value the article assumes, a six millimetre laminate equilibrates in two minutes, under one percent of the four hour dwell. Thermal Diffusivity

\[\tau = \frac{\left(6 \times 10^{-3}\right)^{2}}{3 \times 10^{-7}} = 120, \qquad \frac{\tau}{t} = \frac{120}{14{,}400} \approx 0.0083 \tag{26}\]

Equation 27, Bespoke Pressure Scaling of the Convective Coefficient. The Dittus-Boelter form makes the convective coefficient scale as the 0.8 power of gas pressure once the article holds velocity, temperature and geometry equal between the oven and the autoclave. Nusselt Number

\[\mathrm{Nu} = C_{Nu}\,\mathrm{Re}^{0.8}\,\mathrm{Pr}^{1/3} \qquad\Longrightarrow\qquad \frac{h_{\text{autoclave}}}{h_{\text{oven}}} \sim \left(\frac{p_{\text{autoclave}}}{p_{\text{oven}}}\right)^{0.8} \tag{27}\]

Equation 28, Bespoke Convective Advantage of the Autoclave. At the consolidation pressure ratio of 7.35 the coefficient rises by about 4.93, or by 3.31 at an exponent of 0.6 that the article assumes as the lower end of the range.

\[\frac{h_{\text{autoclave}}}{h_{\text{oven}}} \sim 7.35^{0.8} \approx 4.93, \qquad 7.35^{0.6} \approx 3.31 \tag{28}\]

Equation 29, DiBenedetto Relation. The DiBenedetto relation gives the rise of the glass transition temperature with degree of cure between its uncured and fully cured values. Glass Transition

\[\frac{T_{g} - T_{g0}}{T_{g\infty} - T_{g0}} = \frac{\lambda_{D}\,\alpha}{1 - \left(1 - \lambda_{D}\right)\alpha} \tag{29}\]

Equation 30, Vitrification Limit on the Degree of Cure. Setting the glass transition equal to the cure temperature and inverting the DiBenedetto relation gives the conversion at which the resin vitrifies.

\[\alpha_{\text{vit}} = \frac{f}{\lambda_{D} + \left(1 - \lambda_{D}\right) f} \qquad\qquad f = \frac{T_{\text{cure}} - T_{g0}}{T_{g\infty} - T_{g0}} \tag{30}\]

Equation 31, Bespoke Vitrification Ceilings at 120 and 160 Degrees. With the datasheet’s fully cured glass transition of 180 degrees and an uncured value of minus 20 degrees and a curvature parameter of 0.5 that the article assumes, a 120 degree cure stops near 0.824 and the wet glass transition of 160 degrees demands 0.947. MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials

\[f = \frac{120 - \left(-20\right)}{180 - \left(-20\right)} = 0.70, \qquad \alpha_{\text{vit}} = \frac{0.70}{0.5 + 0.5 \times 0.70} \approx 0.824, \qquad \frac{0.90}{0.5 + 0.5 \times 0.90} \approx 0.947 \tag{31}\]

Equation 32, Bespoke Sensitivity of the 120 Degree Ceiling. The corners of a grid of uncured glass transitions and curvature parameters that the article assumes representative move the 120 degree ceiling between 0.741 and 0.899.

\[\alpha_{\text{vit}} = \frac{120/180}{0.7 + 0.3 \times 120/180} \approx 0.741, \qquad \alpha_{\text{vit}} = \frac{160/220}{0.3 + 0.7 \times 160/220} \approx 0.899 \tag{32}\]

Equation 33, Total Dwell of Two-Stage Cures Against the Autoclave. Adding the datasheet’s post-cure to each low-temperature cure gives total dwells of three and eleven times the autoclave-only dwell. MTM45-1 Prepreg Technical Data Sheet, Cytec Industrial Materials

\[\frac{t_{\text{init}} + t_{\text{post}}}{t_{\text{ac}}}, \qquad \frac{4 + 2}{2} = 3, \qquad \frac{20 + 2}{2} = 11 \tag{33}\]

Equation 34, Wright Learning Curve. Recurring unit cost falls as a power of the cumulative unit number, with an exponent equal to the logarithm of the progress ratio over the logarithm of two. Experience Curve Effects Military Airframe Costs: The Effects of Advanced Materials and Manufacturing Processes

\[C_{i} = C_{1}\,i^{b} \qquad\qquad b = \frac{\ln \varrho}{\ln 2} \tag{34}\]

Equation 35, Break-Even Production Run. The number of aircraft needed to repay a programme is its cost divided by the recurring saving per aircraft.

\[n_{\text{break-even}} = \frac{C_{\text{programme}}}{\Delta C_{\text{per aircraft}}} \tag{35}\]

Equation 36, Surface Area of a Fuselage Half-Shell. One fuselage half is half a cylinder, so its surface is half of pi times the diameter times the length. Advanced Composite Cargo Aircraft Proves Large Structure Practicality, CompositesWorld

\[A_{\text{skin}} = \frac{\pi D L}{2} \tag{36}\]

Equation 37, Bespoke Layup Rate Demanded by the Out-Life. The article requires every ply of a half-shell to be laid within one out-life window at a constant rate, which sets the sustained rate as plies times skin area over the out-life in working hours.

\[\dot{A} = \frac{N\,A_{\text{skin}}}{t_{\text{out}}\,h_{\text{day}}} \tag{37}\]

Equation 38, Bespoke Maximum Plies Within the Out-Life. Inverting the same single-window construction gives the most plies a shop of a given sustained rate can lay on the shell before the material is out of time.

\[N_{\text{max}} = \frac{\dot{A}\,t_{\text{out}}\,h_{\text{day}}}{A_{\text{skin}}} \tag{38}\]

Notation

• $E_{f}$, the facesheet modulus, with $t_{\text{face}}$ the facesheet thickness
• $h_{c}$, the core depth
• $t_{w}$, the vessel wall thickness
• $\sigma_{\text{allow}}$, the allowable wall stress
• $m_{\text{shell}}$, the shell mass of the vessel
• $p_{\text{amb}}$, the ambient pressure
• $p_{\text{gauge}}$, the autoclave gauge pressure
• $p_{\text{in}}$, the pressure inside the bag
• $\Delta p_{\text{bag}}$, the consolidation pressure under a vacuum bag, with $\Delta p_{\text{autoclave}}$ that in an autoclave
• $\lambda h$, the product of the lapse rate $\lambda$ and the geopotential altitude $h$
• $R_{\text{air}}$, the specific gas constant of air
• $\phi_{0}$, the initial void fraction, with $\phi_{1}$ the void fraction after compression
• $\gamma$, the surface tension of the uncured resin
• $r_{\text{min}}$, the smallest void radius that the consolidation pressure can close
• $k_{H}$, the Henry’s law constant
• $k$, the permeability of the fibre bed
• $\mu$, the dynamic viscosity of the fluid
• $d_{f}$, the fibre diameter
• $V_{f}$, the fibre volume fraction
• $\kappa$, the Kozeny constant
• $\varphi$, the porosity of the channel network
• $t_{\text{sweep}}$, the time for a fluid to sweep the flow path
• $\alpha$, the degree of cure
• $H_{\text{ult}}$, the ultimate heat of reaction
• $E_{a}$, the activation energy
• $\alpha_{\text{th}}$, the through-thickness thermal diffusivity
• $\mathrm{Nu}$, the Nusselt number
• $h_{\text{autoclave}}$, the convective heat transfer coefficient in the autoclave, with $h_{\text{oven}}$ that in an oven
• $T_{g}$, the glass transition temperature
• $T_{g0}$, the glass transition temperature of the uncured resin, with $T_{g\infty}$ that of the fully cured resin
• $\lambda_{D}$, the DiBenedetto curvature parameter
• $\alpha_{\text{vit}}$, the degree of cure at vitrification
• $C_{i}$, the recurring cost of the $i$th unit, with $C_{1}$ that of the first
• $\varrho$, the progress ratio
• $n_{\text{break-even}}$, the number of aircraft needed to repay the programme
• $A_{\text{skin}}$, the skin area of one fuselage half-shell
• $\dot{A}$, the sustained layup rate
• $t_{\text{out}}$, the out-life of the prepreg in days
• $h_{\text{day}}$, the working hours a day
• $N_{\text{max}}$, the most plies that can be laid within the out-life

References

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