169 results about "Aerospace vehicle" patented technology

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 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 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.

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.

The invention relates to jet reference fluid formulations for fuel substitutes and methods thereof. Jet reference fluid (JRF) compositions and their use in test methods are disclosed. The jet reference fluid comprises a first hydrocarbon and a second hydrocarbon, and wherein the first hydrocarbon and the second hydrocarbon may or may not comprise an aromatic compound. The jet reference fluid (JRF) composition may include one or more additives, such as ethylene glycol monomethyl ether. A method for testing compatibility of jet reference fluid (JRF) with aviation fuel is also disclosed. The method may be used to assess one or more components or systems of aerospace vehicles, including thermosets, thermoplastics, sealants, elastomers, metals, veneers, coatings, wiring, or combinations thereof.

The application discloses a design method of a reusability aerospace vehicle compression heart rear movement, and a pair of pitching stabilizing plates are symmetrically arranged at both sides of a tail section of a fuselage of the aerospace vehicle; the pitching stabilizing plates are connected with the fuselage through rudder shafts; the pitching stabilizing plates can rotate around the rudder shafts to realize the conversion between an opening mode and a folding mode of the pitching stabilizing plates. The design method of the reusability aerospace vehicle compression heart rear movement can move the compression heart of the aerospace vehicle rearward and realize the adjustment of the pitching stability of the aerospace vehicle under different flight conditions.

This invention belongs to the field of aerodynamic shape design of aerospace vehicles, and relates to a structure and design method for adjusting the zero lift moment of an aircraft. The structure includes a non-circular cross-section fuselage, the tail of which is tapered, and a vertical tail and a horizontal tail are provided in the tapered tail section. A tail fin is provided between the horizontal tail and the fuselage for adjusting the zero lift moment of the entire aircraft. This invention can meet the aerodynamic performance requirements of the aircraft, and at the same time, the integrated design of the tail fin and the servo motor can meet the requirements of the servo motor installation space.

The invention belongs to the field of machining of light alloy parts of aerospace parts, and particularly provides a machining method for a multi-angle narrow groove in the arc-shaped surface of a light alloy ball. Comprising the steps of workpiece parameter measurement, quadrant preliminary division, tool nose angle calculation, tool nose angle judgment, quadrant re-division, tool nose angle determination, feed angle determination and narrow groove machining in the quadrant. According to the machining method, continuous and effective machining of the multi-angle ultra-small narrow grooves in the surface of the thin-wall light alloy part with the arc-shaped surface (such as a spherical surface) can be achieved, and efficient batch machining with quality and quantity guaranteed is achieved through a reasonable and safeguarded dividing means.

The application discloses a kind of processing technology of power two guide inner machine cabinet front section welding assembly, belong to aerospace parts processing technical field.Aiming at the problem that assembly rigidity is poor, processing is easy to deform, and it is difficult to guarantee precision size, the process realizes precision control by optimizing route, improving clamping, configuring special tooling and relaxing unnecessary tolerance.Process route is: 0 is matched→10 vacuum brazing→15 bench grinder→20 numerical control machine processing→30 bench work→40 numerical control machine processing→42 numerical control machine finishing→50 numerical control milling processing→60 bench work→70 electric spark grinding→80 ultrasonic cleaning→85 numerical control machine processing→90 bench work→100 inspection→110 electric arc ion plating→120 inspection→130 cleaning→140 packaging.15, 42, 85 new process, optimize the clamping mode of each core process, configure fixed cover plate and special gauge, reasonably adjust tolerance range, and the qualified rate of part processing can be effectively improved.

This invention discloses a perovskite-type high-entropy ceramic material, its preparation method, and its application. The preparation method of the perovskite-type high-entropy ceramic material of this invention includes the following steps: 1) mixing A-site oxide powder and B-site oxide powder and wet ball milling, followed by drying and grinding to obtain a mixed powder; 2) adding the mixed powder into a graphite crucible and compacting it, then subjecting it to laser radiation heating to obtain the perovskite-type high-entropy ceramic material. The perovskite-type high-entropy ceramic material of this invention exhibits multi-band absorption characteristics, high service temperature, and stable performance at high temperatures, making it suitable for use in stealth coatings for aerospace vehicles. Furthermore, its preparation method is simple, with a short reaction time and low production cost, making it suitable for large-scale industrial production and application.

The invention belongs to the technical field of aerospace vehicle parachute recovery, and particularly relates to a cold propulsion parachute shooting rocket which comprises a connecting base connected to a parachute pack, a partition plate is arranged in the connecting base, and the interior of the connecting base is divided into a first cavity and a second cavity by the partition plate; the gas storage mechanism is arranged on the connecting base and located in the first cavity; the sealing mechanism is fixedly connected to the gas outlet of the gas storage mechanism; the air injection mechanism is arranged on the connecting base and communicates with the second cavity; the triggering device is arranged on the connecting seat; and a gas flow channel is arranged in the triggering device. By applying the cold air propulsion principle and adopting the combination of the industrial high-pressure gas cylinder and the vehicle gauge level ignition head, the problems of matching cost, safety and reliability and use convenience are solved, and the device has the advantages of no burning of the umbrella, safety and reliability, convenience in use, low cost 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.

To provide an optical member and an imaging device in which reflection at an end portion can be sufficiently suppressed even in the optical member, and ghosts can be reduced as the imaging device.SOLUTION: An optical member according to the present invention is an optical member including: a base material made of aluminum or an aluminum alloy; a first layer provided on the base material and made of black porous aluminum oxide; and a second layer provided on the first layer and made of aluminum oxide having a plurality of protrusions, where the base material has an opening, an R-shape or a tapered shape is formed in a peripheral portion of the opening, and the first layer and the second layer are provided on the R-shape or the tapered shape.SELECTED DRAWING: Figure 4