224 results about "Aerospace vehicle" patented technology

The invention belongs to the technical field of solid-liquid phase change heat dissipation, and discloses a memory alloy-based phase change expansion buffer structure, which comprises an elastic structure, a supporting structure, a thin wall, a cavity, a flaring, an electronic device, a heat sink, fins, a connecting structure and a phase change material, the thin wall is made of shape memory alloy and separates the internal cavity and the external phase-change material, the internal cavity is communicated with the external environment through the flaring, and in the flying process of the aerospace vehicle, external airflow flows into the flaring to take away heat stored by the phase-change material continuously. Based on the shape memory function of the memory alloy, additional space expansion buffering can be provided for the phase change material when the temperature changes, and stress damage caused by phase change expansion is avoided. The memory alloy thin wall and the elastic supporting structure are combined, the structure is simple, no moving part exists, circulating work in the high-temperature environment and the low-temperature environment can be achieved, local hot spots caused by internal gap movement of the phase change material in the circulating phase change process are reduced, and heat transfer deterioration is avoided.

The invention relates to the field of additive manufacturing nano precipitated phase reinforced refractory high-entropy alloys, in particular to an additive manufacturing nano precipitated phase reinforced refractory TiNbVAlSix high-entropy alloy. The high-entropy alloy comprises the following chemical components by atomic percent: 45-55% of Ti; 15%-25% of Nb; v, 15%-25%; 8%-15% of Al; and 0-9% of Si. The alloy is prepared through a laser directional energy deposition additive manufacturing method, precipitation of a nano Ti5Si3 phase at the grain boundary and in grains is promoted through addition of the Si element, microstructure characteristics of a disordered BCC phase, an ordered B2 phase and the nano Ti5Si3 phase are formed, and the content of the nano Ti5Si3 phase is in direct proportion to the content of the Si element. The high-entropy alloy has the performance characteristics of light weight and high strength, can meet the requirements of part of aerospace parts, and has important value for development and application of TiNbVAl and related light refractory high-entropy alloy systems.

The invention relates to the technical field of aircrafts, and discloses a three-dimensional interactive aircraft full-process automatic pneumatic simulation cloud platform and method, which can automatically adjust boundary layer grid division parameters and extrapolate to form volume grids according to the characteristics and simulation requirements of different aircrafts by constructing a friction velocity analysis model of aircraft wall surface airflow, and improve the simulation efficiency of the aircrafts. According to the method, the flow condition of the boundary layer of the aircraft can be truly reflected through grid division, accurate division of the aerodynamic shape boundary layer body grid of the aircraft under the condition of the needed incoming flow simulation parameters is achieved, and therefore the simulation efficiency is improved while the accuracy of the aerodynamic simulation result is remarkably improved. Besides, through modular design, distributed architecture and intelligent algorithm optimization, construction of a full-process automatic pneumatic simulation cloud platform from geometric model uploading to simulation result generation is realized, efficiency and precision of pneumatic analysis are remarkably improved, and the method is suitable for pneumatic design research and development requirements of carriers such as unmanned aerial vehicles and aerospace crafts.

The invention discloses a 3D printing self-adaptive wing design method based on generative artificial intelligence, and relates to the crossing field of 3D printing and artificial intelligence. In order to solve the technical problems of complex manufacturing, low reliability and large weight of a traditional process in the prior art, the technical scheme provided by the invention comprises the following steps: pre-training a large language model to obtain a trained basic model; receiving self-adaptive wing structure design parameters input by a user and generating a design scheme script; calling three-dimensional modeling software, automatically establishing a wing three-dimensional model based on the design scheme script, and outputting a model file; calling simulation analysis software, performing wing performance simulation analysis based on the model file, and outputting analysis result data; and calling the basic model to carry out design scheme evaluation and iterative optimization based on the analysis result data until an optimized model file meeting the design requirement is generated. The method can be applied to intelligent design and automatic manufacturing of self-adaptive wing structures of aerospace crafts.

The invention relates to an industrial CT composite material defect reconstruction method based on an unsupervised neural network. The method comprises the following steps: carrying out industrial CT shooting to obtain a cross section two-dimensional image of a composite material component; an unsupervised model for converting an industrial CT composite material image into a defect model for reconstruction and discrimination is constructed, sampling is performed through a multi-scale sampling model, a channel attention mechanism is introduced for weight adjustment, and a multi-scale residual module is introduced for reconstruction; constructing a joint loss function for calculating the unsupervised model; training the constructed unsupervised model by using a data set, wherein a loss function is used for updating parameters; and inputting a to-be-detected industrial CT composite material image into the model, so that three-dimensional reconstruction of the defects of the composite material can be completed. According to the method, the defects of the composite material are reconstructed with high precision, nondestructive testing of the composite material is achieved, and the method can be used for structural health monitoring and defect detection of aerospace vehicles such as airplanes and rockets.

The invention relates to a micro-nano mullite reinforced zirconium oxide inorganic fiber, the phase of the micro-nano mullite reinforced zirconium oxide inorganic fiber is composed of two phases of tetragonal zirconium oxide and mullite, the fiber diameter is 0.1-1.5 [mu] m, and crystal phase stability, microstructure stability and fiber flexibility are maintained at the temperature from room temperature to high temperature of 1400 DEG C. The preparation method comprises the following steps: taking acidic aluminum sol, silica sol, zirconium sol and yttrium salt as metal sources, taking a high-molecular polymer as a spinning auxiliary agent, obtaining micro-nano mullite reinforced zirconium oxide precursor fibers through an electrostatic spinning technology, and carrying out heat treatment on the precursor fibers to obtain the mullite reinforced zirconium oxide inorganic fibers. The invention has the advantages of wide raw material source, cheap raw materials, stable system, good spinnability, high solid content, simple preparation process and the like. The prepared inorganic fiber has good high-temperature stability and flexibility in a wide temperature range from room temperature to high temperature of 1400 DEG C, and has application prospects in the fields of aerospace vehicle flexible heat insulation felts, high-temperature crystal growing furnaces and other high-temperature flexible heat insulation and heat preservation.

The invention relates to a welding seam reinforcing structure for a stainless steel storage tank, and belongs to the technical field of aerospace carrier propellant storage tank structures. A first box bottom, a first short shell, a cylinder section, a second short shell and a second box bottom; the first box bottom and the second box bottom are each of a hemispherical shell structure. The first short shell, the second short shell and the barrel section are all of barrel section structures; the first short shell, the barrel section and the second short shell are horizontally and coaxially butted in sequence; the first box bottom is coaxially mounted at the axial outer end of the first short shell; the second box bottom is coaxially mounted at the axial outer end of the second short shell; the opening end of the first box bottom extends into the first short shell, and the outer wall of the first box bottom is in butt joint with the inner wall of the first short shell. The opening end of the second box bottom extends into the second short shell, and the outer wall of the second box bottom is in butt joint with the inner wall of the second short shell. The problem that the welding performance of reinforcing materials cannot be weakened through partition thickness design is solved, and the purposes of high performance, low cost manufacturing and the like of the stainless steel storage box are achieved.

The invention relates to a multi-branch diffusion box bottom force transmission structure, and belongs to the technical field of aerospace vehicle propellant storage box structures, the multi-branch diffusion box bottom force transmission structure comprises a thrust ring base plate, a thrust ring outer ring, a thrust ring butt joint plate and a thrust ring inner ring, the thrust ring base plate is of a flat plate structure with a hole in the center, the thrust ring outer ring is of a cylindrical structure, and the inner diameters of the upper end face and the lower end face are different; the thrust ring butt joint plate is arranged on the upper end face of the thrust ring outer ring and used for being connected with an engine rack; the thrust ring inner ring is of a cylindrical structure with the upper end face and the lower end face being the same in inner diameter and is arranged in a cavity of the thrust ring outer ring, one end of the thrust ring inner ring is connected with the thrust ring butt-joint plate, and the other end of the thrust ring inner ring is connected with the thrust ring base plate which is connected with the storage tank bottom. The thrust ring structure is additionally arranged on the outer side of the bottom of the storage box, the thrust ring is connected with the bottom of the storage box through multiple branches, thrust transmitted by an engine rack is diffused to a main structure of the bottom of the storage box through the thrust ring, and the effects of saving an engine force transmission section and improving the engine force transmission efficiency are achieved.

The invention provides an aerospace craft discrete trajectory precision reconstruction method based on a variable order, and the method comprises the following steps: calculating the order of a reconstruction model based on a given highest-order dynamic parameter of an aerospace craft discrete trajectory; calculating a coefficient of the reconstruction model; based on a given aerospace craft discrete trajectory, constructing a continuous time model of a flight trajectory; and substituting any moment into the continuous time model of the flight trajectory to obtain trajectory data of the aerospace craft at any moment. According to the method, reconstruction can be completed with higher precision based on given discrete trajectory data, and trajectory continuity is considered; order configuration can be flexibly carried out, and the adaptability to discrete trajectories with different dynamic change rules is improved.

The application relates to the technical field of wave-absorbing composite materials, and particularly discloses a honeycomb sandwich structure high-temperature-resistant wide-frequency wave-absorbing composite material based on Ti3C2T x MXene aerogel and a preparation method of the honeycomb sandwich structure high-temperature-resistant wide-frequency wave-absorbing composite material, the honeycomb sandwich structure high-temperature-resistant wide-frequency wave-absorbing composite material is a multilayer structure, and from outside to inside, the multilayer structure comprises a high-temperature-resistant resin-based composite material wave-transparent skin, a honeycomb structure wave-absorbing layer and a high-temperature-resistant resin-based composite material reflecting skin in sequence, and the honeycomb structure wave-absorbing layer is a composite material honeycomb structure filled with a high-temperature-resistant MXene composite aerogel material.The honeycomb sandwich structure high-temperature-resistant wide-frequency wave-absorbing composite material based on Ti3C2T x MXene aerogel, which uses a MXene composite aerogel material (the density is 2 mg / cm 3 ~15 mg / cm 3 ) and a light composite material honeycomb structure carrier, overcomes the defect that existing wave-absorbing materials are large in density, and has an effective absorption frequency band width of more than 10 GHz when the reflectivity is lower than -10 dB, and can simultaneously meet the requirements of wide-frequency wave-absorbing performance and light weight of wave-absorbing materials for aerospace vehicle equipment.

The invention relates to a nuclear main pump lead-bismuth lubrication guide bearing structure for negative feedback regulation, and belongs to the technical field of systems of nuclear energy, high-temperature industry, energy and chemical industry, scientific research and the like. The bearing structure is internally provided with an even number of cylindrical pipelines and spiral pipelines which are circumferentially arranged, the inner wall of the bearing structure is sequentially provided with a feedback cavity, a high-pressure liquid tank, a liquid return tank and a working cavity in the axial direction, and the two ends of the spiral pipelines are connected with the feedback cavity and the working cavity respectively. The bearing capacity of the lead-bismuth lubrication guide bearing of the nuclear main pump is improved, the leakage problem is solved, and the lead-bismuth lubrication guide bearing is suitable for aerospace vehicle propulsion systems, ocean engineering deep sea equipment and the like.

The invention discloses an MBSE model version pedigree iteration method and system based on a graph theory and a knowledge graph. The method comprises the following steps: constructing an MBSE model of an aerospace craft and mapping the MBSE model into an attribute graph; a directed acyclic graph is adopted to record a version iteration process, management is carried out through a version number system comprising a main version number, a combined version number and a revised version number, and a differential storage strategy is adopted; and performing change detection and merging based on a baseline, accurately identifying changes through a model comparison algorithm including internal attributes, internal relationships, overall relationships and difference analysis, and processing conflicts in collaborative design. According to the method, atomic-scale version control is realized, the problems of missing change traceability, low verification efficiency and multi-baseline conflict are solved, and the efficiency and quality of aerospace craft full-life-cycle model management are improved.

The invention discloses an atmospheric environment simulation method and device for aerospace flight simulation, and relates to the related field of data processing, and the method comprises the steps: carrying out the multi-stage environment construction of a flight test scheme of an aerospace vehicle according to an atmospheric data system tester, and obtaining a multi-stage flight simulation environment; performing a simulation test on the aerospace vehicle to obtain a first test sequence; performing simulation scene variation compensation to obtain a second test sequence; performing multi-dimensional risk prediction on the test scheme to obtain a multi-stage test risk prediction result; and carrying out sensitivity association to obtain a multi-order risk environment sensitive factor, and optimizing a test scheme. The technical problem that the test result is incomplete and inaccurate due to the fact that the environment simulation scene is limited and uncertain factor consideration is lacked in the adaptability test of the aerospace vehicle in different atmospheric environments in the prior art is solved, the flight state of the aerospace vehicle in the complex atmospheric environment is truly and comprehensively simulated, and the test efficiency is improved. And the comprehensiveness and the accuracy of a test result are improved.

Systems, methods, and apparatus for targeting a cloud are provided. A source of a lightning strike is predicted. Furthermore, an aerospace vehicle is operated to dispose a lightning suppression payload at a location associated with the source of the lightning strike.

The application provides a kind of aerospace vehicle assembly workshop intelligent dynamic scheduling method and system, method includes steps S1: by real-time connection assembly workshop central control system to obtain real-time multi-source data;Step S2: training multi-evaluation network coordination safety near end strategy optimization model, optimal control sequence in limited time domain is solved at each sampling time, only the first control action is adopted, the next sampling time is optimized based on last control action and state, after completing all control action optimization, reward model is based on neural network back update;Repeat the above process until convergence;Step S3: the multi-evaluation network coordination safety near end strategy optimization model trained is deployed to carry out workshop state update and rescheduling decision, generate and issue new scheduling plan.The application realizes the real-time response to the abnormal disturbance such as response emergency order, equipment failure, realizes the safe, efficient, flexible dynamic self-adapting scheduling of aerospace vehicle assembly workshop.

The present application relates to a kind of weld reinforcement structure for stainless steel tank, belong to aerospace vehicle propellant tank structure technical field;First tank bottom, first short shell, barrel section, second short shell and second tank bottom;Wherein, first tank bottom and second tank bottom are hemispherical shell structure;First short shell, second short shell, barrel section are barrel section structure;First short shell, barrel section and second short shell are in turn horizontal coaxial butt joint;First tank bottom is coaxially installed at the axial outer end of first short shell;Second tank bottom is coaxially installed at the axial outer end of second short shell;The open end of first tank bottom is inserted into first short shell, and the outer wall of first tank bottom is butt joint with the inner wall of first short shell;The open end of second tank bottom is inserted into second short shell, and the outer wall of second tank bottom is butt joint with the inner wall of second short shell;The present application solves the problem that the welding performance of reinforcing material cannot be reinforced by partition thickness design, realizes the purposes such as high performance, low cost manufacturing of stainless steel tank.

A long range vehicle capable of space travel uses quantum effects such as quantum printing or instantiation to produce consumables during travel. The long range vehicle comprises a transport shell, a propulsor disposed in or on the shell, and at least one Nagel Quantum Effect Device (NQED) operatively coupled to the propulsor, the at least one NQED providing imprinted material to the propulsor.

The present invention relates to the field of aerospace welding technology, and in particular to an aerospace component welding device. The present invention provides an aerospace component welding device that can provide airtight protection for the welding position of an aerospace fuel pipe, and can facilitate accurate positioning and rapid cleaning of the welding position, thereby improving the quality and efficiency of fuel pipe welding. An aerospace component welding device includes a frame and a first protective chamber, etc., wherein the first protective chamber is connected to the upper left portion of the frame. The present invention provides airtight protection through the first protective chamber and the second protective chamber during the welding process, and can quickly position the two sections of the fuel pipe through the positioning wheel, and clean the fuel pipe through the brush rod before welding, thereby achieving the effect of being able to provide airtight protection for the welding position of the aerospace fuel pipe, and being able to facilitate accurate positioning and rapid cleaning of the welding position, thereby improving the quality and efficiency of fuel pipe welding.

A linerless composite tank for a waste or water system on board an aerospace vehicle includes a monolithic tank body having a first composite material co-cured with a second composite material. The first composite material includes a first resin and the second composite material includes a second resin that is different from the first resin. The first composite material forms an innermost surface of the monolithic tank body defining a tank chamber of the monolithic tank body. A method of manufacturing the linerless composite tank includes providing a mold having a desired interior shape of the monolithic tank, applying the first composite material to the mold, applying the second composite material to the mold, and co-curing the first composite material with the second composite material to form the monolithic composite tank.

The application discloses a flexible metal composite skin structure capable of regulating local out-of-plane deformation and belongs to the technical field of metal skin structures. The application introduces a paper-cut structure on the surface of a metal skin, regulates mechanical response by changing characteristic parameters such as a paper-cut pattern and a metal skin thickness, so that the structure has high ductility and small plastic deformation characteristics, and the structure can recover to original deformation after the expansion of a protrusion of a driving device, thereby ensuring the continuity of a wing aerodynamic shape. The application meets the basic requirements of application to a flexible skin of a deformation wing, provides a feasible selection for the fusion of a gasbag anti-icing mechanism and a deformation wing, and is expected to be widely applied in the fields of aircraft deicing, spacecraft deicing and deformation wings.

This invention provides a vertical tail control surface motion mechanism with guide rail limiting and guidance, and an unmanned aerial vehicle (UAV), relating to the field of aerospace vehicle control system technology. The mechanism uses the metal part of the vertical tail connector as the installation reference. A linear servo is hinged and fixed via a servo base. The linear servo push rod is connected to a guide pin. The lower part of the guide pin is embedded in the arc-shaped guide groove of a copper guide rail, and the upper part is hinged to the control surface linkage rocker arm. The control surface linkage rocker arm is rigidly connected to the control surface hinge shaft. This invention uses a copper guide rail to provide full-stroke directional constraint and limiting for the guide pin, significantly compressing the mechanism's motion envelope, adapting to the compact installation space of a thin vertical tail, eliminating transmission backlash, and improving control surface deflection accuracy and motion smoothness. It has the advantages of compact structure, precise operation, resistance to jamming, long service life, and convenient maintenance, and is particularly suitable for the vertical tail rudder control system of small fixed-wing UAVs and light aircraft.

The application discloses a preparation method of a lightweight oxidation-resistant coating on a carbon-based composite material surface, which comprises the following steps: brushing a slurry containing a carbon source on the surface of the carbon-based composite material, solidifying, forming a carbon source transition layer on the surface of the carbon-based composite material, and then performing a molten salt assisted infiltration treatment on the surface of the carbon source transition layer to obtain the lightweight oxidation-resistant coating. The preparation method of the application provides the carbon source for the subsequent process by pretreating the carbon-based composite material, and adds a suitable reinforcing phase to improve the bonding force between the coating and the substrate. Then, the molten salt disproportionation reaction is used to prepare the coating, the thickness and microstructure of the coating are strictly controlled by controlling the infiltration process, and finally, the smooth, uniform and dense lightweight oxidation-resistant carbide ceramic sealing layer is obtained. In the oxidation process, a glassy film is formed to seal the surface oxygen diffusion channel, the short-term ablation resistance is excellent, and the lightweight high-strength requirement of aerospace vehicles can be met.

The present invention relates to a nanocellulose-based high-strength carbon fiber-reinforced polymer composite and a method for manufacturing same and, specifically, to a nanocellulose-based high-strength carbon fiber-reinforced polymer composite, infused with a thermosetting resin containing dispersed nanocellulose to simultaneously enhance strength and lightweight characteristics, and to a method for manufacturing same. The present invention provides the effects of significantly improving tensile strength and impact resistance of a composite by effectively inhibiting crack formation and uniformly distributing stress within the composite. Furthermore, by achieving a weight reduction compared to conventional metallic materials, the present invention can improve the fuel economy and energy efficiency of transportation means, such as automobiles and aerospace vehicles.

The invention discloses a flexible metal composite material skin structure capable of regulating and controlling local out-of-plane deformation, and belongs to the technical field of metal skin structures. The paper-cut structure is introduced to the surface of the metal skin, the mechanical response of the paper-cut structure is regulated and controlled by changing characteristic parameters such as a paper-cut pattern and the thickness of the metal skin, so that the structure has the characteristics of high ductility and small plastic deformation, and the structure can recover to original deformation along with retraction of the driving device after expanding and protruding along with the driving device; and the aerodynamic configuration continuity of the wing is ensured. Basic requirements of flexible skin applied to the deformable wing are met, a feasible choice is provided for fusion of an air bag anti-icing and deicing mechanism and the deformable wing, and the method is expected to be widely applied to the fields of aviation, spacecraft deicing, deformable wings and the like.

The invention relates to a turbulence modeling method suitable for complex flow of an aerospace vehicle compression system, and belongs to the field of aerospace vehicle turbulence modeling. According to the distribution rule of the normalized velocity helicities of the LES flow field at the blade tip of the gas compressor rotor in the aerospace vehicle, constructing a normalized velocity helicities model, namely an h model; according to an LES flow field at the root of a stator of a gas compressor in an aerospace vehicle, a second-order explicit anisotropic Reynolds stress model, namely a Q model, is constructed; according to the h model and the Q model, a novel RANS turbulence model, namely a Wilcox2006k-omega-h-Q model, for reasonably capturing blade tip gap leakage flow and corner separation flow is constructed, and turbulence modeling suitable for complex flow of an aerospace vehicle compression system is completed; according to the method, the novel RANS turbulence model capable of reasonably capturing the blade tip clearance leakage flow and the corner separation flow is constructed, and high-fidelity numerical simulation solution of the internal flow of the compression system of the aerospace vehicle is achieved.

The invention discloses wide-temperature-range silicone rubber-based rubber for aerospace thermal protection, a composite material and a preparation method of the wide-temperature-range silicone rubber-based rubber. According to the invention, three monomers, i.e., methylcyclosiloxane, hexaethylcyclotrisiloxane and phenylene silicon monomer, are subjected to ring opening and condensation copolymerization to obtain polysiloxane macromolecules containing three different chain link structures. A phenylene structure is introduced into a silicon rubber main chain, so that the silicon elastomer main chain is limited to form a volatile cyclic oligomer through a chain back-biting reaction and a chain segment rearrangement exchange reaction, the thermal stability is improved, and the initial decomposition temperature is up to 450.16 DEG C; the regularity of a molecular chain is broken by introducing ethyl, so that the glass-transition temperature is as low as 120.2 DEG C, and no crystallization phenomenon occurs. The base adhesive has excellent cold resistance, radiation resistance, ablation resistance, high temperature resistance and the like, and can be used as the base adhesive to be applied to the aspects of aerospace craft protective coatings, dynamic seal putty adhesives, sealants and the like.

The invention is suitable for the technical field of aerospace aircraft environment control, and provides an environment processing system and method for an aerospace aircraft space, and the system sequentially comprises an air inlet, a first discharge cavity, an airflow channel, a second discharge cavity, a sensing module section and an air outlet in the airflow direction; an electrode I is arranged in the first discharge cavity, a high-voltage electrode in the electrode I is connected to a positive high-voltage power supply, and a grounding electrode is connected to a zero-potential reference; an electrode II is arranged in the second discharge cavity, a high-voltage electrode in the electrode II is connected to a negative high-voltage power supply, and a grounding electrode is connected to a zero-potential reference; the sensing module section is provided with a sensing module for detecting gas components; by adopting the bipolar ground design and through the synergistic effect of the oxidation stage and the reduction stage, air is efficiently treated, meanwhile, the concentration of by-products such as ozone can be effectively controlled, it is ensured that output gas meets the aerospace environment safety standard, and the device is compact in structure and easy to integrate with an existing environment control system.

The application belongs to the field of aerospace coating, and particularly relates to a primer for the outer protective coating of a spacecraft, a preparation method and a use method. The primer comprises the following raw materials in parts by weight: tackifier 2-8 parts, alkyl silicone oil 5-10 parts and diluent 80-90 parts. The primer contains a large amount of inorganic / organic groups, can form a strong chemical bond with the substrate, and improve the adhesion of the coating. Meanwhile, the primer can also have interpenetration synergy with the silicone resin in the coating to form a PIN network structure, further improving the adhesion. In addition, the primer can also be activated to generate silanol under the condition of water molecules, and hydrolysis and bonding with inorganic media to form a firm silicon-oxygen bond. That is, the primer has inorganic / organic dual properties, is applied between organic and inorganic materials, and forms a micro organic-inorganic interface between the two, thereby enhancing the adhesion.

The invention discloses a propulsion system and spaceflight equipment, and relates to the technical field of spaceflight power systems, the propulsion system comprises a nuclear power source, a storage feeding device, an atomization device and an acceleration device, the nuclear power source can supply power to the atomization device and the acceleration device, the storage feeding device is used for storing a magnetic fluid propellant, and the atomization device is used for supplying power to the acceleration device. The storage feeding device communicates with the atomization device, the storage feeding device can convey the magnetic fluid propellant to the atomization device, and the atomization device can atomize the magnetic fluid propellant and convey the magnetic fluid propellant to the acceleration device; the accelerating device can generate a magnetic field and accelerate the magnetofluid propellant in the atomized state. The propelling system and the aerospace equipment are suitable for being used in the environment lacking solar energy, and power is more sufficient.

The application provides a training mold and a design method for 4D printing of a shape memory alloy wing, and belongs to the technical field of aerospace vehicles. The purpose is to solve the problems of insufficient deformation precision, easy damage to the structure caused by stress concentration, long design trial and error period, high cost, and poor consistency of the training effect of components in the prior art. A driving mechanism and an upper mold are installed on a lower mold; the upper mold is provided with a first assigned camber line and a slider track at the top; a driving sleeve is installed in the upper part of a driving rod, and the bottom of the driving sleeve is provided with a slider; a placing platform is arranged on the lower mold, a supporting protrusion is arranged in the middle, a lower base platform is arranged between the placing platform and the supporting protrusion, and the supporting protrusion is provided with a second assigned camber line; and a curved wing is arranged on the base platform. The application solves the problems of insufficient deformation precision, easy damage to the structure caused by stress concentration, long design trial and error period, high cost, and poor consistency of the training effect of components in the prior art.