2344 results about "Spaceflight" patented technology

Disclosed is a stereo vision measuring device based on a binocular omni-directional vision sensor. Each ODVS composing the binocular omni-directional vision sensor adopts the design of mean angle resolution. The parameters of two image collection cameras are in complete accord and in possession of a pretty good symmetry, and can quickly realize the point-to-point matching. The device adopts a unified spherical coordinate in the process of data collection, processing, description and representation of space objects in terms of centering on human in visual space, and adopts the elements of distance sense, direction sense and color sense to express features of each characteristic point, thereby simplifying the complication of calculus, omitting the calibration of the cameras, facilitating the feature extraction and realizing the stereo image matching easily, finally realizing the purpose of high-effective, real-time, and accurate stereo vision measurement. The device can be applied in a plurality of fields of industrial detection, object identification, robot automatic guidance, astronautics, aeronautics, military affairs, etc.

The invention provides a control method and a control device used for micro-satellite cluster flying based on atmosphere resistance, and relates to the technical field of micro-aircraft and astronautics measuring and controlling. The signal output terminal of a GPS receiver is connected with the signal input terminal of a track determining device; the signal output terminals of a solar battery array and a three-axis magnetometer are connected with the input terminal of an attitude fusion filter; the output terminal of the three-axis magnetometer is connected with the input terminal of a pure magnetic measuring attitude fusion filter; the signal output terminal of the attitude fusion filter is connected with the second input terminal of a satellite line; the first output terminal of the satellite chain is connected with the input terminal of a cluster formation control law; the second output terminal of the satellite chain is connected with the input terminal of the satellite attitude control law; the formation and attitude of the satellite cluster flying are controlled by controlling a pneumatic plate. The method and the device achieve the objects of long service life of the aircraft, low power dissipation, low cost and no pollution on the basis of atmosphere resistance.

The invention relates to a preparation method of a power and energy storage lithium-ion battery. A negative active substance of the power and energy storage lithium-ion battery comprises soft carbon, hard carbon, a mixed material of soft carbon and graphite and a mixed material of hard carbon and graphite. The designing method of the battery comprises the steps of designing the gram volume of the negative active substance as the primary lithium-embedding gram volume, designing the gram volume of the positive active substance as the primary lithium-removal gram volume, designing the ratio of the capacity of the positive electrode and the capacity of the negative electrode to be (1: 1) to (1.5: 1). By adopting the designing method, the capacity and comprehensive performance of the battery can be remarkably improved, and excellent lithium-embedding and lithium-removal capacity of the soft carbon material and the hard carbon material can be adequately exerted. Compared with the existing lithium battery technology, the prepared power lithium battery has long service life, high multiplying power, high safety performance and excellent low-temperature performance and can be widely applied to the fields such as electric tools, various portable devices, spaceflight, starting power supply and the like.

The invention discloses a laser-TIG electric arc hybrid welding technology for a spaceflight aluminum alloy plate with medium thickness and high strength and belongs to the technical field of weldingengineering. In the hybrid welding technology, a non-consumable TIG electric arc and laser beams emitted by a optical fiber laser are gathered at the same welding position on a workpiece along weldingdirection so as to jointly form a molten pool; when in welding, the laser beams are in the front and the non-consumable TIG electric arc is in the back; the distance form between the focus of the laser beams and the workpiece is sharp defocus, a dip angle between the laser beams and vertical direction is 15-17 degrees, the vertical distance from the tungsten electrode point end of the TIG electric arc to the surface of the workpiece is 3-5mm, the horizontal distances between the tungsten electrode point end of the TIG electric arc and from the laser beams to an action point on the surface ofthe workpiece are 3-5mm, and a dip angle between the tungsten electrode point end of the TIG electric arc and the horizontal direction of the workpiece is 45-55 degrees. The hybrid welding technologynot only improves the utilization ratio of laser energy, but also obviously enhances welding speed, and reduces metallurgical damage of a spaceflight aluminum alloy welding joint with high strength.

The invention provides an aerocraft view simulation system which consists of a track calculating module which comprises the calculating models of all the tracks and unified interfaces providing communication with other models; a view display module which receives information from a communication module and provides a corresponding display function; the communication module which provides the unified interfaces for obtaining the data of a computer model and simultaneously transmits the relevant data to each view; the communication module is respectively interconnected with the track calculating module and the view display module. Based on the areocraft track pose demonstration view simulation system of a 3D real time dynamic display technology, the invention simulates the flying trace and pose of the areocraft under different environments and intuitively displays the whole running process of the areocraft. Through spaceflight simulation, not only a user is led to more intuitively know the running situation of a spaceflight task, but also the design, validation, demonstration, screening and conformation of a flying scheme can be assisted and finished.

The invention relates to a low-density ablation thermal insulation type composite and a preparation method thereof. The composite adopts phenolic aerogel of the nanometer particle structure as a matrix and adopts a flexible fiber blanket or a fiber weaving body as a reinforcement body, and the composite is obtained through the steps of phenolic resin preparation, phenolic resin solution preparation, thermal treatment of the flexible fiber blanket or the fiber weaving body, steeping of the flexible fiber blanket or the fiber weaving body with the phenolic resin solution, a sol-gel reaction, aging, drying and curing of the composite and the like. Compared with the prior art, the composite is excellent in thermal protective performance, good in mechanical performance, high in designability, simple in preparation technology, low in cost and easy to process and mold, promotes later-period dimensional cutting, meets different thermal protective needs under the medium heat flow and medium and low heat flow environments, and can be applied to manned space flight and deep space detection aircrafts, outer thermal protective layers of various tactic and strategic weapons working for a short time, and inner ablation heat insulation and thermal protective layers of engines, disposable hypersonic vehicles and the like.

The invention discloses a device and a method for detecting the leak rate of an O type rubber sealing ring used for spaceflight, which belong to the technical field of the detection of spaceflight components. The device comprises gas storage equipment, an inflation valve, a first pre-pumping valve, a second pre-pumping valve, a leak detection tooling, a leak marking valve, a standard leak, a vacuum gauge, a deflation valve, a leak detection valve, a leak detector, a forestage angle valve, a prepump, a molecular pump, an ultrahigh vacuum gate valve and a vacuum booster pump. The method comprises the following steps of: firstly, pumping the pressure of a detection chamber and a dummy module below the air pressure of 10Pa, then pumping the detection chamber to a lower pressure by the molecular pump, forming a pressure difference between the detection chamber of the leak detection tooling and the dummy module and afterwards introducing high-purity gas with a standard atmosphere pressure into the dummy module. If a leak exists in a rubber sealing ring to be detected, the high-purity gas can enter the detection chamber by the sealing ring under the action of the pressure difference, and the leak rate of the sealing ring can be accurately calculated by the magnitude of the change of the output indication of the leak detector. The invention has the advantages of high detection sensitivity, high detection efficiency, reliable result and the like.

Belonging to the field of new materials, specifically high temperature/high purity, high temperature thermal field/load-bearing, frictional wear, corrosion-resistant materials and antioxidation materials in the fields of solar energy, semiconductors, metallurgy, energy, chemical industry, materials, machinery, transportation, spaceflight and aviation, etc., the invention provides a carbon fiber reinforced silicon carbide ceramic matrix composite material and a preparation method thereof. The preparation method includes: uniformly spraying or coating a silicon carbide slurry on the surfaces ofcarbon fiber felt and carbon fiber cloth, and then conducting alternate laminating, needling, drying and hot pressing curing to obtain a composite green blank; then carrying out carbonization on the composite green blank, and performing alternate infiltration deposition of pyrolytic carbon and silicon carbide on a boundary phase, and finally conducting pyrolytic carbon infiltration deposition anddensification treatment, thus obtaining the carbon fiber reinforced silicon carbide ceramic matrix composite material. The preparation method provided by the invention has the characteristics of shortpreparation period and low preparation cost, and the prepared carbon fiber reinforced silicon carbide ceramic matrix composite material has good uniformity, high strength and reliable performance.

The invention discloses an evaluation method of reliability of an aerospace electronic product based on a failure mechanism. On the basis that an analysis method with a combination of physical simulation and a test is adopted, a physical simulation model of the electronic product is constructed, the means such as sensitivity analysis, Monte Carlo analysis, and stress analysis are adopted, and product key elements are identified and in combination with actual working conditions of the elements, a failure mechanism analysis is conducted. Currently, the failure mechanism analysis aiming at the elements is a means used for analyzing a failure reason after a failure occurs during the test or in the using process of the electronic product, thus pertinent improvement is conducted on the product, the service life of the product is prolonged, and the reliability of the product is improved; the failure mechanism analysis aims at finding key characteristic parameters which affect the service life and the reliability of weak elements as an independent variable of the reliability model.

An intelligent control method for vertical recovery of carrier rockets based on deep reinforcement learning is disclosed. A method of autonomous intelligent control for carrier rockets is studied. Theinvention mainly studies how to realize attitude control and path planning for vertical recovery of carrier rockets by using intelligent control. For the aerospace industry, the autonomous intellectualization of spacecrafts is undoubtedly of great significance whether in the saving of labor cost or in the reduction of human errors. A carrier rocket vertical recovery simulation model is established, and a corresponding Markov decision-making process, including a state space, an action space, a state transition equation and a return function, is established. The mapping relationship between environment and agent behavior is fitted by using a neural network, and the neural network is trained so that a carrier rocket can be recovered autonomously and controllably by using the trained neural network. The project not only can provide technical support for the spacecraft orbit intelligent planning technology, but also can provide a simulation and verification platform for attack-defense confrontation between spacecrafts based on deep reinforcement learning.

The invention relates to an inertia/vision integrated navigation method for a deep-space detection patrolling device. The method comprises the steps that a state model of inertia/vision integrated navigation of the patrolling device is established according to a serial inertial navigation mechanical arrangement in a fixed coordinate system of a planet; a binocular vision camera is used for shooting a surrounding environment of the patrolling device; a stereoimage sequence is obtained; pixel coordinates of characteristic points are obtained by an image characteristic extraction algorithm; a measurement model by taking the pixel coordinates of the characteristic points as measurement vectors is established; and a position, a speed and a state of the deep-space detection patrolling device are estimated by using Unscented kalman filter. The method can effectively correct a position error of inertial navigation and improve the navigation accuracy, is very applicable to autonomous navigation of the deep-space detection patrolling device, belongs to the technical field of space navigation, can provide high-precision navigational parameters for the deep-space detection patrolling device, and can provide references for the design of an autonomous navigation system of the deep-space detection patrolling device.

The invention discloses a bonding system of a high-reliability thick-film mixed integrated circuit and a manufacturing method thereof. The system and the method are characterized in that the bonding system is an indirectly bonded bonding system, namely, a layer of blocking layer metal film is added on the surface of the metal bonding area and a layer of metal film capable of carrying out high-reliability bonding with the silicon-aluminium wire is then added on the surface of the metal bonding area so as to form a multilayer transitional film; and subsequently the bonding system of the silicon-aluminium wire is carried out on the surface of the metal bonding area. The system and the method have the advantages of: (1) improving the bonding performance of the bonding area of the thick-film gold conducting belt and the silicon-aluminium wire; (2) forming local nickel bonding area or an aluminium bonding area on the bonding area of the same gold conducting belt, and being compatible with the gold wire bonding and silicon-aluminium wire bonding; and (3) adopting a metal mask location register and high-vacuum deposition film-formation technology and having no damaging effects on the substrate of the thick-film. When being applied to all thick-film mixed integrated circuit taking gold conducting belts or silver conducting belts as substrates, the reliability of the mixed integrated circuit can be improved and the mixed integrated circuit has wide application prospect in the fields such as aviation, spaceflight, navigation, communication, industrial control and the like.

The invention relates to an aerogel-metal composite material, and a preparation method and application thereof. In the aerogel-metal composite material provided by the invention, an aerogel is dispersed in a metal material. The particle size of the aerogel is preferably ranged from 0.1mu m to 10cm. The aerogel is provided with holes with the size being preferably ranged from 3nm to 100nm. The preparation method of the aerogel-metal composite material comprises the following steps of after mixing the aerogel and the metal, heating to melt the metal, or mixing the aerogel and the metal melt liquid, and then cooling the mixture in a die to obtain the aerogel-metal composite material. The composite material provided by the invention has the characteristics of low density and high strength, and can be used as a novel structure material so as to be applied in the fields of spaceflight, military, buildings, machinery and the like.

The invention provides a metal propellant storage tank for spaceflight. The metal propellant storage tank for the spaceflight comprises a shell 1 and a metal diaphragm 2. The shell comprises a gas circuit joint 3, an upper semisphere 4, a connecting ring 5, a lower semisphere 6 and a liquid circuit joint 7, wherein the upper semisphere 4 and the lower semisphere 6 are connected through the connecting ring 5, the gas circuit joint 3 is connected with the upper semisphere 4, the liquid circuit joint 7 is connected with the lower semisphere 6, and the metal diaphragm 2 is in butt joint with the connecting ring 5. The overall shell 1 is made of the scandium aluminum magnesium alloy materials whose brand type is 5B70. The metal diaphragm 2 is made of pure aluminum. The invention further provides a manufacturing method of the metal propellant storage tank for the spaceflight. The metal propellant storage tank for the spaceflight solves the problems that the propellant storage tank is large in quality and low in structural efficiency, realizes the light design of the propellant storage tank, effectively reduces the weight of the storage tank, and greatly reduces the launch cost of a vehicle.

The generator includes stator, rotor without winding. Torsion winding and suspension winding are sheathed on the stator. Torsion winding implements the functions of starting up and generating electricity. Superposing magnetic field generated by suspension winding on bias magnetic field generated by torsion winding produce variable lift force so as to realize stable suspension of rotor. Current control method of torsion winding includes following three modes: current chop, modulation of angle position and pulse width modulation. Synthesizing the said three modes, four methods for controlling suspension are adopted in the invention to calculate given suspension current value. Integrating roles of starter, generator and magnetic bearing, the disclosed generator possesses wide application and important meaning in areas of aviation and spaceflight.

The invention relates to the field of five-axis gantry machining center tools, in particular to a direct-drive high-speed five-axis gantry machining center with a replaceable milling head, which solves the problems in the prior art, such as low precision and the like. Two linear guide rails are arranged on a left bridge and a right bridge respectively; a slide plate is in slide fit with a guide rail on a crossbeam through a slide block; a ram is in transmission fit with the slide plate through double lead screws, a double-pendulum head with A and C shafts is mounted at the bottom of the ram, and a head magazine is arranged on one side of a worktable; two ends of the crossbeam are mounted on the left bridge and the right bridge through slide seats; linear motors are adopted on the X direction and Y direction of the five-axis machining center for direct driving, the crossbeam moves horizontally along the left bridge and the right bridge in the X direction, and the slide plate moves horizontally along the crossbeam in the Y direction, double motors in the Z direction of the five-axis machining center drive the ram through gravity centers, and the ram moves vertically on the slide plate in the Z direction. The machining center has stable running and performance, and is suitable for precision finishing of dies in the industries of aviation, spaceflight, automobiles, and the like.

The invention belongs to the technical field of polymer composite materials and particularly relates to a modified graphene/polyimide resin composite material and a preparation method of the modified graphene/polyimide resin composite material. The composite material comprises 95.0 to 99.9 weight percentage of polyimide resin and 0.1 to 5.0 weight percentage of modified graphene, wherein the polyimide resin is thermoset polyimide resin obtained through the heat cross-linking of prepolymers at the crosslinkable group sealing end. The preparation processes comprise graphene oxide modification, solution blending of modified graphene and crosslinkable prepolymers and the in-situ heat cross-linking of precursors. In the composite material, the modified graphene is uniformly dispersed and is in laminar arrangement distribution, and in addition, the modified graphene and the polyimide resin form the covalent bond action force through the in-situ heat cross-linking reaction, so the composite material has excellent interface combination performance. The composite material disclosed by the invention has the advantages that the mechanical performance, the wear performance and the hydrophobic performance are all greatly improved, and the composite material can be applied to the fields of aviation, spaceflight, machinery, electronics, automobiles, home appliances, offices and the like.

A spacecraft attitude-track integrated backstepping tracking control method is provided, and aims to solve the problems that an existing method respectively uses separate control modes to track the spacecraft track and attitude, so the tracking effect is poor; the method comprises the following steps: 1, building a spacecraft attitude-track integrated relative kinematics and dynamics model according to dual quaternions; 2, designing a controller according to a backstepping method and the spacecraft attitude-track integrated relative kinematics and dynamics model built in step 1; 3, designing an anti-saturation method based input bounded controller according to the controller designed in step 2. The method considers the input bound problems on the backstepping controller base, and designs the anti-saturation node based input bounded backstepping controller; the method can track the spacecraft and realize the 6-degree of freedom attitude-track cooperation tracking of the target spacecraft, is suitable for practical in orbit conditions, and applied to the spaceflight field.

The invention relates to the aerospace field, and provides a rendezvous docking method and device of a space non-cooperative target. The method comprises the steps of guiding the space non-cooperative target to a system capture range through ground guideness; determining measurement angle of sight, relative distance and azimuthal angle respectively according to the simplest combination of measurement components capable of determining relative parameters of the space non-cooperative target; carrying out relative navigation by using an extended Kalman filter algorithm, according to the capture measurement results; tracking track the target by executing CW reference trajectory guidance and linear reference trajectory guidance respectively to according to navigation results and giving out a relative position and relative speed equation of an ideal trajectory; and carrying out thrust control by adopting a PID control law and a pseudo rate pulse modulator during an approaching process. Through capturing, tracking and approaching of the space non-cooperative target, autonomous capturing, continuous tracking and stable approaching of the space non-cooperative target can be finished after a spacecraft enters a work range of capturing the non-cooperative target, thereby realizing rendezvous docking of the space non-cooperative target.

The invention, which belongs to the spaceflight drive assembly reliability and life evaluation field, relates to a combined stress acceleration life test method of a spaceflight drive assembly. According to the method, an acceleration stress is selected; an acceleration testing profile is determined and as a result, a combined stress acceleration life testing profile is employed; testing samples are selected and the number of samples is determined; fault determination and a testing period are determined; testing stop time is determined; and according to data obtained by the above-mentioned testing process, a life characteristic value of the spaceflight drive assembly is evaluated. According to the method, a combined stress is employed to carry out acceleration life testing and an acceleration effect is obvious; therefore, rapid evaluation on reliability and life of the spaceflight drive assembly is realized.

The invention discloses a near space dynamic plasma sheath channel modeling and simulating method. The method comprises the steps that channel resources are partitioned according to large-scale space-time-frequency characteristics to construct a large-scale space-time-frequency channel resource matrix, wherein the height corresponds to large-scale space domain characteristics, the speed corresponds to large-scale time domain characteristics, and frequency points correspond to large-scale frequency domain characteristics; for all channel resource matrixes, dynamic small-scale channel parameters are obtained; small-scale channel model simulating is achieved according to given small-scale channel parameters; large-scale channel model simulating is achieved by repeating small-scale channel models at multiple states on a near space flight path. The method is suitable for channel modeling under different dynamic rules, random-amplitude phase probability density distribution which may occurs under a plasma sheath is simulated, and channel modeling feasibility is guaranteed; the method is suitable for near space aircraft plasma sheath channel modeling and spaceflight reentry-return spacecraft plasma sheath channel modeling.