47 results about "Advanced composite materials" patented technology

Systems and methods for eliminating carbon dioxide and capturing solid carbon are disclosed. By eliminating carbon dioxide gas, e.g., from an effluent exhaust stream of a fossil fuel fired electric power production facility, the inventive concepts presented herein represent an environmentally-clean solution that permanently eliminates greenhouse gases while at the same time producing captured solid carbon products that are useful in various applications including advanced composite material synthesis (e.g., carbon fiber, 3D graphene) and energy storage (e.g., battery technology). Capture of solid carbon during the disclosed process for eliminating greenhouse gasses avoids the inefficiencies and risks associated with conventional carbon dioxide sequestration. Colocation of the disclosed reactor with a fossil fuel fired power production facility brings to bear an environmentally beneficial, and financially viable approach for permanently capturing vast amounts of solid carbon from carbon dioxide gas and other greenhouse gases that would otherwise be released into Earth's biosphere.

The invention discloses a high-temperature-resistant water-based polyimide sizing agent for carbon fibers, modified carbon fibers, a resin-based composite material of the modified carbon fibers, a preparation method and application of the resin-based composite material, and belongs to the technical field of advanced composite materials. The sizing agent disclosed by the invention is prepared by carrying out condensation polymerization on aromatic dianhydride and monofunctional aromatic amine to generate polyamide acid and then carrying out an ionizing salt formation process. The sizing agent has excellent storage stability and thermal stability, can effectively improve the wettability of the carbon fiber surface, and significantly improves the interface bonding performance of the carbon fiber reinforced polyimide composite material. The sizing agent provided by the invention can remarkably improve the room-temperature and high-temperature interface bonding strength of the carbon fiber reinforced polyimide composite material, and is suitable for the fields of aerospace, high-end equipment manufacturing and the like.

The invention relates to the technical field of power electronic component manufacturing and advanced composite material application, in particular to a 3D inductor based on the Ampere's law and a method thereof. The three-dimensional precise interlocking winding comprises a functional composite framework, a three-dimensional precise interlocking winding and a magnetic core assembly, according to the system, a framework is formed by compositing a heat-conducting insulating substrate and soft magnetic powder, and air gaps between winding layers are physically filled through step-shaped positioning ribs; the core is that a low-thermal-resistance export path is established by utilizing the high heat conduction characteristic of the framework, and a heat conduction mode is converted from coil-to-air to coil-to-framework; the gradient difference between the core temperature and the surface temperature in the coil is effectively reduced through the embedded heat dissipation array, the heat dissipation problem under the high power density is solved, and the device performance is remarkably improved.

The application discloses a method for researching the influence of random hole geometric deviation on the strength of an aircraft wall plate connecting structure, and relates to the field of advanced composite material connection, and comprises the following steps: determining a characterization parameter of hole geometric deviation of a composite material strip-hole laminated plate test piece; establishing a simulation model of a composite material single-nail connecting structure plug-nail connection without hole geometric deviation; based on the characterization parameter and the simulation model of the composite material single-nail connecting structure plug-nail connection without hole geometric deviation, a simulation model of a composite material single-nail connecting structure interference plug-nail process is established; a simulation model of a composite material connecting structure tensile load is established; based on the simulation model of the composite material connecting structure tensile load, a probability distribution graph of the strength change value of the structure is established, and the strength distribution trend under different geometric deviations is determined; and based on the strength distribution trend under different geometric deviations, a new composite material hole making deviation design criterion is constructed. The application can improve the hole making precision of the connecting hole, and reduce the manufacturing difficulty and cost.

The application discloses a phthalonitrile resin with a siloxane chain structure, and the structure is shown in the following formula, wherein x is an integer of 1-50, y is an integer of 5-23, z is an integer of 5-23, and the molar ratio of the siloxane chain grafted with a benzoxazine monomer and the siloxane chain grafted with a phthalonitrile monomer is 1:0.9-1.1.In the application, the phthalonitrile resin takes siloxane as a main chain, and a side chain comprises a substituted benzoxazine structure and a phthalonitrile structure.Compared with a petroleum-based phthalonitrile resin without siloxane, the resin of the application can still maintain high heat resistance after curing, and the processing fluidity is significantly improved, the melt viscosity is reduced, the curing temperature is reduced, the material toughness is effectively improved, and the resin is suitable for fields such as aerospace, advanced composite materials and electronic packaging which have a synergistic requirement for heat resistance and processability.

The invention relates to the field of photoelectric fairing materials, in particular to a multifunctional composite material for a photoelectric fairing. The multifunctional composite material for the photoelectric fairing comprises a substrate, and a microwave shielding layer, an anti-reflection layer, an infrared low-emission layer and a high-temperature protection layer which are sequentially stacked on the substrate. The multifunctional composite material for the photoelectric fairing is an advanced composite material with wide spectrum, high transmittance, low infrared emissivity and strong electromagnetic shielding performance, and can meet the requirements of photoelectric detection and electromagnetic protection of a high-speed aircraft in an extreme environment.

The invention discloses a nanosecond laser precision machining method for a SiCf / SiC composite material, and belongs to the field of laser machining and advanced composite material manufacturing. The method comprises the following steps: carrying out linear ablation or surface ablation on a pretreated SiCf / SiC composite material by adopting nanosecond pulse laser with the wavelength of 355 nm; the laser energy density, the scanning speed, the scanning times, the line overlapping ratio and the scanning path are optimized through the system, and high-precision and low-damage machining is achieved. The core optimization parameters are as follows: the laser energy density is 5.33 J / cm < 2 >, the scanning speed is 200mm / s, the line overlapping rate is 66.58%, and a one-way scanning mode is adopted. Through the combination of experiments and simulation, the mechanism (melting, evaporation, decomposition, and material removal by liquid drop splashing and gas volatilization) of nanosecond laser ablation of SiCf / SiC is disclosed, the heat affected zone, the oxidation phenomenon and the recondensate defect are effectively controlled, the quality and the contour precision of the machined surface are remarkably improved, and the machining precision is improved. The method is suitable for micromachining of key components such as aerospace engine hot end components and medical high-end equipment.

The invention discloses a preparation method of an organic silicon modified boron phenolic resin composite material. The method comprises the following steps: reacting boron phenolic resin with isocyanate propyl alkoxy silane in an organic solvent at 75-85 DEG C in the presence of organic tin dilaurate to prepare organic silicon modified boron phenolic resin; dissolving organic silicon modified boron phenolic resin and hydroxyl-terminated polymethylsiloxane in an organic solvent at room temperature, uniformly mixing, heating to volatilize the organic solvent, adding organic tin dilaurate after the organic solvent is volatilized, uniformly mixing, standing, reacting and defoaming; and then curing at room temperature to obtain the organic silicon modified boron phenolic resin composite material. By means of excellent flexibility and heat resistance of organic silicon and excellent rigidity and ablation resistance of phenolic resin, the prepared material is resistant to high temperature, can be used as an advanced composite material matrix, an organic thermal protection material matrix and the like, and has wide application prospects in thermal protection materials of buildings and cables and thermal protection materials of hypersonic weaponry.

An aerial system includes at least one fuselage and at least one wing assembly having a plurality of pneumatic structural tubes and a plurality of ribs through which each of the plurality of tubes extends. Each tube in the plurality of tubes is arranged adjacent to at least one other tube in the plurality of tubes and each rib in the plurality of ribs has a respective profile such that the respective profiles of the plurality of ribs define at least a portion of a geometry of the wing assembly. A wing skin spans across the plurality of ribs to serve as an exterior wing surface of the wing assembly. The aerial system may additionally include a power plant and / or a wing box to physically interface with a corresponding wing box compartment in the fuselage. Each of the plurality of pneumatic structural tubes is constructed of a piece of advanced composite material, such as an Ultra High Molecular Weight Polyethylene (UHMWPE) Composite Fabric (UCF) material or another advanced composite material.

The invention provides a composite material prefabricated body sewing forming method and system, and relates to the technical field of advanced composite material manufacturing. According to the method, on the basis of joint cooperation of a mechanical arm, a modular stitching head and a control system, selection and area matching of stitching processes are completed by analyzing the local thickness, geometric morphology, curvature change and enhancement direction requirements of a composite prefabricated body, and different stitching processes are adopted in different areas of the same prefabricated body for cooperative stitching. In the forming process, the control system conducts unified planning and coordinated control on the motion trail of the mechanical arm, the action of the sewing head and sewing process parameters, and switching and accurate execution of the sewing process are achieved. The method can effectively meet the three-dimensional reinforced forming requirements of complex curved surfaces and special-shaped composite material preforms, improves sewing consistency, reliability and process flexibility, and is suitable for manufacturing preforms of high-performance composite material structures in the fields of aerospace and the like.

The invention belongs to the technical field of advanced composite materials, and particularly relates to a high-temperature-resistant water-based sizing agent, a preparation method thereof and application of the high-temperature-resistant water-based sizing agent in a carbon fiber reinforced polyimide composite material. The water-based sizing agent is prepared by taking an aromatic triamine monomer, aromatic anhydride and an ionized functional agent as raw materials through a controllable condensation polymerization reaction. The high-temperature-resistant and high-temperature-resistant liquid crystal composition has excellent solubility, high-temperature stability and long-term storage stability, and 5% thermal weight loss temperature is higher than 550 DEG C. The sizing agent can significantly improve the interface bonding strength of carbon fibers and a resin matrix. The water-based sizing agent provided by the invention has the characteristics of high temperature resistance and interface enhancement function, can meet the strict requirements of the aerospace field on the mechanical properties of composite materials such as carbon fiber / polyimide in an extreme thermal environment, and has important application value.

The invention discloses an energy storage-reinforcement integrated rib and a manufacturing method, and relates to the technical field of advanced composite material manufacturing and green building, and the energy storage-reinforcement integrated rib comprises a fiber reinforced composite material rib body. When the FRP rib is used and in the aspect of a product, the FRP rib comprises a hollow tubular bearing framework made of a fiber reinforced composite material, an alkali-resistant anti-corrosion layer formed on the outer surface of the hollow tubular bearing framework and an axial hollow cavity used for containing the replaceable battery unit, a buffer heat conduction layer can be arranged in the cavity, and detachable sealing end covers are arranged at the two ends of the cavity; functions of structural load bearing, environmental corrosion resistance and electric energy storage are integrated. In the aspect of the method, a unique continuous composite pultrusion process is adopted, an alkali-resistant outer layer and a bearing framework are synchronously formed through a hollow mold core, the size and the inner wall quality of a hollow cavity are accurately controlled by utilizing an internal cooling and peelable core mold technology, and a space is reserved for filling of a buffer heat conduction layer.

The invention discloses a preparation method of a regenerated carbon fiber reinforced metal-based composite material, which comprises the following steps: S1, pretreatment of a waste carbon fiber composite material: carrying out three-stage pyrolysis treatment on the waste carbon fiber composite material in an inert gas environment to obtain regenerated carbon fibers; and S2, metal or alloy with excellent physical performance and processability is selected as a base material, metal powder and the regenerated carbon fibers are evenly mixed, the mixture is put into a pressing die to be repressed into a formed blank, the formed blank is put into a heating furnace to be sintered, and a tightly-combined composite material structure is formed. The high-performance carbon fiber reinforced metal-based composite material is successfully prepared through an innovative regenerated carbon fiber surface treatment technology in combination with an advanced composite material preparation process, and a new way is provided for cyclic utilization of carbon fiber resources and improvement of the performance of the composite material.

This invention discloses a method for preparing high aspect ratio boron nitride nanosheets through precursor conversion, belonging to the field of two-dimensional material preparation technology. The method includes the following steps: 1. Uniform blending of a boron nitride precursor and a foaming agent; 2. Programmed temperature foaming and high-temperature sintering of the mixed powder; 3. Liquid-phase fractionation and centrifugation of the sintered powder to prepare high aspect ratio boron nitride nanosheets. This invention achieves high-throughput preparation of boron nitride nanosheets with aspect ratios between 1000 and 3300 through in-situ foaming polymerization by adjusting the type and proportion of the foaming agent. This solves the problems of long processing time, low yield, complex post-processing, and small aspect ratio of the obtained boron nitride nanosheets in traditional boron nitride nanosheet preparation methods, laying the foundation for the industrial preparation of boron nitride nanosheets and their application in the field of advanced composite materials.

The invention discloses a low-dimensional carbon / fiber composite material damping performance optimization preparation method based on interface regulation and control. The method comprises the following steps: step 1, negative pressure impregnation of a nanocarbon macroscopic body; 2, high-speed shearing, mixing and dispersing of the nanocarbon macroscopic body; and step 3, performing interface regulation and control compounding on the carbon fiber fabric and the nano reinforced resin slurry. The core innovation of the method lies in that through gradient compounding of a nanocarbon macroscopic body three-dimensional skeleton and a resin matrix, multi-scale interface structure regulation and control and forming process parameter optimization, a quantitative relation between an interface energy consumption mechanism and the damping performance is established, and synergistic enhancement of the vibration reduction performance and the mechanical performance of the composite material is achieved. According to the invention, full impregnation and uniform dispersion of the nanocarbon macroscopic body in the resin matrix are realized, the problem of obstruction of the nanofiller in the forming process is effectively solved through an interface regulation and control composite process, a composite material laminated board with a controllable structure is formed, and the composite material laminated board is suitable for weight reduction requirements of advanced composite material equipment for aerospace and the like.

The invention discloses an integrated energy storage rib, which relates to the technical field of composite structures and comprises a long-strip-shaped battery core and a packaging protection layer directly formed outside the long-strip-shaped battery core through a fiber winding process, and the long-strip-shaped battery core and the packaging protection layer are combined to form an approximately solid integral component. Preferably, the packaging protection layer is of a multi-layer structure and comprises an insulating buffer layer on the inner layer and a high-strength bearing layer on the outer layer. Through an advanced composite material winding process, fusion of an energy storage element and a structural force bearing element on the microscopic scale is achieved, a traditional building rib material is endowed with the energy storage function, and the structural strength, the interface bonding force, the heat dissipation efficiency and the insulation reliability which are far better than those of a traditional packaging mode are achieved; the integrated energy storage rib is particularly suitable for an intelligent civil engineering structure which needs to integrate the functions of bearing, energy storage, health monitoring and the like.

The present invention proposes a stacked jammer delivery controller with data communication capabilities, comprising a contact interface module, an ignition control module, a communication processing module, and a housing. The controller is capable of two-way communication with jammers and an integrated self-defense system. By adopting a stacked longitudinal structural design, the ignition delivery assembly and the control box are integrated into one, resulting in a lightweight and compact structure that facilitates later functional expansion and disassembly and maintenance. The controller contains a rich set of data communication interfaces, enabling communication with intelligent jammers for detection, maintenance, and management. It can also communicate with the integrated self-defense system to receive and respond to the system's jammer delivery strategies. The stacked modular structural design results in a compact structure that facilitates later functional expansion and disassembly and maintenance. The housing is made of advanced composite materials, resulting in a lightweight design and enhanced environmental adaptability.

The invention relates to a CFRP high-quality laser drilling method cooperatively assisted by hydrochloric acid and a zinc plate, and belongs to the technical field of composite material processing. The method comprises the following steps: S1, pretreating the surface of a sample; s2, mounting a sample and accurately positioning the sample; s3, planning a processing path and setting an aperture; s4, determining process parameters; s5, drilling is carried out according to set parameters; and S6, after machining, the heat affected zone, the roundness, the taper and the inner wall roughness of the through hole are measured. According to the method, the hydrochloric acid solution is used for strengthening heat dissipation and promoting chip discharge, meanwhile, the zinc plate is used for absorbing residual heat and regulating and controlling the appearance of an outlet through the interaction between the zinc plate and laser, and therefore the quality of the through hole is remarkably improved, the taper of the through hole is as low as 0.029, the roughness of the inner wall is only 1.097 m, the roundness of an inlet and the roundness of an outlet are as high as 99.4% and 98.1% respectively, and no thermal damage exists in an outlet area. The process is efficient and stable, high-quality through hole preparation of an advanced composite material can be achieved, the application requirement of the high-end equipment field is met, and good engineering application value is achieved.

The present invention discloses a fiber metal composite laminate and a preparation method thereof, and belongs to the technical field of preparation of advanced composite materials. The present invention first grinds MWCNT, PEG and SiO2 together to obtain MWCNT-STF, and then fills the MWCNT-STF dilution obtained after dissolving the MWCNT-STF into the gaps between fiber fabrics or attaches to the surface of the fiber fabric through ultrasonic impregnation, thereby increasing the friction between fiber fabric yarns, and then stacks the MWCNT-STF / fiber fabric, aluminum plate and adhesive film, and obtains a fiber metal composite laminate after hot pressing. This fiber metal composite laminate has strong anti-penetration ability, strong energy absorption ability and good impact resistance.

The invention relates to the field of instrument and meter technologies and advanced composite material preparation, in particular to a composite material for a measuring pipeline of an electromagnetic flowmeter and a preparation method of the composite material, and the composite material for the measuring pipeline of the electromagnetic flowmeter comprises polytetrafluoroethylene and polyimide. The preparation method comprises the following steps: pretreating polytetrafluoroethylene and polyimide to obtain pretreated polytetrafluoroethylene and polyimide; mixing the pretreated polytetrafluoroethylene and polyimide to obtain a first mixture; granulating the first mixture to obtain a second mixture; and carrying out extrusion injection molding on the second mixture to obtain the composite material for the measuring pipeline of the electromagnetic flowmeter. According to the prepared composite material, the wear resistance of a measuring pipeline lining of the electromagnetic flowmeter is improved, and the stability of the pipeline size is ensured.

The invention relates to a low-cost and high-precision unmanned aerial vehicle control surface integral forming method, and belongs to the technical field of advanced composite material manufacturing. According to the method, the core force bearing part of the control surface of the unmanned aerial vehicle breaks through the traditional step-by-step manufacturing mode of composite material forming and metal piece post-assembly, and integrated compression molding of the metal connecting piece and the composite material control surface is achieved. Through the technical means of precise positioning of the metal connecting piece, compression molding and forming integration of the composite material and the like, integrated forming of the metal connecting piece and the composite material is achieved, and the problem that traditional control surface manufacturing needs separate part manufacturing, machining and manual assembling is solved. The prepared unmanned aerial vehicle control surface has the advantages of being high in qualified rate, high in forming precision, high in production efficiency, low in cost, good in structural integrity and the like.

The invention discloses an advanced composite material three-dimensional weaving digital forming island and a preparation technological process. A preform forming auxiliary island is provided with a three-dimensional weaving machine, a digital flexible guiding three-dimensional weaving forming machine and three-dimensional weaving equipment; the preform forming main island is provided with a three-dimensional needling and sewing forming machine; and the prefabricated body curing island is provided with RTM curing equipment which comprises curing stations such as mold pressing curing and autoclave curing. And automatic material transfer systems are arranged between the auxiliary forming island and the main forming island, between the main forming island and the curing island and between the curing island and the component storage island. The system is further provided with a central control system for processing and deciding acquired data, orderly scheduling material transfer and ensuring efficient and orderly operation of the whole system. All the areas are wrapped by sensing information flow and material flow to form an island type layout, efficient, accurate and flexible preparation of large, complex and multifunctional advanced composite material preforms can be achieved, the preparation period of the preforms can be effectively shortened, and the product quality can be improved.

The invention discloses a composite flapping wing structure based on a chiral / anti-chiral core layer, relates to the technical field of advanced composite material structure design, metamaterial structure design and application and the like, and aims to solve the problems of stress concentration, complex driving, low efficiency and the like in underwater flapping wing propulsion. The structure comprises chiral / reverse chiral core layers, flexible skin layers and the like which are alternately arranged, the chiral / reverse chiral core layer realizes uniform stress distribution during deformation through negative Poisson's ratio characteristics, and the flexible skin layer enhances shear transfer and reduces flow resistance. Compared with a traditional connecting rod flapping wing mechanism, the structure driving efficiency and reliability are improved, the driving structure is simplified, the deformation characteristic of the flapping wing mechanism is more flexible, and therefore the flapping wing mechanism can adapt to the more complex and multi-mode working environment.

The invention belongs to the technical field of advanced composite materials, and discloses a high-hardness and high-toughness recyclable CFEP-SiC composite material and a preparation method thereof. The CFEP-SiC composite material is prepared from the following raw materials in percentage by weight: 55.7 to 58.5 percent of T800-grade carbon fiber, 17.5 to 18.9 percent of bisphenol A type epoxy resin, 7.0 to 7.6 percent of alicyclic epoxy resin, 7.0 to 7.6 percent of a DDS curing agent, 0.9 to 1.1 percent of a CTBN prepolymer, 3.4 to 3.8 percent of alpha-SiC nanoparticles, 1.6 to 2.0 percent of beta-SiC whiskers, 0.25 to 0.35 percent of hydrophobic gas-phase SiO2, 0.35 to 0.45 percent of a silane coupling agent, 0.25 to 0.35 percent of a dispersing agent, 0.15 to 0.25 percent of a microcapsule catalyst and 1.6 to 2.0 percent of core-shell structure particles. Through collaborative design of multi-scale toughening, multi-dimensional reinforcing and controllable recycling functional units and in combination with a resin transfer molding (RTM) process, the hardness and toughness of the composite material are remarkably improved, the composite material is endowed with the recoverable characteristic, and the application requirements of the aerospace field are met.

This invention provides a silicon-chain acrylic liquid crystal photosensitive resin and its preparation method. A compound containing mesocrystalline units with -OH terminals, EHC, and catalyst 1 are mixed and reacted to obtain solution A. NaOH is added dropwise to solution A to remove the water generated in the reaction. After continuing the reaction, the product is filtered, and excess EHC is removed from the filtrate to obtain solution B. Solution B is mixed with methanol / acetone, and the resulting crystals are washed, filtered, and dried to obtain liquid crystal epoxy resin C. C is mixed with an inhibitor and reacted, then acrylic acid and catalyst 2 are added dropwise to react and obtain acrylic liquid crystal photosensitive resin D. D is mixed with 1,1',3,3'-dimethyldisiloxane, and a solvent, catalyst 3, and inhibitor are added to carry out a hydrosilylation reaction to obtain silicon-chain acrylic liquid crystal photosensitive resin E. The silicon-chain acrylic liquid crystal photosensitive resin provided by this invention can be widely used in artificial muscles, actuators, shape memory, smart devices, and some highly elastic advanced composite materials.

A debris shield may include one or more microfoam units, the one or more microfoam units comprising internal voids. The debris shield may include one or more phase change materials positioned within the internal voids. The debris shield may include an advanced composite material layer positioned over a surface of the one or more microfoam units.

The invention discloses high-toughness thermosetting polyimide resin as well as a preparation method and application thereof. The preparation method comprises the following steps: carrying out a reaction on a dianhydride monomer containing a benzobisnorbornene cyclobutane structure, an aromatic diamine monomer and a phenylacetylene phthalic anhydride end-capping reagent by adopting a one-pot method to obtain a reactant, and carrying out post-treatment to obtain the soluble thermosetting polyimide resin. The structural formula of the soluble thermosetting polyimide resin is # imgabs0 #; according to the invention, the polyimide resin is directly prepared by adopting a one-pot method, not only can the release of small molecule volatile matters in the molding process of the composite material be avoided, but also the dianhydride monomer containing the benzobisnorbornene cyclobutane structure is adopted, so that the prepared thermosetting polyimide resin has high solubility, heat resistance and mechanical toughness after being imidized; advanced composite materials prepared from the resin can be widely applied to the field of aerospace.

The invention discloses an advanced resin-based composite material with a wear-resistant surface and a preparation method thereof, the composite material comprises two layers of carriers and a filler, the filler is located between the two layers of carriers, and the carriers are one of a fabric, a non-woven fabric and a felt. The filler is one or more of graphite powder, polyether-ether-ketone powder, ultra-high molecular weight polyethylene powder, polytetrafluoroethylene powder, carbon fiber powder, polyformaldehyde powder, glass fiber powder, aramid fiber powder and polyamide powder. Different functional materials are introduced to the surface of the composite material to construct a layer-by-layer wear-resistant structure, namely a surface wear-resistant functional layer; in the friction process, all functional materials have a synergistic effect through stress transmission and other forms, surface energy loss is reduced, the surface friction reduction effect is achieved, and therefore the use efficiency of the materials is improved, and the service life of the materials is prolonged. Meanwhile, the original forming process and performance of the composite material are not changed, and integration of high wear resistance and structural performance of the surface of the advanced composite material is achieved.

The present application relates to the field of photoelectric fairing material, and particularly relates to a multifunctional composite material for photoelectric fairing. The multifunctional composite material for photoelectric fairing comprises a substrate and a microwave shielding layer, an antireflection layer, an infrared low-emissivity layer and a high-temperature protection layer which are sequentially stacked on the substrate. The multifunctional composite material for photoelectric fairing is an advanced composite material with wide spectrum, high transmittance, low infrared emissivity and strong electromagnetic shielding performance, and can meet the requirements of photoelectric detection and electromagnetic protection of high-speed aircraft in extreme environments.

The invention relates to the technical field of autoclave self-inspection, in particular to an advanced composite material autoclave self-inspection system, which comprises a high-precision pressure sensor, a high-precision pressure sensor, a high-precision pressure sensor, a high-precision pressure sensor and a high-precision pressure sensor, the valve control unit consists of a plurality of valve control ends; the control unit is used for recording the pressure numerical value Pn monitored by the high-precision pressure sensor every unit time T, calculating the pressure difference value Pan in the unit time T, and judging that the autoclave possibly leaks when Pan is greater than q; when Pan is larger than q, the control unit is further used for controlling the valve control units to be completely opened and then closed again, then controlling the negative pressure assembly of the autoclave to be started to drive the internal air pressure of the autoclave to recover to the initial value P0, and recalculating the pressure difference value Pcn; according to the system, secondary verification is carried out after possible leakage is judged for the first time, the misjudgment probability is reduced, the accuracy and reliability of system judgment are enhanced, and the production efficiency and the quality assurance level of advanced composite materials are improved.