In-line autoclave suitable for preform geometry

Abstract

The present invention relates to a tandem autoclave adapted to the geometry of a preform. The present application relates to an apparatus and a method for a tandem autoclave adapted to the geometry of a preform. The method comprises aligning a laying mandrel carrying a preform for insertion into an autoclave, the autoclave having an inner surface complementary to the profile of the preform; and sealing the laying mandrel in the autoclave.

Description

Technical Field

[0001] This disclosure relates to the field of processing machine bodies or other high-performance components, and more specifically, to the autoclave processing of such components. Background Technology

[0002] To manufacture bodies or other high-performance components made of composite materials such as carbon fiber reinforced polymer (CFRP), autoclaves are used to harden uncured preforms into final parts. Autoclaves are designed to process composite parts at elevated temperatures and / or pressures by drawing heated gas into the autoclave under pressure. In traditional factory environments, autoclaves can be designed to accommodate a wide variety of part geometries or multiple parts during the same processing cycle. This results in large autoclaves, requiring significant initial equipment investment, as well as substantial foundation, installation, and auxiliary equipment costs.

[0003] For large autoclaves, their large thermal mass and large volume for accommodating various component geometries require significant energy and gas usage, thus impacting their operating costs. Heating the gas and drawing it into the autoclave requires substantial time and energy, and additional heated gas must be drawn in and maintained or replenished until the autoclave and its contents reach the desired processing temperature and time, further increasing operating costs.

[0004] Given that large autoclaves are mounted on dedicated infrastructure and use gas storage tanks (such as those for inert nitrogen) that need to be mounted on the outer walls, they can also hinder the efficient flow of assembly lines within a factory environment. Furthermore, the size, cost, and operating costs of autoclaves make it conventional to use them in a centralized location at the end of all pre-curing manufacturing processes. In continuous or moving assembly line manufacturing configurations, transporting parts in and out of autoclaves does not allow for optimized part handling. Moreover, the inherent time required for heating, pressurizing, and cooling such autoclaves further limits effective processing time and factory operations.

[0005] Therefore, it is desirable to have methods and apparatus that take into account at least some of the problems discussed above, as well as other possible problems.

[0006] The abstract of WO 2021 / 032430 A1 states: "The present invention relates to a method and apparatus for manufacturing parts from fiber composite materials (2), the method comprising the steps of: introducing a plurality of layers (10, 11) of matrix-impregnated fibers into an inner mold (3) within a mold space (9) formed between an inner mold (3) and an outer mold (4); placing a diaphragm (6) on the matrix-impregnated fibers to seal the outer mold, thereby forming a cavity (7) between the outer mold (4) and the diaphragm (6), the cavity extending along a transverse surface of the outer mold; and subjecting the cavity (7) to a temperature greater than the melting point of the matrix." A temperature-controlled pressure fluid at a pressure greater than ambient pressure is applied to the diaphragm at that pressure. To fabricate a component with at least one reinforcing layer and a particularly smooth, stepless surface, it is proposed to locally place at least one reinforcing layer (11) with a small extension and predominantly parallel alignment on the portion of the base layer (10) facing the outer mold (4). Subsequently, a diaphragm (6) with an average roughness depth of less than 1.0 μm, preferably less than 0.1 μm, applies a set pressure to the component (2) within the cavity.

[0007] The abstract of US 4,997,511A states that "methods and apparatus for mass production of composite material products include: a novel autoclave having a cylindrical vacuum chamber; a cylindrical compression chamber surrounding the vacuum chamber; a reusable flexible diaphragm defining a boundary between the vacuum chamber and the compression chamber; and means for supplying heat and pressure between the diaphragm and the compression chamber. A core or mandrel is wrapped with fiber-reinforced resin and placed in the autoclave, within the flexible diaphragm. Alternatively, part layup can be accommodated by wrapping with consumable shrink tape between a resilient liner and a rigid tool to fit various part shapes having a constant or nearly constant cross-section along their entire length. The autoclave is then sealed and evacuated, causing the diaphragm to compress the resin layer against its core or mandrel due to atmospheric pressure or higher pressure in the compression chamber. The autoclave is then heated to cure the resin. Subsequently, the autoclave is opened and the finished product is removed, making the autoclave immediately reusable." Summary of the Invention

[0008] The embodiments described herein provide a pressurizer for receiving preforms laid out as part of a continuous production line manufacturing process. The pressurizer is sized to receive a specific type of preform and includes an inner surface corresponding to the contour defined by the preform. One technical benefit is a reduction in the volume and mass heated within the pressurizer, thereby reducing cycle time and increasing efficiency. Furthermore, the pressurizer described herein allows hardened composite parts to exit by moving in the same direction as they enter the pressurizer. This saves space on the factory floor, thus reducing costs.

[0009] Other exemplary embodiments (e.g., methods and computer-readable media related to the foregoing embodiments) may be described below. The features, functions, and advantages discussed may be implemented independently in various embodiments or may be combined in other embodiments, and further details of these aspects may be found with reference to the following description and drawings. Attached Figure Description

[0010] Now, some embodiments of the present disclosure will be described by way of example only with reference to the accompanying drawings. In all the drawings, the same reference numerals denote the same elements or elements of the same type.

[0011] Figure 1 This is a block diagram of an assembly line system including a pressure heat exchanger in an exemplary embodiment.

[0012] Figure 2 This is a flowchart illustrating a method for hardening prefabricated components using an operational assembly line system in an exemplary embodiment.

[0013] Figure 3 This is a perspective view of a preform being inserted into a pressure heat exchanger in an exemplary embodiment.

[0014] Figure 4 This is a perspective view of a pressurizer in an exemplary embodiment, wherein a laying mandrel has been inserted into the pressurizer.

[0015] Figures 5A to 5C This is an exemplary implementation. Figure 4 A view of the pressure heat exchanger.

[0016] Figure 5D This is a view of other laying mandrels and pressurizers for the wing plates in an exemplary embodiment.

[0017] Figure 5E Various sealing schemes for the compressor in exemplary embodiments are described.

[0018] Figure 6 This is a side view of an exemplary embodiment, including a laying mandrel for sealing an extended area of ​​the pressurizer.

[0019] Figure 7 This is a top view of the pressurizer and preparation station in an exemplary embodiment.

[0020] Figures 8 to 12 This is a flowchart illustrating other techniques for operating the laying mandrel and complementary heat exchanger in an exemplary embodiment.

[0021] Figure 13 A method for removing a prefabricated component from a cleanroom in an exemplary embodiment is described.

[0022] Figure 14This is a flowchart illustrating an aircraft manufacturing and maintenance method in an exemplary embodiment.

[0023] Figure 15 This is a block diagram of an aircraft in an exemplary embodiment. Detailed Implementation

[0024] The accompanying drawings and the following description provide specific exemplary embodiments of this disclosure. Therefore, it will be understood that those skilled in the art will be able to devise various arrangements that, while not expressly described or shown herein, implement the principles of this disclosure and are included within its scope. Furthermore, any examples described herein are intended to aid in understanding the principles of this disclosure and are to be construed as not being limited to such specific examples and conditions. Therefore, this disclosure is not limited to the specific embodiments or examples described below, but is limited by the claims.

[0025] The body can be realized as a composite material part. Composite material parts, such as carbon fiber reinforced polymer (CFRP) parts, are initially laid out in multiple layers, which together are called a preform. Individual fibers within each layer of the preform are aligned parallel to each other, but different layers can exhibit different fiber orientations to increase the strength of the final composite material part along different dimensions. Alternatively, the preform can also comprise a woven fiber fabric or material with irregular or discontinuous fibers. The preform can include a viscous resin that cures to harden the preform into a composite material part. Carbon fibers impregnated with uncured thermosetting or thermoplastic resins are called “prepregs.” Other types of carbon fibers include “dry fibers,” which are not impregnated with thermosetting resins but may include tackifiers or binders. Dry fibers can be injected with resin and then cured. For thermosetting resins, curing is a one-way process called curing, while for thermoplastic resins, it can reach a viscous form if the resin is reheated.

[0026] Figure 1 This is a block diagram of a production line assembly system 100 in an exemplary embodiment, including a pressurizer 180 for hardening preforms (i.e., curing thermosetting preforms, reheating and consolidating thermoplastic preforms) into composite parts. The production line assembly system 100 includes any system, device, or component operable to iteratively and rhythmically drive preforms 170 for fuselage half-sections (or other bow-shaped sections of the fuselage including skin and stringers) in a processing direction 179. In this embodiment, the production line assembly system 100 includes a pressurizer 180 that hardens the preforms 170 by applying heat and pressure.

[0027] Precast component 170 is laid onto laying mandrel 120, which advances along the factory floor 110 in the processing direction 179 and is driven by an autonomous guided vehicle (AGV) 130 or along a track 132 leading to the autoclave 180. Laying mandrel 120 includes a perimeter 121. A liner 160 (or vacuum bag) is placed over precast component 170 and follows the contour 162 of precast component 170. The laying surface 123 of laying mandrel 120 (see...) Figure 5A The profile 162 of the preform 170 is defined by the liner 160. The liner 160 seals the preform 170 to the laying mandrel 120, which in turn seals the laying mandrel 120 to the inner surface 186 of the pressurizer 180. In this embodiment, the liner 160 is sealed to the laying mandrel 120 via vacuum (e.g., via a vacuum system inside the laying mandrel 120), which causes the preform 170 to be subjected to a consolidation force. In other embodiments, this task is performed using a vacuum bag (e.g., vacuum bag 714).

[0028] During operation, the laying mandrel 120 is driven into the hollow portion (e.g., channel 189) of the pressurizer 180 through inlet 722. When the laying mandrel 120 is inserted into the pressurizer 180, the laying mandrel 120 and the pressurizer 180, together with the peripheral seal 150 and the liner 160, define a pressure chamber 187 (referred herein to as a vacuum chamber, pressure chamber, pressurized chamber, or sealed chamber) for the preform 170. The peripheral seal 150 at the laying mandrel 120 seals the inner surface 186 of the pressurizer 180, causing the pressurizer 180 and the laying mandrel 120 to together form the pressure chamber 187 in which the preform 170 is heated. In other words, the peripheral seal 150 seals the periphery 121 of the laying mandrel 120 to the inner surface 186 of the pressurizer 180. In this embodiment, the laying mandrel 120 also includes a gap seal 124, which may include a rigid or other thermal barrier for sealing the gap 310 (e.g., an arcuate gap) by clamping it to the pressurizer 180 to form a pressure chamber 187 (i.e., any sealed / sealable chamber capable of supporting pressures different from atmospheric pressure). The gap seal 124 is mounted to the laying mandrel 120 via a hinge 125. The gap seal 124 may be formed in an arcuate shape and may include a rigid segment of material. Although hinged gap seals 124 have been discussed, they are only one embodiment for sealing within the pressurizer 180, and other types of seals may be used to engage the laying mandrel 120, the liner 160, and the pressurizer 180 to form the pressure chamber 187.

[0029] Because the inner surface 186 of the autoclave 180 follows the contour 162 of the preform 170, it is complementary to the contour 162 and separated from it only by a small distance (e.g., gap 310) (e.g., less than 25.4 cm (10 inches), such as less than 5.08 cm (2 inches)). This means that the heat and pressure applied to the pressure chamber 187 are applied to a smaller volume than in a conventional autoclave, thereby increasing heating efficiency and hardening rate. It also means that the autoclave 180 has a smaller thermal mass and can be pressurized using smaller components (e.g., with nitrogen or other inert fluids).

[0030] Heater 182 is disposed beneath an insulating shield 188 within the pressurizer 180. In this embodiment, the insulating shield 188 includes blades 184 that provide structural reinforcement to the pressurizer 180 and facilitate heat dissipation after the pressurizer 180 has completed its heating cycle. Heater 182 at the pressurizer 180 and heater 122 at the laying mandrel 120 may include radiant heaters that increase the temperature of the chamber. In one embodiment, heaters 122 / 182 are zone-controlled to ensure that the temperature is uniformly maintained within the desired range across the entire surface of the preform 170. By continuously monitoring and adjusting the heat applied by heaters 122 / 182 zone by zone, the temperature of the preform 170 is precisely controlled throughout the preform 170.

[0031] Heaters 122 / 182 are insulated from the exterior of the pressurizer 180 and the interior of the laying mandrel 120 by insulating shields 188 and 128, respectively. Insulating shields 128 / 188 may include vacuum-sealed or other thermally insulated areas. Pressure system 190 controls the pressure at pressure chamber 187 during hardening / processing, for example, by evacuating or increasing the pressure in pressure chamber 187. In this embodiment, a vent 183 is also provided for driving heated gas to a vacuum chamber 187 formed between the laying mandrel 120, pressurizer 180, peripheral seal 150, and liner 160. Including heaters 122 / 182 at the laying mandrel 120 and pressurizer 180 reduces the distance between heaters 122 / 182 and preform 170, thereby increasing heat transfer efficiency. The use of a "properly sized" pressure chamber 187 with minimal excess volume ensures that the assembly line system 100 uses less gas (e.g., nitrogen or other inert fluids), thereby reducing material costs and thermal cycling time. The pressure chamber 187 discussed herein thus reduces the thermal mass and complexity of the compressor structure, thereby reducing the amount of pressurized gas that needs to be stored.

[0032] In some embodiments, an airbag 199 is disposed at the preform 170 and structurally supports any suitable hollow interior 170-1 of the preform 170 (e.g., the hollow interior 170-1 of a cap-shaped stringer disposed at the preform 170), thereby preventing the hollow interior 170-1 from collapsing during processing. Therefore, the airbag 199 is disposed below the liner 160 or vacuum bag used to consolidate the preform 170. In this way, the airbag 199 supports the hollow interior 170-1 of the preform 170 against compaction caused by the pressure applied by the pressurizer 180.

[0033] The air bladder 199 is in communication with the pressure chamber 187 formed by the pressure heater 180, which means that when the pressure chamber 187 is pressurized, the air bladder 199 is also pressurized and thus inflates. In this way, the air bladder 199 inflates by the pressure from the pressure chamber 187.

[0034] After heating, blades 184 at the press 180 facilitate cooling the press 180 to a handling temperature, at which the lay-up mandrel 120 and composite part 714 are removed in the processing direction 179, and a next lay-up mandrel 120 can be inserted from upstream. In other embodiments, two lay-up mandrels 120 are arranged in series or tandem and are placed into the press 180 simultaneously. In such embodiments, each lay-up mandrel 120 can be sealed to the press 180 to close different doors / entries (e.g., inlet 722 or outlet 724) of the press 180. The next lay-up mandrel 120 is then inserted into the press 180, and the process is repeated. This unique technical arrangement, which allows the lay-up mandrels 120 to define partial boundaries of the chamber 187 of the press 180, saves both energy and time. Furthermore, because the press 180 has a smaller thermal mass than conventional presses, it can be heated and cooled rapidly, thereby reducing cycle time and increasing production capacity.

[0035] In this embodiment, the autoclave 180 itself forms part of the boundary or gated passage 189 between the cleanroom environment 177 and the assembly area / environment 178 (which does not operate as a cleanroom environment). For example, the autoclave 180 may be positioned such that the inlet 722 is within the cleanroom environment 177 by means of a boundary 192 (such as a hood or wall) that prevents dust from entering the cleanroom environment 177. Thus, the autoclave 180 forms part of the boundary of the cleanroom environment 177. After the preform 170 has been processed into the composite part 714, the composite part exits the autoclave 180 via the outlet 724 and enters the assembly area 178.

[0036] To reiterate the above, the pressurizer 180 includes an inner surface 186 configured to slidably receive the laying mandrel 120 and configured to combine with the laying mandrel 120 to form a pressure chamber 187 after the laying mandrel 120 has been slidably received, and the pressurizer 180 also defines an arcuate or wavy gap 310 defined by the inner surface 186, the gap 310 being configured to receive a seal 124 that seals the laying mandrel 120 to the inner surface 186. The laying mandrel 120 defines the profile of the preform 170 and includes a peripheral seal 150 and a gap seal 124. The peripheral seal 150 seals the laying mandrel 120 to the pressurizer 180 as it slides into the pressurizer 180, and the gap seal 124 seals the gap 310 (e.g., an arcuate gap) between the laying mandrel 120 and the pressurizer 180 after the laying mandrel 120 has slid into the pressurizer 180. In this way, the arcuate laying mandrel 120 and the arcuate pressurizer 180 form complementary arcs.

[0037] In one embodiment, the preform 170 is heated in a pressurizer 180, which operates as a dedicated station with a full-length pulse corresponding to the length of a half-cylinder section of the machine body. Therefore, an assembly line for laying can be present before and after the pressurizer 180, with the upper and lower half-cylinder sections connected in series on the assembly line. When the lower half-cylinder section is downstream of the upper half-cylinder section, it receives each type of work before the corresponding upper half-cylinder section. For example, the lower half-cylinder section may harden before the upper half-cylinder section, or receive a frame before the upper half-cylinder section, etc. In one embodiment, the upper and lower half-cylinder sections are co-cured in a series pressurizer, but the lower half-cylinder section exits the pressurizer and enters the assembly line first. In one embodiment, two half-cylinder sections are processed simultaneously by the same pressurizer 180. Laying mandrels 120 for the half-cylinder sections are arranged in series and sealed together or independently within the pressurizer 180 and processed simultaneously.

[0038] A controller 197, including a processor 197-1 and a memory 197-2, manages the operation of various components described herein (e.g., heaters 122 / 182, pressure system 190, pressurizer 180, etc.) to perform the methods described herein. In one embodiment, the controller 110 is implemented as custom circuitry, or as a hardware processor or some combination thereof that executes programmed instructions stored in memory.

[0039] Will target Figure 2 Further details regarding the operation of the assembly line system 100 are discussed. For this embodiment, it is assumed that the laying mandrel 120 receives the preform 170, and the preform 170 is sealed to the laying mandrel 120 via an application liner 160. Thus, the preform 170 is ready to harden into the composite part 714.

[0040] Figure 2 This is a flowchart illustrating a method for hardening prefabricated components using an illustrative embodiment of an operational assembly line system. (See reference) Figure 1 The steps in method 200 are described in the assembly line system 100, but those skilled in the art will understand that method 200 can be performed in other systems. Not all steps in the flowcharts described herein are included, and other steps not shown may be included. The steps described herein may also be performed in an alternative order. Furthermore, although the steps herein are described with respect to a half-cylinder section, they can be applied to any suitable bow section of the fuselage, such as a full-cylinder section, a quarter-cylinder section, or other section dimensions. In other embodiments, the pressurizer is sized to harden any suitable structure, such as flanges, beams, frames, floor beams, stabilizers, doors, etc. In this case, the insulating shield 188 of the pressurizer is sized and shaped to complement the profile of the laying mandrel 120 used for these components, and a peripheral seal 150 is used to seal the laying mandrel 120 to the pressurizer 180. In one embodiment, one or more airbags 199 are placed at the preform 170 prior to sealing (optional step 200-1). These airbags 199 structurally support one or more hollow interiors 170-1 of the prefabricated component 170.

[0041] Step 201 includes sealing the liner 160 on top of the preform 170 to the laying mandrel 120. This includes securing the liner 160 to the preform 170 with tape, suction adhesion, vacuum sealing, or other means while preventing airflow across the liner 160 to the preform 170. Step 202 includes advancing the laying mandrel 120 carrying the preform 170 in the processing direction 179. This may include driving the laying mandrel 120 via an AGV 130 or advancing the laying mandrel 120 via a track 132 connected to the pressurizer 180. In one embodiment, the laying mandrel 120 has advanced in the processing direction 179 through multiple laying stations and a preparatory station where the preform 170 is sealed to the laying mandrel 120. This may include driving the laying mandrel 120 into the pressurizer 180 after sealing the liner 160 to the laying mandrel 120. In such an implementation, the liner 160 itself functions as a vacuum bag for the preform 170.

[0042] Step 204 includes aligning the laying mandrel 120 for insertion into the pressurizer 180, which has an inner surface 186 that follows the profile 162 of the preform 170 and is complementary to the profile 162 of the preform 170. This may include positioning the laying mandrel 120 such that driving the laying mandrel 120 in the processing direction 179 results in the laying mandrel 120 being inserted into the pressurizer 180 via inlet 722. Thus, unlike a pressurizer that defines all the walls / boundaries of a pressure chamber itself, the pressurizer 180 in method 200, together with the laying mandrel 120 and any peripheral seals 150, gap seals 124, and / or shrouds 128, forms a pressure chamber 187. The seals and / or shrouds engage with a pressurizer shroud 188, which may have a longitudinal opening at the plant floor.

[0043] In step 206, the AGV 130 (or trailer or manual trolley) drives the laying mandrel 120 into the pressurizer 180 via inlet 722 in the processing direction 179, thereby nesting the preform 170 into the inner surface 186 of the pressurizer 180. This may include aligning the peripheral seal 150 with a complementary feature 185 (e.g., a groove or protrusion) at the inner surface 186; and engaging the peripheral seal 150 with the complementary feature 185 at the inner surface 186 to form an airtight boundary. In other embodiments, an airtight seal is formed without requiring the complementary feature 185 by carefully determining the dimensions of the peripheral seal 150. Because the inner surface 186 follows the contour 162, driving the laying mandrel 120 into the pressurizer 180 results in a gap 310 of less than 25.4 cm (10 inches) (e.g., less than 5.08 cm (2 inches)) between the inner surface 186 of the pressurizer 180 and the contour 162 of the preform 170. An airtight seal can be achieved via compression of a flexible coating or lining at the peripheral seal 150, which occurs when the peripheral seal 150 is driven into the complementary feature 185 of the pressurizer 180. In other embodiments, pairs of laying mandrels 120 are placed in series within the pressurizer 180. For example, pairs of laying mandrels 120 carrying separate half-cylinder segments (which will subsequently be joined into a complete cylinder segment after the half-cylinder segments have hardened and demolded) can be placed in series within the pressurizer 180 such that one laying mandrel 120 is downstream of the other within the pressurizer 180. The vacuum bag 717 can be sealed to the laying mandrel 120 before the laying mandrel 120 is sealed into the pressurizer 180 (optional step 207).

[0044] In step 208, the laying mandrel 120 is sealed within the pressurizer 180. This may include sealing the gap 310 between the laying mandrel 120 and the pressurizer 180 at either or both ends (e.g., inlet 722 and outlet 724) along the processing direction 179. The seal may include sealing the gap with tape or with a solid clamping plate (not shown) mediating between the inner surface 186 and the laying mandrel 120. In some embodiments, the seal may include a gap seal 124 that seals the gap 310 between the laying mandrel 120 and the pressurizer 180 after the laying mandrel 120 has slid into the pressurizer 180. In one embodiment, the periphery 121 of the laying mandrel 120 is sealed to the inner surface 186 of the pressurizer 180 (optional step 209). In embodiments where multiple laying mandrels 120 are placed in the compressor (e.g., in series), each laying mandrel 120 may seal a separate inlet (e.g., inlet 722 or outlet 722) (or a portion thereof) of the compressor 180. When the laying mandrels 120 are arranged in series, each may be individually sealed, or the laying mandrels 120 may utilize a series sealing / joining technique (e.g., one laying mandrel 120 forms an upstream seal with the compressor 180, while another laying mandrel 120 forms a downstream seal with the compressor 180). After sealing is complete, the laying mandrels 120 define the lower boundary of the compressor 180 (i.e., the lower boundary of the pressure chamber 187 at the compressor 180). In one embodiment, the laying mandrels 120 are sealed within an arcuate gap 310 in the compressor 180, including a sealing preform 170 and an inner surface 186 of the compressor 180.

[0045] Step 210 includes curing the preform 170 into a composite part 714 by applying heat and pressure within the autoclave 180. For thermosetting preforms, this includes heating the preform 170 to a curing temperature and applying pressure to solidify the preform 170 into a desired shape. For thermoplastic preforms, this may include: raising the temperature of the preform 170 to the melting temperature of the thermoplastic material within the preform 170; solidifying the preform 170 under pressure; and cooling the preform 170 until it hardens / solidifies into the composite part 714. Curing the preform 170 may include: activating a heater 122 disposed below the preform 170 (e.g., below the layup surface 123) in the layup mandrel 120; and / or activating a heater 182 disposed outside the inner surface 186 in the autoclave 180. The heaters 182 and / or 122 may include a resistive heater 126, an electromagnetically responsive sensor 127, etc. During hardening, one or more air bladders 199 may support one or more hollow interiors 170-1 of the preform 170 to prevent compaction caused by pressure applied by the pressurizer 180 (optional step 211).

[0046] After the composite part 714 has hardened, the press 180 is opened, and the laying mandrel 120 can travel out of the press 180 via the outlet 724 in the processing direction 179 to accept further work. Step 212 includes removing the liner 160, performing any desired post-hardening finishing or machining, and demolding the composite part 714. The composite part 714 then undergoes further work (e.g., installing a frame on the composite part 714, installing a window on the composite part), and the laying mandrel 120 is cleaned.

[0047] Figure 3 This is a perspective view of a preform 170 being inserted into a pressurizer 180 (e.g., under an insulating cover 188 of the pressurizer 180) in an exemplary embodiment. Figure 3 The diagram illustrates how the laying mandrel 120 forms the boundary of the press 180 in the processing direction 179, and also illustrates a peripheral seal 150 interlocking with the press 180. A gap seal 124 locks into the shroud 188 of the press 180 to seal the end of the laying mandrel 120 in place. That is, the gap seal 124 bridges the gap between the laying mandrel 120 and the press 180 (e.g., at inlet 722 and outlet 724). Figure 3 (Not shown in the image) to seal the pressure chamber 187.

[0048] also, Figure 3 An example is illustrated by an arcuate gap 310 between the inner surface 186 of the laying mandrel 120 and the pressurizer 180, which remains narrow (i.e., less than 25.4 cm (10 inches)) along the entire profile 162 of the preform 170. In other words, the volume between the laying mandrel 120 and the pressurizer 180 is designed to be kept minimal to eliminate the amount of enclosed space that must be heated and / or pressurized during operation. This reduction in stored energy significantly reduces safety management methods and system complexity compared to conventional pressurizers. As desired, this reduced volume provides opportunities for zoned or localized control of heating and pressurization.

[0049] Figure 4 This is a perspective view of a press 180 in an exemplary embodiment, wherein a laying mandrel 120 has been inserted into the press 180. In this embodiment, a single laying mandrel 120 has been placed in the press 180. However, in other embodiments, multiple laying mandrels 120 may be placed in the press 180 for one-time curing.

[0050] and Figure 4 The view arrow 5A corresponds to Figure 5AA laying mandrel 120 is shown prior to laying while awaiting entry into the pressurizer 180. The laying surface 123 of the laying mandrel 120 defines a profile 162, and the laying mandrel 120 includes a heater 122 beneath the laying surface 123. Figure 5B In the middle, the laying has been completed, and the laying mandrel 120 has been covered by the prefabricated part 170 and the liner 160.

[0051] Figure 5C This is an exemplary implementation. Figure 4 End view of the heat press 180, and with Figure 4 The view arrow 5C corresponds to this. Figure 5C This indicates that the gap 310 between heaters 122 and 182 is sealed by a cover 500 disposed between the laying mandrel 120 and the pressurizer 180. The cover 500 is annular in shape and may include a rigid tool or flexible component that provides thermal insulation to and seals the pressurizer 180. In this embodiment, the pressurizer 180 forms the upper boundary 512 of the pressure chamber 510, while the laying mandrel 120 (or a liner or preform molded thereto) forms the lower boundary 514 of the pressure chamber 510. A seal may be applied in region 5E to form a pressure chamber 187.

[0052] Figure 5D This is a view of additional laying mandrels 560 and pressurizer 550 for the flange in an exemplary embodiment. In this embodiment, the laying mandrel 560 is inserted into the pressurizer 550, which includes a support 552, a lower wall 554, and an upper wall 556. A preform 580 is laid onto the contour 562 of the laying mandrel 560, and a liner 570 covers the preform 580. The upper wall 556, the support 552, and the liner 570 together form a pressure chamber 590 for hardening the preform 580. A peripheral seal 592 forms the boundary between the inlet and outlet pages of the pressure chamber 590. For components of different sizes, the peripheral seal 592 conforms to the laying mandrels of different sizes for those components.

[0053] Figure 5E Various sealing schemes for the compressor 180 in exemplary embodiments are described, and compared with... Figure 5CThis corresponds to region 5E. In the first arrangement 500-10 depicted on the left, the seal 500-40 directly contacts the compressor wall 500-30 and the liner 500-50, which contacts the mandrel surface 500-20. In the second arrangement 500-12, the seal 500-40 directly contacts the liner 500-50, which itself directly contacts the compressor wall 500-30. The seal 500-40 also directly contacts the mandrel surface 500-20. In the third arrangement 500-14, the seal 500-40 independently bridges the compressor wall 500-30 and the mandrel surface 500-20, and the liner 500-50 terminates before reaching the seal 500-40.

[0054] Figure 6 This is a side view of an exemplary embodiment including a laying mandrel 610 for sealing an extended region within the pressurizer. The laying mandrel 610 can be used to facilitate the manufacture of a fuselage section with a cross-section or length smaller than other fuselage sections manufactured via the pressurizer. The laying mandrel 610 itself has a length L corresponding to the length of the pressurizer and includes extended regions 620 and 630 having height H (and / or cross-sectional arc) corresponding to the inlet / outlet of the pressurizer. Therefore, extended regions 620 and 630 can be sealed to the pressurizer because the laying mandrel 610 is sized to match the pressurizer, regardless of the size of the hardened preform. Furthermore, the laying region 640 is sized to be a preform profile smaller than other preforms used in the pressurizer. Therefore, the laying region 640 can exhibit a smaller diameter, height, or length than the pressurizer, but this is compensated for by the dimensions of the laying mandrel 610.

[0055] Figure 7 This is a top view of the pressurizer and preparation station in an exemplary embodiment. Figure 7 An example is a laying mandrel 710, which receives a preform 170 and a liner 716 and / or a vacuum bag 717 at a preparation station 718. The laying mandrels 710 are arranged in series for insertion into a pressurizer 720, which has an inlet 722 at a first location and an outlet 724 at a second location, the inlet 722 and outlet 724 being separated by a distance in the processing direction 779. In one embodiment, the pressurizer 720, inlet 722, and outlet 724 are all arcuate. These processes can also be utilized, and the geometry can be modified as needed to facilitate the manufacture of flanges, beams, ribs, or frames. The pressurizer 720 forms part of an arcuate pressure chamber, which is achieved by inserting the laying mandrel 710 into the pressurizer 720 and sealing the laying mandrel 710 in place.

[0056] After exiting the pressurizer 720, the laying mandrel 710 advances to a removal station 730 to perform the removal and / or vacuum removal of the liner 716, at which the composite part 714 is demolded from the laying mandrel 710. The laying mandrel 710 and liner 716 are then cleaned and returned to the beginning of the manufacturing line to receive a new preform 170 of the composite part 714. The composite part 714 continues in the processing direction 779 for post-curing treatments to become an aircraft (e.g., fastener reception, window mounting, etc.). This process ensures that the laying mandrel 710 and liner 716 can be reused quickly and efficiently without creating waste and without requiring a large amount of space on the factory floor.

[0057] Figures 8 to 11 This is a flowchart illustrating other techniques for operating the laying mandrel and complementary pressurizer in an exemplary embodiment. (The following is a separate section:) Figure 1 These methods are described in the pressure heat pump 180. Figure 8 A method 800 for sealing a pressurizer 180 is illustrated. The method includes driving or inserting a laying mandrel 120 into the pressurizer 180 in a processing direction 179 in step 802, and sealing the inlet (optionally, outlet 724) of the pressurizer 180 to a closed state via a seal 124 mounted on the laying mandrel 120 in step 804. Sealing the inlet 722 to a closed state may include clamping the seal 124 into the pressurizer 180 (optional step 806). Thus, according to the above processing, the laying mandrel 120 is positioned within a desired distance (e.g., gap 310) of the pressurizer 180 (e.g., the shroud 188 of the pressurizer 180), such that an air bladder 199 at the laying mandrel 120 can receive pressure from the pressurizer 180, and the periphery 121 of the laying mandrel 120 is sealed to the pressurizer 180 to form a pressure chamber 187, which is then pressurized.

[0058] In another embodiment, the method further includes heating the preform 170 at the laying mandrel 120 via a heater 182 at the pressurizer 180 and / or heating the preform 170 at the laying mandrel 120 via a heater 122 at the laying mandrel 120. In other embodiments, the method further includes securing the preform 170 to the laying mandrel 120 by sealing the edge of the liner 160 to the laying mandrel 120. In yet another embodiment, the laying mandrel 120 is driven into the pressurizer 180 to form a pressure chamber 187 between the laying mandrel 120 and the pressurizer 180. This involves bringing together three separate elements (peripheral seal 150, liner 160, and pressurizer 180) to form the pressure chamber 187, and then removing several of the components when curing is complete. In yet another embodiment, the method further includes driving the laying mandrel 120 out of the pressurizer 180 via an outlet 724 in a processing direction 179. In another embodiment, the sealing inlet 722 includes sealing the arcuate gap 310 between the laying mandrel 120 and the pressurizer 180, thereby forming a thermal insulation barrier (optional step 808). The concepts discussed herein can be used for any suitable composite material parts, such as winglets, ribs, beams, and / or frames for aircraft fuselages. In such an embodiment, the shroud 188 of the pressurizer 180 is sized (i.e., size and shape) to fit the profile of the laying mandrel 120 (e.g., ...). Figure 5D The profile 562 is complementary, and a preform 170 has been placed on the laying mandrel 120. This complementarity allows the laying mandrel 120 itself to form the boundary of the pressurizer 180 and allows the peripheral seal 150 to be used to seal the pressurizer 180 and the laying mandrel 120 together.

[0059] Figure 9A method 900 for forming a pressure chamber 187 at a pressurizer 180 is described. The method includes: in step 902, driving a laying mandrel 120 into the pressurizer 180 in a processing direction 179; in step 904, forming a pressure chamber 187 having boundaries defined by the laying mandrel 120 and the pressurizer 180; and in step 905, inflating one or more air bladders 199 at a preform 170 laid on the laying mandrel 120 via pressure from the pressure chamber 187. The air bladders 199 support the hollow interior 170-1 of the preform 170 to prevent compaction. The method 900 also includes, in step 906, hardening the preform 170 at the laying mandrel 120 into a composite material part 714. The hardened preform 170 may include heating the preform 170 using a heater 122 at the laying mandrel 120 and / or a heater 182 at the compressor 180 (optional step 912). In other embodiments, the hardened preform 170 may include pressurizing a pressure chamber 187 using heated gas from a pressure system 190 at the compressor 180 (optional step 914). Method 900 further includes removing the laying mandrel 120 in step 908.

[0060] In other embodiments, the laying mandrel 120 is driven via an autonomous guided vehicle (AGV) 130, a trolley, wheels, or the like. In other embodiments, method 900 further includes demolding the composite material part 714 from the laying mandrel 120 (optional step 910).

[0061] In another embodiment, the pressurizer 180 forms a first boundary of the pressure chamber 187, the laying mandrel 120 forms a second boundary of the pressure chamber 187, and the peripheral seal 150 forms a third boundary. In another embodiment, the pressure chamber 187 is arcuate, and forming the pressure chamber 187 includes sealing the arcuate gap 310 between the laying mandrel 120 and the pressurizer 180 (as well as the longitudinal edge) (see...). Figure 8 Step 804 in the document. In yet another embodiment, sealing the arcuate gap 310 includes forming a thermally insulating (and pressure-retaining) barrier (see step 804 in the document). Figure 8 Step 808 in the middle.

[0062] Figure 10A method 1000 for sealing a pressurizer 180 is illustrated. The method includes: in step 1002, driving a laying mandrel 120 into the pressurizer 180 in a processing direction 179 (e.g., by AGV, on a track, manually, etc.); and in step 1004, heating a preform 170 at the laying mandrel 120 via a heater 122 disposed in the laying mandrel 120 and a heater 182 disposed in the pressurizer 180. Heating the preform 170 may include passing a driving current through a resistance heater 126 at the laying mandrel 120 and the pressurizer 180 (optional step 1006), or applying an electromagnetic field to a sensor 127 at the laying mandrel 120 and the pressurizer 180 (optional step 1008). In another embodiment, the preform 170 is heated via pressurized and heated gas drawn into a pressure chamber 187 of the pressurizer 180. In other embodiments, heating the preform 170 includes raising the temperature of the preform 170 to the curing temperature of the thermosetting resin within the preform 170 (optional step 1010), or heating the preform 170 includes raising the temperature of the preform 170 to the melting temperature of the thermoplastic resin within the preform 170 (optional step 1012), and then cooling the preform 170 to below the melting temperature.

[0063] In other embodiments, method 1000 further includes securing the preform 170 to the laying mandrel 120 by sealing the edge of the liner 160 to the laying mandrel 120. After the preform 170 has hardened, method 1000 may further include driving the laying mandrel 120 out of the pressurizer 180 in the processing direction 179. Furthermore, prior to heating, method 1000 may include sealing the gap 310 between the laying mandrel 120 and the pressurizer 180 with a thermal insulation barrier (e.g., a seal). The laying mandrel 120 is sized to be withdrawn from the pressurizer 180 via travel in the same processing direction 179 as the laying mandrel 120 is inserted into the pressurizer 180. Additionally, the laying mandrel 120 forms the lower boundary of the chamber 187 of the pressurizer 180 upon insertion into it.

[0064] Figure 11A method 1100 for sealing a pressurizer 180 in an exemplary embodiment is described. Method 1100 includes: in step 1102, driving a laying mandrel 120 into the pressurizer 180 in a processing direction 179 (e.g., via an AGV 130, via a guide rail, via a manual trolley, etc.); and in step 1104, sealing the laying mandrel 120 to the pressurizer 180 via seals 124 / 150, thereby forming a pressure chamber 187 defined by the laying mandrel 120 and the pressurizer 180. Method 1100 further includes: in step 1106, hardening a preform 170 at the laying mandrel 120 into a composite material part 714; and in step 1108, driving the laying mandrel 120 out of the pressurizer 180 in the processing direction 179. The autoclave 180 operates as a port between the pre-curing / cleanroom environment 177 and the post-curing environment (e.g., assembly area 178).

[0065] In other embodiments, the laying mandrel 120 is driven via an autonomous guided vehicle (AGV) 130. Method 1100 may also include demolding the composite part 714 from the laying mandrel 120 (optional step 1110). In one embodiment, the hardened preform 170 includes heating the preform 170 using a heater 122 at the laying mandrel 120 and / or a heater 182 at the autoclave 180 (see [link to previous embodiment]). Figure 9 Step 912). In one embodiment, the laying mandrel 120 is driven into the pressurizer 180 to form a pressure chamber 187 between the laying mandrel 120 and the pressurizer 180 (i.e., after the peripheral seal 150 and / or other seals are in place). In other embodiments, the laying mandrel 120 is driven out of the pressurizer 180 in the processing direction 179, thereby transferring the laying mandrel 120 outside the cleanroom environment 177. That is, during laying and preparation, the laying mandrel 120 is held in the cleanroom environment 177 and then moved into the pressurizer 180, which forms the boundary between the cleanroom environment 177 and a non-cleanroom environment (e.g., assembly area 178). After curing is complete, the laying mandrel 120 is advanced from the pressurizer 180 into the non-cleanroom environment, where demolding and finishing take place. Then, the laying mandrel 120 is cleaned and returned to the cleanroom environment 177 to receive the preform 170 of another composite part 714.

[0066] In one embodiment, sealing the laying mandrel 120 to the pressurizer 180 includes sealing the arcuate gap 310 between the laying mandrel 120 and the pressurizer 180 (see [link]). Figure 8 Step 804 in the process. Sealing the bow gap 310 may include forming a thermal insulation barrier between the pressurizer 180 and the laying mandrel 120 (see step 804 in the process). Figure 8Step 808).

[0067] Figure 12 A method 1200 for sealing a pressurizer 180 in an exemplary embodiment is depicted. Method 1200 includes, in step 1202, moving a preform 170 on a laying mandrel 120 from a cleanroom 177 to align with the pressurizer 180. In one embodiment, a liner 160 is placed over the preform 170 and conforms to the laying mandrel 120. Step 1204 includes sealing the laying mandrel 120 to the pressurizer 180. In one embodiment, this results in a pressure chamber 187 between the liner 160 and the pressurizer 180. The pressure chamber 187 is bounded on one side by the pressurizer 180 and on the other side by the liner 160. Method 1200 also includes, in step 1206, hardening the preform 170 into a composite part 714 within the pressurizer 180 and in step 1208, removing the laying mandrel 120 from the pressurizer 180. When the laying mandrel 120 leaves the pressurizer 180, it completely leaves the cleanroom environment 177 and enters the assembly environment 178, where the demolding and finishing of the final composite part 714 are performed.

[0068] Figure 13 A method 1300 for removing a preform 170 from a cleanroom 177 according to an exemplary embodiment is depicted. The method includes, in step 1302, moving the preform 170 on a laying mandrel 120 from the cleanroom 177 to align it with a pressurizer 180, and in step 1304, sealing the laying mandrel 120 to the pressurizer 180 with a peripheral seal 150. Sealing the laying mandrel 120 to the pressurizer 180 creates a pressure chamber 187 surrounding the preform 170. Method 1300 further includes processing the preform 170 within the pressurizer 180 in step 1306. Processing the preform 170 may include curing the preform 170 (optional step 1310), pressurizing the pressure chamber 187 formed by the laying mandrel 120 and the pressurizer 180 (optional step 1312), or other processing actions. Method 1300 also includes, in step 1308, allowing the laying mandrel 120 to leave the pressurizer 180 and enter a non-clean room (e.g., assembly area 178).

[0069] In the following examples, additional processes, systems, and methods are described in the context of a pressurizer in a continuous assembly line environment.

[0070] Referring more specifically to the accompanying drawings, one can see... Figure 14 The aircraft manufacturing and maintenance methods 1400 shown are as follows: Figure 15Embodiments of this disclosure are described within the context of the aircraft 1402 shown. In the early production process, method 1400 may include the specification and design 1404 of the aircraft 1402 and material procurement 1406. During production, the manufacturing of components and sub-assemblies of the aircraft 1402 and system integration 1410 are performed. Thereafter, the aircraft 1402 may be inspected and delivered 1412 for entry into service 1414. Upon entry into service by the customer, the aircraft 1402 is scheduled for routine maintenance and overhaul 1416 (which may also include modifications, refits, refurbishments, etc.). The equipment and methods implemented herein may be used during any or more suitable phases of production and maintenance described in method 1400 and / or aircraft 1402 (e.g., airframe 1418, system 1420, interior 1422, propulsion system 1424, electrical system 1426, hydraulic system 1428, environmental system 1430) (e.g., specifications and design 1404, material procurement 1406, component and sub-assembly manufacturing 1408, system integration 1410, verification and delivery 1412, service 1414, maintenance and overhaul 1416).

[0071] Each process of method 1400 may be performed or executed by a system integrator, a third party, and / or an operator (e.g., a customer). For the purposes of this description, a system integrator may include, but is not limited to, any number of aircraft manufacturers and main system subcontractors; a third party may include, but is not limited to, any number of suppliers, subcontractors, and vendors; and an operator may be an airline, leasing company, military entity, service organization, etc.

[0072] like Figure 15 As shown, an aircraft 1402 produced using method 1400 may include an airframe 1418 and an interior 1422 having multiple systems 1420. Examples of systems 1420 include one or more of a propulsion system 1424, an electrical system 1426, a hydraulic system 1428, and an environmental system 1430. Any number of other systems may be included. Although examples from aerospace are shown, the principles of this disclosure can be applied to other industries such as the automotive industry.

[0073] As mentioned above, the equipment and methods implemented herein can be used during any one or more stages of production and maintenance as described in method 1400. For example, components or sub-assemblies corresponding to component and sub-assembly manufacturing 1408 can be made or manufactured in a manner similar to the production of components or sub-assemblies during the service of aircraft 1402. Additionally, one or more equipment implementations, method implementations, or combinations thereof can be utilized during sub-assembly manufacturing 1408 and system integration 1410, for example, by significantly accelerating the assembly of aircraft 1402 or reducing the cost of aircraft 1402. Similarly, one or more equipment implementations, method implementations, or combinations thereof can be utilized during the service of aircraft 1402 (e.g., but not limited to maintenance and overhaul 1416). For example, the techniques and systems described herein can be used for material procurement 1406, component and sub-assembly manufacturing 1408, system integration 1410, service 1414 and / or maintenance and overhaul 1416 and / or can be used for airframe 1418 and / or interior 1422. These technologies and systems can even be used in system 1420, including, for example, propulsion system 1424, electrical system 1426, hydraulic system 1428 and / or environmental system 1430.

[0074] In one embodiment, the part forms part of the airframe 1418 and is manufactured during component and subassembly manufacturing 1408. The part can then be assembled into the aircraft in system integration 1410 and utilized in service 1414 until wear renders it unusable. Then, during maintenance and overhaul 1416, the part can be discarded and replaced with a newly manufactured part. To manufacture the new part, the components and methods of the present invention can be utilized throughout component and subassembly manufacturing 1408.

[0075] Any of the various control elements (e.g., electrical or electronic components) shown in the figures or described herein can be implemented as hardware, a processor implementing software, a processor implementing firmware, or some combination thereof. For example, an element can be implemented as dedicated hardware. A dedicated hardware element may be referred to as a “processor,” a “controller,” or some similar term. When provided by a processor, these functions may be provided by a single dedicated processor, a single shared processor, or multiple separate processors, some of which may be shared. Furthermore, the explicit use of the terms “processor” or “controller” should not be construed as exclusively referring to hardware capable of executing software, and may implicitly include, but is not limited to, digital signal processor (DSP) hardware, network processors, application-specific integrated circuits (ASICs) or other circuits, field-programmable gate arrays (FPGAs), read-only memory (ROM) for storing software, random access memory (RAM), non-volatile memory, logic devices, or some other physical hardware component or module.

[0076] Additionally, control elements can be implemented as instructions executable by a processor or computer to perform the functions of that element. Some examples of instructions are software, program code, and firmware. When executed by a processor, instructions operate to instruct the processor to perform the functions of the element. Instructions can be stored on a processor-readable storage device. Some examples of storage devices are digital or solid-state memories, magnetic storage media such as disks and magnetic tapes, hard drives, or optically readable digital data storage media.

[0077] Illustrative, non-exclusive examples illustrate background techniques useful for understanding the invention, as described in the following paragraphs.

[0078] According to one aspect of this disclosure, a method (200) for hardening a preform (170) into a composite material part (714) is disclosed, the method comprising the following steps:

[0079] Align (204) the laying mandrel (120) carrying the preform (170) for insertion into the pressurizer (180), the pressurizer (180) having an inner surface (186) complementary to the profile (162) of the preform (170); and

[0080] The laying mandrel (120) is sealed (208) in the pressure heatr (180).

[0081] Optionally, the method further includes the following steps:

[0082] In the processing direction (179), the laying mandrel (120) is driven (206) into the press (180), thereby nesting the preform (170) into the inner surface (186) of the press (180).

[0083] Alternatively, driving the laying mandrel (120) (206) into the pressurizer (180) results in a gap (310) of less than 25.4 cm (10 inches) between the inner surface (186) of the pressurizer (180) and the profile (162) of the preform (170).

[0084] Optionally, the method further includes the following steps:

[0085] The preform (170) is hardened (210) into a composite part (714) by applying heat within a pressurizer (180). Optionally, hardening (210) the preform includes applying heat via a heater (122) disposed below the preform (170) in a laying mandrel (120).

[0086] Optionally, the hardened (210) preform (170) includes the application of heat via a heater (182) located outside the inner surface (168) in a pressurizer (180).

[0087] Optionally, the autoclave (180) forms the boundary (192) between the cleanroom environment (177) and the assembly environment (178).

[0088] Alternatively, after sealing the liner (160) to the laying mandrel (120), the laying mandrel is sealed in the pressurizer (180).

[0089] Optionally, the method further includes the following steps:

[0090] After sealing (207) the vacuum bag (717) in the laying mandrel (120), the laying mandrel (120) is sealed in the pressurizer (180).

[0091] Optionally, sealing (208) the laying mandrel (120) in the pressurizer (180) includes sealing the arcuate gap (310) between the sealing preform (170) and the inner surface (186) of the pressurizer (180). Optionally, sealing (208) the laying mandrel (120) in the pressurizer (180) includes sealing (209) the periphery of the laying mandrel (120) on the inner surface of the pressurizer (180).

[0092] Optionally, a mandrel (120) is laid to form the lower boundary (514) of the chamber of the heat press (180).

[0093] Optionally, the method further includes the following steps:

[0094] An airbag (199) is provided at the preform (170) (200-1) to structurally support the hollow interior (170-1) of the preform (170).

[0095] Optionally, the method further includes the following steps:

[0096] The hollow interior (170-1) of the precast component (170) is supported (211) to prevent compaction caused by pressure applied by the heat press (180).

[0097] According to one aspect of this disclosure, a portion of an aircraft (1402) assembled according to the method (200) in any of the foregoing examples is disclosed.

[0098] According to one aspect of this disclosure, a non-transitory computer-readable medium (197-2) containing programming instructions is disclosed, which, when executed by a processor (197-1), are operable to perform a method of hardening a preform (170) into a composite material part (714), the method comprising the following steps:

[0099] Align the laying mandrel (120) carrying the preform (170) for insertion into the pressurizer (180), the pressurizer (180) having an inner surface (186) complementary to the profile (162) of the preform (170); and

[0100] The laying mandrel (120) is sealed in the pressure heat exchanger (180).

[0101] Optionally, the method further includes the following steps:

[0102] In the processing direction (179), the laying mandrel (120) is driven into the press (180), thereby nesting the preform (170) into the inner surface (186) of the press (180). Optionally, driving the laying mandrel (120) into the press (180) results in a gap (310) of less than 25.4 cm (10 inches) between the inner surface (186) of the press (180) and the contour (162) of the preform (170).

[0103] Optionally, the method further includes the following steps:

[0104] The preform (170) is hardened into a composite part (714) by applying heat within a pressurizer (180). Optionally, the hardening of the preform (170) includes applying heat via a heater (122) disposed below the preform (170) in a laying mandrel (120). Optionally, the hardening of the preform (170) includes applying heat via a heater (182) disposed outside the inner surface (168) in the pressurizer (180).

[0105] Optionally, the autoclave (180) forms the boundary (192) between the cleanroom environment (177) and the assembly environment (178).

[0106] Optionally, the method further includes the following steps:

[0107] The laying mandrel (120) is driven out of the pressurizer (180) in the processing direction (179).

[0108] Optionally, the method further includes the following steps:

[0109] After sealing the liner (160) into the laying mandrel (120), the laying mandrel (120) is sealed into the autoclave (180).

[0110] Optionally, the method further includes the following steps:

[0111] After sealing the vacuum bag (717) in the laying mandrel (120), the laying mandrel (120) is sealed in the pressurizer (180).

[0112] Optionally, the laying mandrel is sealed into the pressurizer, including the arcuate gap (310) between the sealing preform and the inner surface of the pressurizer, and the periphery (121) of the laying mandrel is sealed to the inner surface of the pressurizer.

[0113] Optionally, the mandrel is laid to form the lower boundary (514) of the chamber (187) of the heat exchanger.

[0114] Optionally, the method further includes the following steps:

[0115] An airbag (199) is installed at the prefabricated part to structurally support the hollow interior (170-1) of the prefabricated part.

[0116] Optionally, the method further includes the following steps:

[0117] The hollow interior (170-1) of the supporting preform (170) is protected against compaction caused by pressure applied by the pressurizer.

[0118] According to one aspect of this disclosure, a portion of an aircraft (1402) assembled according to a method stored on a computer-readable medium (197-2) according to any of the above examples is disclosed.

[0119] According to one aspect of this disclosure, a system (100) for hardening a preform (170) into a composite material part (714) is disclosed, the system comprising:

[0120] A laying mandrel (120) having a laying surface (123) defining the outline (162) of a preform (170); and

[0121] The pressurizer (180) is sized to receive the laying mandrel (120) such that the laying mandrel (120) forms the boundary of the chamber (187) of the pressurizer and includes an inner surface (186) that is complementary to the profile (162) of the laying mandrel (120).

[0122] Optionally, the laying mandrel (120) also includes a heater (122) disposed below the laying surface (123).

[0123] Optionally, the pressure heat exchanger (180) also includes an insulating cover (188).

[0124] Optionally, the spacing between the inner surface (186) and the profile (162) is less than 25.4 cm (10 inches).

[0125] According to one aspect of this disclosure, a part of manufacturing an aircraft (1402) using any of the systems (100) described in the foregoing examples is disclosed.

[0126] According to one aspect of this disclosure, a method (1300) for removing a prefabricated component (170) from a cleanroom (177) is disclosed, the method comprising the following steps:

[0127] Remove the prefabricated part (170) on the laying mandrel (120) from the clean room (177) (1302);

[0128] Seal (1304) the laying mandrel (120) to the heat press (180);

[0129] The preform (170) is processed (1306) within the heat press (180); and

[0130] The laying mandrel (120) is removed from the press (180) (1308) and thus enters the assembly environment (178) which is separate from the clean room (177).

[0131] Optionally, removing (1302) the preform (170) on the laying mandrel (120) includes moving the laying mandrel (120) to align with the pressurizer (180).

[0132] Optionally, sealing (1304) the laying mandrel (120) to the pressurizer (180) includes sealing the corrugated gap (310) between the laying mandrel (120) and the pressurizer (180).

[0133] Optionally, the laying mandrel (120) is sealed (1304) in the pressurizer (180) to form a pressure chamber (187), in which the preform (170) is hardened.

[0134] According to one aspect of this disclosure, a portion of manufacturing an aircraft (1402) according to any of the methods (1300) in the foregoing examples is disclosed.

[0135] According to one aspect of this disclosure, a device in the form of a pressure heat exchanger (180) is disclosed, the device comprising:

[0136] Inner surface (186); and

[0137] A wavy gap (310) is defined by an inner surface (186) having dimensions corresponding to the dimensions of the laying mandrel (120).

[0138] Optionally, the pressurizer (180) also includes a heater (182) that heats the preform (170) disposed at the laying mandrel (120).

[0139] According to one aspect of this disclosure, a portion of an aircraft (1402) is disclosed using the equipment described in any of the foregoing examples.

[0140] According to one aspect of this disclosure, an apparatus in the form of a laying mandrel (120) is disclosed, the apparatus comprising:

[0141] The paved surface (123) defines the outline (162) of the preform (170);

[0142] A first seal (150) that seals the laying mandrel (120) to the pressurizer (180) when the laying mandrel (120) is pushed into the pressurizer (180); and

[0143] The second seal (124) seals the arcuate gap (310) between the laying mandrel (120) and the pressurizer (180) after the laying mandrel (120) slides into the pressurizer (180).

[0144] Optionally, the laying mandrel (120) also includes a heater (122) disposed below the laying surface (123), the heater (122) heating the preform (170) disposed at the laying mandrel (120).

[0145] According to one aspect of this disclosure, a portion of an aircraft (1402) is disclosed using the equipment described in any of the foregoing examples.

[0146] According to one aspect of this disclosure, a method (900) for forming a pressure chamber (187) at a pressure heat exchanger is disclosed, the method comprising the following steps:

[0147] The laying mandrel (120) is driven (902) into the pressurizer (180) in the processing direction (179);

[0148] Forming (904) a pressure chamber (187) having a boundary defined by a laying mandrel (120), a pressure heat exchanger (180) and a peripheral seal (150);

[0149] The precast component (170) at the location where the mandrel (120) is laid is hardened (906) into a composite material part (714); and

[0150] Remove (908) and lay mandrel (120).

[0151] Optionally, the step of laying the mandrel 120 is performed via an autonomous guided vehicle (AGV) 130 using a drive (902).

[0152] Optionally, the method further includes the following steps:

[0153] Demolding (910) of the composite material part (714) from the laying mandrel (120).

[0154] Optionally, the hardened (906) preform (170) includes a heater (122) used at the laying mandrel (120) to heat (912) the preform (170).

[0155] Optionally, the hardened (906) preform includes heating (912) the preform with a heater (182) at the autoclave (180).

[0156] Optionally, hardening the preform (906) (170) includes pressurizing (914) the pressure chamber (187) using a pressure system (190). Optionally, the method further includes the following steps:

[0157] The air bladder (199) at the preform (170) is inflated (905) by pressure from the pressure chamber (187), wherein the air bladder (199) supports the hollow interior (170-1) of the preform (170) to prevent compaction.

[0158] Optionally, forming (904) the pressure chamber (187) includes sealing (804) the arcuate gap (310) between the laying mandrel (120) and the pressure heat exchanger (180). Optionally, sealing (804) the arcuate gap (310) includes forming (808) a thermal insulation barrier.

[0159] According to one aspect of this disclosure, a portion of an aircraft (1402) assembled according to the method (900) in any of the foregoing examples is disclosed.

[0160] According to one aspect of this disclosure, a system (100) is disclosed, the system comprising:

[0161] A heat press (180) comprising a hollow portion (189);

[0162] A laying mandrel (120) is defined for laying an area (640) of the preform (170) and is sized to facilitate insertion into the hollow portion (189) of the pressurizer (180), thereby defining a pressure chamber (187) for hardening the preform (170) into a composite part (714); and

[0163] A seal (124, 150) closes the pressure chamber (187) by bridging the gap (310) between the laying mandrel (120) and the pressure heat exchanger (180).

[0164] Optionally, the system also includes:

[0165] An autonomous guided vehicle (AGV) (130) drives a laying mandrel (120) into the hollow section (189).

[0166] Optionally, both the laying mandrel (120) and the pressurizer (180) include heaters (122, 182) for curing the preform (170) into a composite part (714).

[0167] Optionally, the system also includes:

[0168] A pressure system (190) pressurizes the pressure chamber (187).

[0169] Optionally, the heaters (122, 182) include a resistance heater (126).

[0170] Optionally, the heater (122, 182) includes a sensor (127).

[0171] Alternatively, the pressure chamber (187) is arc-shaped.

[0172] Optionally, the autoclave (180) forms part of the boundary (192) of the cleanroom environment (177).

[0173] Optionally, the laying mandrel (120) is arc-shaped.

[0174] Optionally, the pressurizer (180) also includes a vent (183) for driving heated air into a pressure chamber (187) formed between the laying mandrel (120) and the pressurizer (180).

[0175] According to one aspect of this disclosure, a part of manufacturing an aircraft (1402) using any of the systems (100) described in the foregoing examples is disclosed.

[0176] According to one aspect of this disclosure, a method (1300) for removing a prefabricated component (170) from a cleanroom (177) is disclosed, the method comprising the following steps:

[0177] Move the precast component (170) on the laying mandrel (120) from the clean room (177) to align it with the autoclave (180);

[0178] The laying mandrel (120) is sealed (1304) to the heat press (180) using a peripheral seal (150);

[0179] The preform (170) is processed (1306) within the heat press (180); and

[0180] The laying mandrel (120) is moved from the heat press (180) (1308) into the non-clean room (178).

[0181] Optionally, processing (1306) the preform (170) includes curing (1310) the preform (170).

[0182] Optionally, processing (1306) the preform (170) includes pressurizing (1312) the pressure chamber (187) formed by the laying mandrel (120) and the pressurizer (180).

[0183] According to one aspect of this disclosure, a portion of an aircraft (1402) assembled according to the method (1300) described in the foregoing example is disclosed.

[0184] According to one aspect of this disclosure, a method (800) for sealing a heat exchanger (180) is disclosed, the method comprising the following steps:

[0185] Drive (802) in the processing direction (179) to lay the mandrel (120) into the pressurizer (180); and

[0186] The inlet (722) of the pressure heat exchanger (180) is sealed (804) to a closed state by a seal (124) installed at the laying mandrel (120).

[0187] Optionally, sealing the inlet (722) (804) includes clamping (806) the seal (124) to the pressure heat exchanger (180).

[0188] Optionally, the method further includes the following steps:

[0189] The preform (170) at the mandrel (120) is heated by the heater (182) at the pressurizer (180).

[0190] Optionally, the method further includes the following steps:

[0191] The preform (170) at the laying mandrel (120) is heated (1004) by the heater (122) at the laying mandrel (120).

[0192] Optionally, the method further includes the following steps:

[0193] The liner (160) is sealed (201) on top of the preform (170) to the laying mandrel (120).

[0194] Optionally, the step of driving (802) the laying mandrel (120) into the pressurizer (180) forms a pressure chamber (187) between the laying mandrel (120) and the pressurizer (180).

[0195] Optionally, the method further includes the following steps:

[0196] The laying mandrel (120) is driven (1108) out of the pressurizer (180) in the processing direction (179).

[0197] Optionally, the sealing (804) inlet (722) includes an arcuate gap (310) between the sealing (804) laying mandrel (120) and the pressure heat exchanger (180).

[0198] Optionally, sealing the (804) inlet (722) includes forming a (808) thermal insulation barrier.

[0199] According to one aspect of this disclosure, a portion of an aircraft (1402) assembled according to the method (800) in any of the foregoing examples is disclosed.

[0200] According to one aspect of this disclosure, a system (100) is disclosed, the system (100) comprising:

[0201] A heat press (180), which is defined as a hollow portion (189) for receiving a laid mandrel (120); and

[0202] The laying mandrel (120) defines a laying area (640) for the preform (170) and includes a seal (124) that seals the gap (310) between the laying mandrel (120) and the pressurizer (180).

[0203] Optionally, the seal (124) is configured to be clamped to the pressure heat exchanger (180).

[0204] Optionally, the system also includes:

[0205] Heater (182), which is located at the pressure heat exchanger (180).

[0206] Optionally, the system also includes:

[0207] Heater (122) is located at the laying mandrel (120).

[0208] Optionally, the system also includes:

[0209] A liner (160) seals the precast component (170) to the laying mandrel (120).

[0210] Alternatively, when the laying mandrel (120) is inserted into the pressurizer (180), the laying mandrel (120) and the pressurizer (180) define a pressure chamber (187) for the preform (170).

[0211] Optionally, the seal (124) is mounted to the laying mandrel (120) via a hinge (125).

[0212] Optionally, the seal (124) is formed in an arc shape.

[0213] Optionally, the seal (124) includes a rigid material segment.

[0214] According to one aspect of this disclosure, a part of manufacturing an aircraft (1402) using any of the systems (100) described in the foregoing examples is disclosed.

[0215] According to one aspect of this disclosure, a method (1000) for sealing a heat exchanger (180) is disclosed, the method comprising the following steps:

[0216] The laying mandrel (120) is driven (1002) into the pressurizer (180) in the processing direction (179); and

[0217] The preform (170) at the laying mandrel (120) is heated (1004) by a heater (122) provided in the laying mandrel (120) and a heater (182) provided in the pressurizer (180).

[0218] Optionally, heating (1004) the preform (170) includes driving (1006) current through a resistance heater (125) at the laying mandrel (120) and the pressurizer (180).

[0219] Optionally, the method further includes the following steps:

[0220] Heating the preform (170) (1004) includes applying an electromagnetic field (1008) to the sensor (127) at the laying mandrel (120) and the pressurizer (180).

[0221] Optionally, heating (1004) the preform (170) includes increasing (1010) the temperature of the preform (170) to the curing temperature of the thermosetting resin within the preform (170).

[0222] Optionally, heating (1004) the preform (170) includes increasing (1012) the temperature of the preform (170) to the melting temperature of the thermoplastic resin within the preform (170).

[0223] Optionally, the method further includes the following steps:

[0224] The liner (160) is sealed on top of the preform (170) to the laying mandrel (120).

[0225] Optionally, the step of driving the laying mandrel (120) (1002) into the pressurizer (180) is formed in the pressure chamber (187) between the laying mandrel (120) and the pressurizer (180).

[0226] Optionally, the method further includes the following steps:

[0227] The laying mandrel (120) is driven (1108) out of the pressurizer (180) in the processing direction (179).

[0228] Optionally, the method further includes the following steps:

[0229] The gap between the mandrel (120) and the pressurizer (180) is sealed with a thermal insulation barrier (804).

[0230] According to one aspect of this disclosure, a portion of an aircraft (1402) assembled according to any of the methods described in the foregoing examples is disclosed.

[0231] According to one aspect of this disclosure, a system (100) is disclosed, the system (100) comprising:

[0232] A pressure heat exchanger (180), which defines a hollow portion (189) for receiving a laid mandrel (120) and includes heaters (122, 182); and

[0233] The laying mandrel (120), which defines a laying area (640) for the preform (170), is sized to be inserted into the hollow portion (189) of the pressurizer (180) and includes a heater (122).

[0234] Optionally, the heater (182) at the pressure heat exchanger (180) and the heater (122) at the laying mandrel (120) include resistance heaters (126).

[0235] Optionally, the heater (182) at the pressurizer (180) and the heater (122) at the laying mandrel (120) include a sensor (127).

[0236] Optionally, the laying mandrel (120) is sized to be withdrawn from the pressurizer (180) via a journey in the same direction (179) as the laying mandrel (120) is inserted into the pressurizer (180).

[0237] Optionally, the system also includes:

[0238] A liner (160) seals the precast component (170) to the laying mandrel (120).

[0239] Alternatively, when the laying mandrel (120) is inserted into the pressurizer (180), the laying mandrel (120) and the pressurizer (180) define a pressure chamber (187) for the preform (170).

[0240] Optionally, the laying mandrel (120) is sized such that when the laying mandrel (120) is inserted into the pressurizer (180), there is a gap (310) of less than 25.4 cm (10 inches) between the pressurizer (180) and the preform (170).

[0241] Optionally, the mandrel (120) is laid in the pressurizer 180 to form the lower boundary (514) of the pressure chamber (187) of the pressurizer (180).

[0242] Optionally, when the laying mandrel (120) is inserted into the pressurizer (180), the laying mandrel (120) and the pressurizer (180) together form a pressure chamber (187).

[0243] According to one aspect of this disclosure, a part of manufacturing an aircraft (1402) using any of the systems (100) described in the foregoing examples is disclosed.

[0244] According to one aspect of this disclosure, a method (1100) for sealing a heat exchanger (180) is disclosed, the method comprising the following steps:

[0245] The laying mandrel (120) is driven (1102) into the pressurizer (180) in the processing direction (179);

[0246] The laying mandrel (120) is sealed (1104) to the pressurizer (180) via a seal (150), thereby forming a pressure chamber (187) defined by the laying mandrel (120) and the pressurizer (180);

[0247] The precast component (170) at the location where the mandrel (120) is laid is hardened (1106) into a composite material part (714); and

[0248] The laying mandrel (120) is driven (1108) out of the pressurizer (180) in the processing direction (179).

[0249] Optionally, the step of laying the mandrel (120) by driving (1102) is performed via an autonomous guided vehicle (AGV) (130).

[0250] Optionally, the method further includes the following steps:

[0251] Demold the composite material part (714) from the laying mandrel (120) (1110).

[0252] Optionally, the hardened (1106) preform (170) includes a heater (122) used at the laying mandrel (120) to heat (912) the preform (170).

[0253] Optionally, the hardened (1106) preform includes heating (912) the preform (17) with a heater (182) at the autoclave (180).

[0254] Optionally, the step of driving the laying mandrel (120) (1102) into the pressurizer (180) is formed in the pressure chamber (187) between the laying mandrel (120) and the pressurizer (180).

[0255] Optionally, the step of driving the laying mandrel (120) (1102) outside the pressurizer (180) in the processing direction (179) transfers the laying mandrel (120) outside the cleanroom environment (177).

[0256] Optionally, sealing (1104) the laying mandrel (120) to the pressurizer (180) includes sealing (804) the arcuate gap (310) between the laying mandrel (120) and the pressurizer (180). Optionally, sealing (1104) the arcuate gap (310) includes forming (808) a thermal insulation barrier.

[0257] According to one aspect of this disclosure, a portion of an aircraft (1402) assembled according to the method (1100) in any of the foregoing examples is disclosed.

[0258] According to one aspect of this disclosure, a system (100) is disclosed, the system (100) comprising:

[0259] The autoclave (180, 720) has an inlet (722) and an outlet (724), the outlet (724) being separated from the inlet (722) by a distance in the processing direction (179, 779). The autoclave (180, 720) forms part of a pressure chamber (187), which is accomplished by inserting a laying mandrel (120, 710) into the autoclave (180, 720) and sealing the laying mandrel (120, 710) in place.

[0260] Optionally, the system also includes:

[0261] Laying mandrels (120, 710) define a laying area (640) for the preform (170) and are sized to be inserted into the pressurizer (180, 720) via an inlet (722) and removed from the pressurizer (180, 720) via an outlet (724). Optionally, the laying mandrels (120, 170) form the boundary (514) of the pressure chamber (187) at the pressurizer (180, 720).

[0262] Optionally, the laying mandrel (120, 710) includes a seal (124) for sealing the arcuate gap (310) between the sealing heat press (180, 720) and the laying mandrel (120, 710). Optionally, the seal (124) is mounted to the laying mandrel via a hinge (125).

[0263] Optionally, the system also includes:

[0264] An autonomous guided vehicle (AGV) (130) drives a laying mandrel (120, 710).

[0265] Optionally, the laying mandrel (120, 710) includes a heater (122) and the pressurizer (180, 720) includes a heater (182) for curing the preform (170) into a composite part (714).

[0266] Optionally, the heaters (122, 182) include a resistance heater (126).

[0267] Optionally, the heater (122, 182) includes a sensor (127).

[0268] Optionally, the system also includes:

[0269] A pressure system (190) pressurizes the pressure chamber (187).

[0270] Optionally, the step of inserting the laying mandrel (120, 710) into the pressurizer (180, 720) forms a pressure chamber (187) between the laying mandrel and the pressurizer (180, 720).

[0271] Optionally, the autoclave (180, 720) forms the boundary (192) of the cleanroom environment (177).

[0272] Optionally, the laying mandrel (120, 710), inlet (722), and outlet (724) are arcuate and form complementary arcuate shapes. Optionally, the pressurizer (180, 720) also includes a vent (183) for driving heated air into a pressure chamber (187) formed between the laying mandrel (120, 710) and the pressurizer (180, 720).

[0273] According to one aspect of this disclosure, a part of manufacturing an aircraft (1402) using any of the systems (100) described in the foregoing examples is disclosed.

[0274] According to one aspect of this disclosure, a system (100) is disclosed, the system (100) comprising:

[0275] The heat press (180, 720) includes:

[0276] The inner surface (186) defines a hollow portion (189) configured to receive a laying mandrel (120, 710) of a preform (170) carrying a composite material part (714) and to be complementary to the profile (162) at the laying mandrel (120, 710).

[0277] The entrance (722) leads to the hollow section (189);

[0278] An outlet (724) leading to the hollow section (189) is separated from the inlet by a distance in the processing direction (179, 799) of the laying mandrel travel; and

[0279] Heaters (122, 182) that process the preform (17) into the composite material part (714);

[0280] as well as

[0281] A pressurization system (190) pressurizes a pressure chamber (187) defined by an inner surface (186), seals (124, 150) and a laying mandrel (120, 710).

[0282] Optionally, the heater (122, 182) includes a resistance heater (126). Optionally, the heater (122, 182) includes a sensor (127).

[0283] Alternatively, the pressure chamber (187) is arc-shaped.

[0284] According to one aspect of this disclosure, a part of manufacturing an aircraft (1402) using any of the systems (100) described in the foregoing examples is disclosed.

[0285] Although specific embodiments have been described herein, the scope of this disclosure is not limited to those specific embodiments. The scope of this disclosure is defined by the following claims.

Claims

1. A method (200) for hardening a preform (170) into a composite material part (714), the method comprising: Align (204) the laying mandrel (120) carrying the preform (170) for insertion into the pressurizer (180), the pressurizer (180) having an inner surface (186) complementary to the profile (162) of the preform (170); and The laying mandrel (120) is sealed into the pressurizer (180), wherein the pressurizer (180) forms the boundary (192) between the cleanroom environment and the assembly environment (178).

2. The method (200) according to claim 1, further comprising: The laying mandrel (120) is driven (206) into the pressurizer (180) in the processing direction (179), thereby nesting the preform (170) into the inner surface (186) of the pressurizer (180).

3. The method (200) according to claim 1 or 2, further comprising: The preform (170) is hardened (210) into a composite material part (714) by applying heat in the pressurizer (180).

4. The method (200) according to claim 1 or 2, further comprising: After sealing the liner (160) and / or vacuum bag (717) into the laying mandrel (120), the laying mandrel is sealed into the pressurizer (180).

5. The method (200) according to claim 1 or 2, wherein, Sealing the laying mandrel (120) into the pressurizer (180) includes sealing the arcuate gap between the preform (170) and the inner surface (186) of the pressurizer (180).

6. The method (200) according to claim 5, wherein, Sealing the laying mandrel (120) into the pressurizer (180) includes sealing the periphery of the laying mandrel (120) to the inner surface of the pressurizer (180).

7. The method (200) according to claim 1 or 2, wherein, The laying mandrel (120) forms the lower boundary (514) of the chamber of the heat press (180), and / or The method further includes: providing (200-1) an airbag (199) at the preform (170) to structurally support the hollow interior (170-1) of the preform (170), and / or The method also includes supporting (211) the hollow interior (170-1) of the preform (170) to prevent compaction caused by the pressure applied by the pressurizer (180).

8. The method (200) according to claim 2, wherein, The laying mandrel (120) is driven (206) into the pressurizer (180) to obtain a gap of less than 25.4 cm, or 10 inches, between the inner surface (186) of the pressurizer (180) and the profile (162) of the preform (170).

9. The method (200) according to claim 3, wherein, Hardening (210) of the preform includes applying heat via a heater disposed below the preform (170) in the laying mandrel (120), and / or Hardening (210) of the preform (170) includes applying heat via a heater located outside the inner surface (186) in the pressurizer (180).

10. A method (1300) for removing a prefabricated component (170) from a cleanroom (177), the method comprising: Remove (1302) the prefabricated part (170) from the clean room (177) and lay the mandrel (120); The laying mandrel (120) is sealed in the heat press (180). The preform (170) is processed (1306) within the heat press (180); and The laying mandrel (120) is removed from the pressurizer (180) (1308) and thus enters the assembly environment (178) separated from the clean room (177).

11. The method (1300) according to claim 10, wherein: Removing the preform (170) from the laying mandrel (120) (1302) includes moving the laying mandrel (120) to align it with the pressurizer (180).

12. The method (1300) according to claim 10 or 11, wherein: Sealing the laying mandrel (120) to the pressurizer (180) includes sealing the corrugated gap between the laying mandrel (120) and the pressurizer (180).

13. The method (1300) according to claim 10 or 11, wherein: The laying mandrel (120) is sealed in the pressurizer (180) to form a pressure chamber (187), in which the preform (170) is hardened.

14. An apparatus for laying mandrels (120), the apparatus comprising: The paved surface (123) defines the outline (162) of the preform (170); A first seal (150) seals the laying mandrel (120) in the pressurizer (180) when the laying mandrel (120) is pushed into the pressurizer (180). as well as The second seal (124) seals the arcuate gap between the laying mandrel (120) and the pressurizer (180) after the laying mandrel (120) is pushed into the pressurizer (180).

15. The device according to claim 14, wherein: The laying mandrel (120) also includes a heater disposed below the laying surface (123), the heater heating the preform (170) disposed at the laying mandrel (120).

16. A system (100) for hardening a preform (170) into a composite material part (714), the system comprising: The device according to claim 14 or 15; as well as A pressurizer (180) is sized to receive the laying mandrel (120) such that the laying mandrel (120) forms the boundary of the pressure chamber (187) of the pressurizer, and the pressurizer includes an inner surface (186) complementary to the profile (162) of the laying mandrel (120).

17. The system according to claim 16, wherein, The pressurizer (180) forms the boundary (192) between the cleanroom environment and the assembly environment (178).

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