271 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 belongs to the field of complex equipment system design and verification, and discloses a model-based complex equipment system design and verification integrated method, which takes four layers of'demand-behavior-structure-parameter 'as a framework, combines task scene demands, and constructs a full-process design and analysis method of a reusable space launch vehicle system. The method comprises the following steps: decomposing a complex system from demand analysis, performing parameter calibration and performance verification on a model by combining theoretical and experimental data, constructing a reusable space launch vehicle system model, and performing comprehensive analysis and verification of the system; in combination with a three-dimensional virtual environment and a configuration optimization algorithm of the model, performing rapid optimization on various configurations of the aerospace vehicle, and evaluating feasibility and performance of a design scheme; through bidirectional interaction of design and verification models and communication of system-level design and professional-level design, the problems of design and verification separation, insufficient model collaboration and the like in the prior art are solved, and the efficiency and precision of design and verification of a complex equipment system are improved.

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 belongs to the field of wireless communication, and particularly relates to wireless communication of aerospace crafts, in particular to a differential coding modulation communication method suitable for large Doppler frequency shift. The method comprises the following steps: 1, setting frame structure parameters; 2, framing is carried out according to power control, a synchronization header, a header and a data segment, and a frame structure is generated; step 3, quantizing and de-spreading the received signal to generate a to-be-synchronized data stream; 4, determining a frame synchronization position and a bit synchronization position, calculating frequency offset by using FFT (Fast Fourier Transform), and calculating channel frequency offset to carry out frequency offset compensation; 5, calculating a correlation value after compensating the data stream, and determining a coarse synchronization position of a receiving end frame; and 6, carrying out five-path parallel correlation peak calculation to obtain a data block bit synchronization position, a position ahead of two sampling points, a position lagging of two sampling points, a position lagging of one sampling point and a position ahead of one sampling point.

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.

A method for deicing in a laser sensor window in an aerospace vehicle. A deicing laser beam is transmitted from a laser beam generator in the aerospace vehicle into the laser sensor window in the aerospace vehicle. The deicing laser beam has properties that remove ice from the laser sensor window. A sensor laser beam is transmitted from the laser beam generator through the laser sensor window.

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.

In an example. the present invention provides an airplane or aerospace vehicle system configured with a high intensity pulse laser generation system.

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 discloses application of a composite film with a multi-element and multi-phase structure in surface lubrication of an aerospace vehicle or a nuclear power bearing in a high-temperature environment. The composite film comprises a titanium transition layer, a titanium / molybdenum disulfide / tantalum / tungsten diboride gradient transition layer and a multi-element and multi-phase structure layer which are sequentially formed on the surface of a base body. The multicomponent multiphase structure layer comprises a molybdenum disulfide / tantalum / tungsten diboride composite layer, the molybdenum disulfide / tantalum / tungsten diboride composite layer comprises tantalum nanoparticles, a molybdenum disulfide layer and a tungsten diboride layer, and the tantalum nanoparticles are distributed between the molybdenum disulfide layer and the tungsten diboride layer. The composite film with the multi-element and multi-phase structure shows higher hardness and hardness / elasticity ratio and low friction coefficient and wear rate at the high temperature of 400 DEG C, and meanwhile, the composite film can meet stable lubrication and long-life reliable service of aerospace vehicles and nuclear power bearings under harsh and complex variable working conditions.

The invention discloses an aerospace vehicle rapid response function composite casting mold forming method and device, and belongs to the crossing field of a sand mold 3D printing technology and an integrated die casting technology. According to the method, firstly, a numerical control machining center or sand mold 3D printing equipment is adopted for manufacturing a multi-material composite core mold, then a cut or printed sand mold / core is assembled on a core mold base in a ridge-closing mode, a servo cabin metal mold is driven to be matched with the sand mold core mold through a mold closing locking mechanism, and the whole set of die-casting mold is formed. Secondly, light alloy (magnesium, aluminum, titanium and the like) is smelted at a high temperature, the speed field and the pressure field of high-temperature molten metal mold filling are indirectly controlled by controlling the movement speed of a piston rod, and high-quality castings are obtained through crystallization and solidification under the pressure. The innovatively proposed'metal mold and sand mold 'combined die-casting die can quickly realize the dynamic heat balance of the temperature of the die. According to the aerospace vehicle rapid response function composite casting mold forming method and device, innovative and green development of a light high-strength alloy casting process is promoted.

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.

An aerospace wiring harness inspection system comprises a mobile personal computing device; a camera system connected to the mobile personal computing device, a machine learning model running in the mobile personal computing device; and a controller. The machine learning model is trained to detect anomalies in a set of images of a wiring harness in an aerospace vehicle. The controller configured to control the camera system to generate a set of images of the wiring harness; send the set of images of the wiring harness to the machine learning model; and receive a result from the machine learning model indicating whether an anomaly is present in the wiring harness.

The invention relates to the field of wireless communication, in particular to aerospace vehicle wireless communication, and discloses a dual-frequency dual-high measurement and control tracking system and method based on trajectory prediction and constellation mapping. The system comprises an L omnidirectional antenna, a C directional antenna, a dual-frequency information extraction and fitting module, a track constellation mapping and module, an antenna parameter dynamic adjustment module and an antenna tracking performance monitoring module. The dual-frequency information extraction and fitting module receives data of the two antennas, extracts flight information of a fitted aircraft and outputs coordinate conversion parameters; the trajectory constellation mapping and module predicts a short-term flight trajectory of the aircraft according to the coordinate conversion parameters and outputs flight trajectory constellation coordinate range information; the antenna parameter dynamic adjustment module sets a tracking interval according to flight path constellation coordinate range information, and outputs high-precision antenna pointing information to control a C directional antenna in combination with directional antenna parameters; the antenna tracking performance monitoring module is used for evaluating the directional performance of the C directional antenna.

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 invention relates to an energy storage battery pack heat dissipation structure on an unmanned aerial vehicle, and belongs to the field of aerospace vehicle heat management systems. Comprising an energy storage battery pack air duct, an incoming flow inlet and an incoming flow outlet, a plurality of holes are formed in each partition plate in the energy storage battery pack to form an energy storage battery pack air duct; a hole is formed in the machine head fairing and serves as an incoming flow inlet; a hole is formed in the fuselage cabin section and serves as an incoming flow outlet; incoming flow enters the machine body from the hole of the machine head fairing, flows through the energy storage battery pack air channel and then flows out from the hole of the machine body cabin section, and a complete air flow channel is formed. The high-heat-flux energy storage battery pack heat dissipation device can effectively dissipate heat of the high-heat-flux energy storage battery pack, and is suitable for aviation aircrafts at different flight heights. The system is especially suitable for a low-pressure high-flight-speed flight environment at a near space height.

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.

The present application belongs to the field of overall design of single-stage orbital aerospace vehicles, and particularly relates to a method for estimating the mass of an aerospace vehicle. It includes: step one, obtaining the general equation of the vehicle acceleration process; step two, constructing a mass ratio estimation model of the rocket propulsion mode according to the general equation of the vehicle acceleration process; step three, constructing a mass ratio estimation model of the air-breathing propulsion mode according to the general equation of the vehicle acceleration process and the mass ratio estimation model of the rocket propulsion mode; step four, constructing a mass estimation model of the single-stage orbital aerospace vehicle according to the mass ratio estimation model of the rocket propulsion mode and the mass ratio estimation model of the air-breathing propulsion mode. The present application completes the estimation of the total mass of the single-stage orbital aerospace vehicle, and can quickly obtain the law between the power mode transition point, the vehicle structure mass fraction, the orbital load and the total mass of the vehicle, thereby improving the convergence speed of the solution.