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2357 results about "Spaceflight" patented technology
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Spaceflight (or space flight) is ballistic flight into or through outer space. Spaceflight can occur with spacecraft with or without humans on board. Yuri Gagarin of the Soviet Union was the first human to conduct a spaceflight. Examples of human spaceflight include the U.S. Apollo Moon landing and Space Shuttle programs and the Russian Soyuz program, as well as the ongoing International Space Station. Examples of uncrewed spaceflight include space probes that leave Earth orbit, as well as satellites in orbit around Earth, such as communications satellites. These operate either by telerobotic control or are fully autonomous.
Component with carbon nanotubes
InactiveUS20090140098A1Lightning protection is goodAircraft lighting protectorsMilitary adjustmentAviationCarbon nanotube
The present invention relates to a component, in particular in the field of aviation and spaceflight, having a resin matrix in which carbon nanotubes are embedded for high conductivity of the component.
Owner:AIRBUS OPERATIONS GMBH
Stereo vision measuring apparatus based on binocular omnidirectional visual sense sensor
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.
Owner:汤一平
Tiny satellite formation flying control method based on atmospheric drag and control device
InactiveCN101381004ANo pollution in the processReduce power consumptionCosmonautic vehiclesCosmonautic vehicle trackingAstronauticsPower consumption
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.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Power and energy storage lithium-ion battery and preparation method thereof
ActiveCN103441305AImproved gram capacity playIncrease capacityFinal product manufactureElectrolyte accumulators manufactureGramEngineering
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.
Owner:BTR NEW MATERIAL GRP CO LTD
Laser interference system used for measuring micro roll angle
Owner:UNIV OF SHANGHAI FOR SCI & TECH
Laser-TIG electric arc hybrid welding technology for spaceflight aluminum alloy plate with medium thickness and high strength
InactiveCN101670495AIncrease profitReduce metallurgical damageLaser beam welding apparatusSpaceflightLaser beams
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.
Owner:BEIJING UNIV OF TECH
Aircraft vision emulation system
InactiveCN101398866AEasy to joinStrong developmentSoftware simulation/interpretation/emulationSpecial data processing applicationsFlight vehicleData shipping
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.
Owner:HARBIN ENG UNIV
Low-density ablation thermal insulation type composite and preparation method thereof
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.
Owner:EAST CHINA UNIV OF SCI & TECH
Device and method for detecting leak rate of O type rubber sealing ring used for spaceflight
InactiveCN101726396AHigh detection sensitivityImprove detection efficiencyDetection of fluid at leakage pointEngineeringAtmospheric pressure
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.
Owner:NO 510 INST THE FIFTH RES INST OFCHINA AEROSPAE SCI & TECH
Voice denoising method based on audio recognition
The invention provides a speech noise reduction method based on audio recognition, which reduces the noise of a receiving end by aiming at the speech communication under complex noise environment, belonging to the field of computer science and technology. Most of the existing noise reduction methods are only suitable for stable noise environment and can not remove the noise under the situations of complex noise environment, especially the situation of frequent mutagenicity noise and the like. The method leads a mode recognition idea in the communication speech noise reduction, divides an audio signal into a speech signal and a non-speech signal, automatically identifies the input signal by extracting the speech characteristic and designing a sorter model, and judges the audio type; if the audio type is noise, the audio signal is removed; if the audio type is speech, the audio signal is remained and processed further. The method meets the real-time requirement and has better reduction noise effect at the same time, can be suitable for the situations with complex communication environments such as manned spaceflight speech communication, construction sites, battlefields and the like, and provides an idea and a method for the noise reduction of signals.
Owner:UNIV OF SCI & TECH BEIJING
Preparation method of graphene/metal composite panel
InactiveCN103935103AGuaranteed decentralizationEvenly dispersedArmourLamination ancillary operationsAviationDispersity
The invention relates to a preparation method of a graphene / metal composite panel. The preparation method comprises the steps of firstly uniformly mixing a monodispersed graphene solution with a polyvinyl alcohol solution to prepare graphene / polyvinyl alcohol mixed slurry, spraying the graphene / polyvinyl alcohol mixed slurry to the upper and lower surfaces of a plurality of metal panels, heating to remove polyvinyl alcohol in a coating, and finally laminating the metal panels to prepare the graphene / metal composite panel in a hot rolling manner. The preparation method has the beneficial effects that by compositing the graphene / polyvinyl alcohol mixed slurry with the metal panels, the dispersity of graphene can be guaranteed; by utilizing a hot rolling process, the graphene can be beneficially dispersed into matrixes of the panels so as to play a strengthening effect; the molecular association between the graphene and the metal panels is realized in the premise of well preserving intrinsic physical properties of the graphene and a metal material; the process is simple, the large-batch and large-size graphene composite panels are easily prepared, the production cost is lowered, and the preparation method has excellent engineering application prospects in the fields of light armor materials, aviation, spaceflight and the like.
Owner:BEIJING GRAPHENE TECH RES INST CO LTD
Satellite autonomous orbit determination method based on satellite-borne GNSS multiple antennas
ActiveCN103675861AExcellent data fusion resultsImprove the accuracy of orbit determinationInstruments for comonautical navigationSatellite radio beaconingNatural satelliteKaiman filter
A satellite autonomous orbit determination method based on satellite-borne GNSS multiple antennas. According to the method, a Kalman filter is extended; multiple GNSS antennas measured pseudorange observation values are made full use of to carry out real-time filtering correction of an orbit prediction value using a high precision mechanical model; and high precision satellite orbit information is obtained. According to the invention, the problems of the high precision orbit determination in a complex posture maneuver can be solved. In the invention, the orbit determination result is high in precision, good in stability, and highly real-time, can meet the orbit determination demand of the low orbit satellite and high precision satellite, can be widely applied to the high precision orbit determination of the space station, high resolution earth observation satellite and other space missions, and has a wide promotion and application prospect.
Owner:SPACE STAR TECH CO LTD
Nano-pore SiO2 aerogel thermal insulation composite material and preparation method thereof
The invention discloses a nano-pore SiO2 aerogel heat-insulating composite material and a preparation method thereof. The nano-pore aerogel heat-insulating composite material comprises SiO2 aerogel, an infrared opacifier and reinforced fibers. The preparation method comprises: mixing silicasol and indium-tin oxide ITO nano alcohol slurry or nano composite alcohol slurry of ITO and TiO2 through supersonic wave action, mixing the mixture and the reinforced fibers, directly pouring the mixture into a die to form a wet gel complex, and performing supercutical fluid drying. The material has good heat transfer function and good obstructing function on solid heat conduction, air heat convection and infrared radiation heat conduction, simultaneously has good hydrophobicity, simple technique, low cost and wide application scope, has the mechanical strength reaching more than 1.2 MPa, and can be used in situations with higher heat protection requirement in the fields of avigation, spaceflight, military affairs and domestic use.
Owner:CHANGSHA XINGNA AEROGEL
Independent celestial navigation method for Mars capturing section of deep space probe
ActiveCN102168981AAvoid Accuracy ImpactImprove navigation accuracyInstruments for comonautical navigationFixed starsDynamic models
The invention relates to an independent celestial navigation method for a Mars capturing section of a deep space probe. The method comprises the following steps of: establishing a state model of the deep space probe according to a circular restrictive four-body track dynamics model; acquiring picture element and picture line information of Mars, Martian satellites and a background fixed star, converting the acquired picture element and picture line information into angle information of the Mars, the Martian satellites and the background fixed star and establishing an angle measuring model of the Mars, a Martian satellite I and a Martian satellite II; and estimating the attitude information of the probe by adopting a q-method and estimating the position and speed of the deep space probe in combination with Unscented Kallman filtering. The method has high estimation accuracy, and is very suitable for independent navigation of Mars capturing. The method belongs to the technical field of aerospace navigation. By adopting the method, high-accuracy navigation parameters can be provided for Mars capturing of the deep space probe, and references can be provided for the design of an independent navigation system of the deep space probe.
Owner:BEIHANG UNIV
Carbon fiber reinforced silicon carbide ceramic matrix composite material and preparation method thereof
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.
Owner:湖南兴晟新材料科技有限公司
Evaluation method of reliability of aerospace electronic product
InactiveCN106529090ATight performanceBoost Design ImprovementsProbabilistic CADSpecial data processing applicationsDependabilityReliability model
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.
Owner:CHINA AEROSPACE STANDARDIZATION INST
Intelligent control method for vertical recovery of carrier rockets based on deep reinforcement learning
ActiveCN109343341AFast autonomous planningIncrease autonomyAttitude controlAdaptive controlAttitude controlReturn function
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.
Owner:BEIJING AEROSPACE AUTOMATIC CONTROL RES INST +1
Self boundary marking method based on forecast filtering and UPF spacecraft shading device
ActiveCN101082494AOvercoming inaccuracyImprove filtering accuracyNavigation by speed/acceleration measurementsNavigation by astronomical meansSpaceflightInformation integration
There are a sort of predictive filtering and the self-demarcation of the UPF spaceflight, it relates to the spaceflight airmanship field. It applies to the self-demarcation of the spaceflight peg-top, especially it relates to a sort of spaceflight self-demarcation method of the inertia / starlight which bases the predictive filtering and the UPF (Unscented Particle Filter) information coalescence, thereby it applies to the navigation determining gesture of the spaceflight. First it establishes the self-demarcation state equations of the spaceflight, and then it makes the gesture information which is observed by the star sensing device to become the measuring equations, finally it adopts the self-demarcation arithmetic which bases the predictive filtering and the UPF spaceflight to estimate and amend the drift error of the peg-top, thereby it obtain the high exact gesture of the spaceflight.
Owner:BEIHANG UNIV
Inertia/vision integrated navigation method for deep-space detection patrolling device
ActiveCN103033189AHigh precisionAvoid errorsInstruments for comonautical navigationFeature extraction algorithmSpaceflight
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.
Owner:BEIHANG UNIV
Bonding system of high-reliability thick-film mixed integrated circuit and manufacturing method thereof
InactiveCN101673693AImprove reliabilityImprove bonding performanceSolid-state devicesSemiconductor/solid-state device manufacturingAviationSpaceflight
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.
Owner:GUIZHOU ZHENHUA FENGGUANG SEMICON
Aerogel-metal composite material, and preparation method and application thereof
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.
Owner:HONGDA TECH BEIJING CO LTD
Metal propellant storage tank for spaceflight and manufacturing method thereof
ActiveCN104648696ASolve lightweight design problemsImprove performanceCosmonautic propulsion system apparatusRocket engine plantsButt jointSpaceflight
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.
Owner:SHANGHAI INST OF SPACE PROPULSION
Bearing-free switch magnetic-resistance starting generator and control method
InactiveCN1710782AReduce noiseReduce torque rippleWindings conductor shape/form/constructionStarter generatorAviation
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.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Six-degree-of-freedom quasi-zero-rigidity vibration isolation system based on Stewart platform
InactiveCN105041961AGood suppression effectImprove carrying capacityNon-rotating vibration suppressionLow frequency vibrationSix degrees of freedom
The invention provides a six-degree-of-freedom quasi-zero-rigidity vibration isolation system based on a Stewart platform. The system comprises an upper platform, a lower platform and six same landing legs fixed between the upper platform and the lower platform through hinge blocks. The three hinge blocks are distributed in an equilateral triangle mode, two corresponding landing legs are fixed to each hinge block, the adjacent landing legs are perpendicular, and the upper platform has six degrees of freedom relative to the lower platform. The six landing legs have the quasi-zero-rigidity characteristic, so that the vibration isolation system has the quasi-zero-rigidity characteristic on the six degrees of freedom, the all-order resonant frequency of the vibration isolation system is small, and the wide vibration isolation frequency range is achieved. The system has the advantages of being high in bearing capacity and low in resonant frequency, has the good restraint effect on low-frequency vibration, and is suitable for vibration isolation of flywheel systems and optical cameras in the spaceflight field and vibration isolation of equipment such as precision machine tools and precision measuring systems in the civil field.
Owner:XI AN JIAOTONG UNIV
Aircraft engine mounting vehicle
InactiveCN102009340AHigh loading and unloading positioning accuracyHigh degree of automationAircraft assemblyMetal working apparatusAviationControl system
The invention discloses an aircraft engine mounting vehicle. The aircraft engine mounting vehicle comprises a lifting bracket (1), a shear type lifting mechanism (2), a back-and-forth moving frame (3), a left-right moving frame (4), a rotating disk mechanism (5), an electrohydraulic servo control system (6) and a vehicle body (7), wherein the lifting bracket (1) is provided with a longitudinal linear guide rail (15); the back-and-forth moving frame (3) is provided with a transverse linear guide rail (16) and a longitudinal slide block (17); the left-right moving frame (4) is provided with a transverse slide block (18); and the electrohydraulic servo control system (6) comprises a control unit (20) and an executing unit (21). In the aircraft engine mounting vehicle, a closed-loop servo control system consisting of the linear guide rail, a high-accuracy sensor, a high-response spaceflight servo valve, a precise servo oil cylinder and a programmable logic controller (PLC) is adopted, so 0.1mm absolute accuracy fine adjustment can be realized; and the aircraft engine mounting vehicle has the advantages of improving the aircraft engine assembling and disassembling efficiency and reducing the assembling and disassembling cost, along with high assembling, disassembling and positioning accuracy of an engine, and high automation degree and maneuverability.
Owner:成都立航科技股份有限公司
Direct-drive high-speed five-axis gantry machining center with replaceable milling head
ActiveCN102049705AImprove machining accuracyQuick responseFeeding apparatusLarge fixed membersAviationSlide plate
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.
Owner:通用技术集团沈阳机床有限责任公司
Modified graphene/polyimide resin composite material and preparation method thereof
InactiveCN102532896AUniform and stable dispersionSolve the problem of fragmentationPigment treatment with non-polymer organic compoundsPolymer scienceHome appliance
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.
Owner:FUDAN UNIV
Spacecraft attitude-track integrated backstepping tracking control method
ActiveCN106814746AImplement collaborative trackingLarge practical application engineering valueAttitude controlPosition/course control in three dimensionsControl mannerDynamic models
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.
Owner:黑龙江省工研院资产经营管理有限公司
Rendezvous docking method and device of space non-cooperative target
ActiveCN104316060ARealize rendezvous and dockingInstruments for comonautical navigationPosition/course control in three dimensionsPulse modulatorSpaceflight
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.
Owner:SHENZHEN GRADUATE SCHOOL TSINGHUA UNIV
Combined stress acceleration life test method of spaceflight drive assembly
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.
Owner:BEIHANG UNIV
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