90 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 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.

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 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 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 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 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.

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.

This invention relates to an engine for an aircraft, wherein an annular vortex guide, in cross-section, has an air inlet centrally located about the longitudinal axis of the engine and an air outlet centrally located about the longitudinal axis, spaced apart from the air inlet. The air inlet and air outlet are in fluid communication with each other via an air intake duct, which is defined by the vortex guide and houses an air supply device. The air outlet is overlapped by an air deflector. When the engine is operating normally, the air deflector is positioned above the vortex guide from a geodesic angle, extending radially outward from the air outlet and defining an exhaust gap in fluid communication with the air outlet. According to the invention, the vortex guide is a body of revolution formed by rotating a closed curve with a continuous thread at least radially outward about a rotation axis; the air inlet directly connects to the external environment of the engine, so that when the engine is operating normally, air from the side of the engine opposite to the air deflector is delivered through the air inlet into the air intake duct.

This invention discloses a knitting machine for a thermal insulation and sealing elastic inner support structure for aerospace vehicles, comprising: a frame, a knitting cylinder, a knitting toothed plate, a needle feed cam, multiple needles, a gantry, an elastic structure support, and a drafting mechanism. The drafting mechanism is disposed on the frame and is used to clamp and pull the knitted elastic structure and the mesh sleeve wrapped around the elastic structure. This invention relates to the field of knitting machine technology. By installing the gantry on the knitting toothed plate and rotating it synchronously, the special metal wire is fed in a follow-up manner, enabling the special metal wire to enter the knitting area evenly and stably, effectively solving the problem of uneven knitting of special metal wire. Through the cooperation of the knitting toothed plate, the needle feed cam, and the needles, the regular up-and-down reciprocating motion of the needles on the fixed needle cylinder is achieved. At the same time, the knitting toothed plate drives the gantry to rotate around the elastic structure support to feed the wire, ensuring that the metal wire is always evenly wrapped around the elastic structure support during the knitting process.

A generative artificial intelligence system and method of operating the same to control complex systems. In one embodiment, the method includes incorporating measures of merit into system requirements for an aerospace vehicle system to provide aggregated system requirements and measures of merit, and receiving design parameters of the aerospace vehicle system represented as stochastic variables. The method also includes executing first order physics-based engineering equations of the design parameters with the generative artificial intelligence system on the processor to produce a design for an operation of the aerospace vehicle system to meet the aggregated system requirements and measures of merit in a single iteration improving computational efficiency and reducing power consumption of the processor operating the generative artificial intelligence system.

A representative hatch system can include a base portion surrounding an opening, a hatch portion movable relative to the base portion between a closed configuration and an open configuration, and a movement mechanism positioned to move the hatch portion relative to the base portion between the closed and open configurations. The movement mechanism can include four arms pivotably attached to the hatch portion and the base portion via four pivot axes. When the hatch portion is in the closed configuration, the axes can be coplanar. The axes can be spaced apart from a sealing plane between the hatch portion and the base portion. The arms can traverse a periphery of the hatch portion. A representative aerospace system can include a hatch system supported in a wall portion of an aerospace vehicle. The movement mechanism can keep the sealing surface of the hatch facing away from an interior of the vehicle.

This application discloses an online trajectory planning method, system, and storage medium for the ascent phase of a combined-propulsion aerospace vehicle, belonging to the field of aircraft guidance and control technology. The method includes: offline generation of a large number of trajectory samples under parameter deviation conditions within the framework of the direct method, forming a dataset for network training; dividing the ascent phase of the combined-propulsion aerospace vehicle into a turbine-based combined cycle propulsion (TBCC) phase and a liquid rocket propulsion (RKT) phase based on the differences in the dynamic characteristics of the engine modes, and designing corresponding state-control networks for each, followed by training to obtain a segmented network; using the segmented network, outputting the control variables required at the current moment, providing the corresponding flight strategy, and realizing online trajectory planning. Numerical simulation results of this application verify that the method can maintain high terminal accuracy and strong robustness under different thrust deviation scenarios while ensuring the accuracy and real-time performance of online applications.

Thermal protection systems for aerospace vehicles, such as hypersonic vehicles or space vehicles, are disclosed herein. In some embodiments, the disclosed thermal protection systems can be used to protect propellant tanks (e.g., composite propellant tanks) and vehicle primary structures (e.g., composite primary structures) from exceeding upper design temperature limits during vehicle ascent, reentry into Earth's atmosphere, and / or high velocity flight through an atmosphere. In some embodiments, a thermal protection system can include a framework of elongated composite members forming a plurality of cells. One or more layers of insulation material such as aerogel can be positioned in each of the cells. The cells can be covered by an external skin of the vehicle. In some embodiments, the framework is attached to a propellant tank and the insulation material is in contact with the external surfaced of the propellant tank.

A polishing device for aerospace components includes a main support base, a rotary drive motor, a polishing roller, aerospace components, a displacement drive ring, and a first locking block. The main support base has a first support platform on one side and a second support platform on the other side. The first support platform has a first support block in the middle, and a driven block connecting platform on the side of the first support block. Three sets of driven block connecting platforms are evenly arranged around the first support block. The driven block connecting platform has a driven block connecting groove inside, which is adapted to a driven slider. The driven slider is connected to the driven block connecting groove and slides inside the driven block connecting groove. The first support block has a first locking block connecting groove inside, and a first locking block is provided on the side of the first support block facing the middle of the main support base. The side of the first locking block facing the first support block has a first locking block connecting post.

This invention belongs to the field of aerospace vehicle technology, and particularly relates to a connection and separation device employing winding locking and fusible triggering. It includes: a release device comprising a segmented body, a winding spring, a fusible wire, and a wire; one end of the winding spring is connected to the segmented body, and the other end is connected to the fusible wire; and a separation body comprising a connecting rod and a body to be separated, the connecting rod being inserted into the segmented body. In the locked state, the fusible wire is tensioned under the action of the winding spring, the segmented body is wound and tightened by the winding spring, and the end of the connecting rod is fixed within the segmented body. In the unlocked separation state, the fusible wire breaks upon energization, the winding spring releases its restriction on the segmented body, the connecting rod is released from the segmented body, and the separation body separates from the release device. The connection and separation device of this invention has advantages such as fast response speed, low cost, wide application temperature range, simple structure, light weight, large load capacity, low impact, and no pollution.

A method for obtaining micro-vibration test conditions for aerospace vehicles involves: searching for micro-vibration disturbance sources during the vehicle's on-orbit operation; classifying the micro-vibration disturbance sources and identifying those that cannot be avoided; conducting micro-vibration environment measurement tests on the unavoidable disturbance sources to obtain the time-domain curve of the maximum vibration environment of the disturbance sources; establishing a finite element model for micro-vibration response analysis; conducting transient response analysis to determine the micro-vibration response of precision instruments; converting the time-domain curve of the micro-vibration response of the precision instruments into a frequency-domain curve and performing envelope design to obtain the micro-vibration test conditions of the precision instruments for subsequent experimental verification.

The application relates to the field of aerospace vehicle general design, and discloses an aircraft interior and exterior trajectory integrated optimization method based on a sparse neural network, which comprises the following steps: constructing a design variable set by using design variables of an aircraft, and setting an output response; constructing a sample in combination with the design variable set based on a design space of the design variables, so as to form a training sample set; determining the output response of each sample by using an interior trajectory simulation model and an exterior trajectory simulation model, so as to form an output response set; introducing a norm as a sparse regular term of a total loss function, so as to construct a sparse neural network based on the norm; training the sparse neural network by using the training sample set and the output response set; taking the sparse neural network as a low-precision model, and taking the interior trajectory simulation model and the exterior trajectory simulation model as high-precision models; continuously optimizing the low-precision model in combination with a dynamic trust factor, and finally determining a candidate design point serving as an optimal design scheme.