144 results about "Space technology" patented technology

The invention relates to a dexterous hand teleoperation control method based on Kinect human hand motion capturing. The hardware for realizing the method comprises a Kinect sensor, a computer and a remote robot dexterous hand system. A mixing movement outline model is used for tracking the outline of the hand, hand posture tracking is realized through a particle filter algorithm, the far-end situation is observed through feedback image information transmitted by a robot in real time, and therefore a specific operation task is implemented. Through the movement outline model combining depth information and YCbCr skin color detection space technology, the problem that a real solution can not be obtained easily when an image contains high noise or a target is provided with a weak boundary is solved. A particle filter posture detection method based on template matching is adopted, and the human hand three-dimensional posture with high-dimensional characteristics can be detected and estimated. Through a master-slave operation combining a manual control mode and a program mode, convenience and rapidness are realized, and the guiding performance and usability of human-machine interaction are represented.

Affordable commercial service platforms in space focusing on customer affordability, quality microgravity services, innovation and combining five emerging space technologies. The invention provides an integrated approach to microgravity services in orbit. First, the reusable launch vehicle (RLV) offers affordable transportation services, platform reboost, and eliminates platform subsystems of propulsion, RCS, liquid storage/resupply, and the like. Second, deployable structures are not heavy for the launch, but expand in orbit. Third, orbital phone networks offer customers control of unmanned experiments. Fourth, an enhanced robotic system transfers payloads. Fifth, manufactured thin film solar cells in orbit offer advantages including weight/cost reductions. The orbital service platform has a low initial cost, expands as the market demands, is repairable, offers quality unmanned microgravity, leads to production facilities using similar hardware and offers numerous affordable commercial services.

A transponder satellite communication navigation positioning system relates to the field of space technology. The system is equipped with a high-precision atomic clock at a ground communication navigation reference station, and the satellite orbit data is given by the satellite orbit determination system; the satellite integrity is given by the monitoring system The data forms the navigation message, and the ranging code composed of pseudo-random codes forms an integrated baseband signal, which is modulated by spread spectrum to form a navigation signal carrier, which is transmitted through the antenna and forwarded by 3 to 9 satellites in a certain geometric distribution in space The device converts the frequency and forwards the downlink, and broadcasts the signal to the coverage area; the ground user terminal receiving device receives the navigation signal carrier, and despreads and demodulates it to obtain the navigation data, thereby determining the position, speed and time of the user terminal receiving device. The invention has the advantages of low investment, guaranteed accuracy, convenient and flexible system maintenance and management, and dual functions of navigation and communication, so that the navigation and positioning accuracy can reach meter-level precision or be better than meter-level precision.

The invention discloses a three-level acceleration type spiral plasma propulsion device. The three-level acceleration type spiral wave plasma propulsion device is characterized in that an antenna is connected with an RF (Radio Frequency) power source, the antenna and a discharge chamber are fixedly arranged in a sleeve, and an electromagnetic coil is fixedly arranged on the outer circumferential surface of the sleeve in a surrounding way; the rear part of the discharge chamber is provided with a rotating electric field ion acceleration system, and the rotating electric field ion acceleration system comprises four graphite electrodes which are uniformly and symmetrically arranged on the outer circumferential surface of the sleeve; the tail end of the rotating electric field ion acceleration system is provided with an electromagnetic spray pipe ion acceleration system, and the electromagnetic spray pipe ion acceleration system comprises a conical expanding spray pipe of which one end is connected with the tail part of the discharge chamber, and the electromagnetic coil. According to the three-level acceleration type spiral plasma propulsion device disclosed by the invention, the rotating electric field acceleration system is adopted for carrying out secondary acceleration on a plasma, acceleration is further carried out through the electromagnetic spray pipe, and a three-level acceleration effect is formed, thus the thrust is generated by efficiently accelerating ions, the work of a propulsor under high power can be realized, the reliable performance of high ion ejecting speed and high propulsion capacity can be realized, wide application prospect is obtained, and a high-performance power platform can be provided for future space technology development.

The invention relates to a passive radar detection method by use of synergistic or asynergistic satellite signals to detect low altitude targets, belonging to the technical field of space technology, which comprises a satellite and a ground passive radar system; wherein, the system comprises a plurality of detection stations and a data processing station, and interactive communications are conducted between the detection stations and the data processing station by means of radio or optical fiber transmission method. The signals, expanded frequency measurement codes and the signals reflected on low altitude aircrafts by and of the satellite, especially high radiation power satellite, are received by the detection station receivers of the passive radar with high sensitivity. After correlation, the path difference between the direct radiation signals of the satellite and the signals from the same source reflected by the low altitude targets can be derived; then, a group of passive detection equations can be established; the solutions can be obtained simultaneously. And a three-dimensional position coordinate of the low or super low altitude targets can be thus acquired. The invention has the advantages of huge detection area, small blind area, the capability of detecting low or super low aircrafts like cruise missiles and super low altitude airplanes passively at long range, and extensive application value for military use.

The invention discloses a burst type navigation signal system and a receiving method, relating to the space technology. A signal broadcast carrier can be a navigation satellite, a space balloon or an airship and the like; a navigation signal of the burst type navigation signal system comes from a burst type satellite navigation beacon broadcasted by a straight hair type satellite navigation system or a forwarding type satellite navigation system through a satellite or an intermittent satellite navigation signal; a user terminal uses a high-gain antenna to carry out the time-sharing sky coverage in manners of pitching and azimuth 2-dimensional scanning; and a satellite within the direction scope of the high-gain antenna has the additional signal to interference ratio advantage endowed by the high-gain antenna, thereby the anti-interference effect is reached. With the utilization of the burst signal system and the receiving method, the problem of a large-area phased array antenna in the traditional airspace anti-interference measure is effectively avoided, and the time-frequency domain anti-interference measure is also convenient to carry out simultaneously; and the burst type navigation signal system is easily arranged on a smaller or high-mobility weapon platform and has low cost and high reliability.

The invention discloses a composite nanostructure based on a three-dimensional porous transition metal carbide Ti3C2MXene and a general preparation method thereof, and belongs to the field of nanomaterials. The three-dimensional composite structure is composed of a three-dimensional porous Mxene-supported inorganic nanostructure, and has a honeycomb hierarchical porous structure. A precursor of atwo-dimensional transition metal carbide and a metal-organic framework compound is subjected to high-temperature pyrolysis or a chemical reaction in an inert or reactive atmosphere to prepare the composite nanostructure with a controllable size. According to the composite nanostructure, stacking of MXene itself is inhibited, an active surface area, porosity, and ion permeability of MXene are increased, and thereby a surface interface of MXene is efficiently used. At the same time, introduction of the metal-organic framework compound realizes uniform and stable compounding of the three-dimensional porous MXene and an inorganic nanomaterial, the fundamental difficult problem that plagues exerting and application of inorganic nanomaterial performance is solved, and the composite nanostructurehas wide application prospects in the fields such as catalysis, energy, photo-electricity, space technology, and military industry.

An optical system of satellite-borne differential absorption spectrometer comprises a relay optical system and an Offner imaging spectrometer system. The relay optical system is composed of a relay reflector, relay lenses and a color separation filter. The Offner imaging spectrometer system is composed of an incident slit, a convex grating, and a concave reflector. The relay optical system uses the color separation filter to split a detection waveband to form four channels, which are focused by four groups of relay lenses to the incident slit of the spectrometer. Light at each waveband entersthe spectrometer from the incident slit of the spectrometer, is split by the convex grating, and has the light path turned and focused on a detector. The invention utilizes a relay reflector to turn the light path, and utilizes the color separation filter to split the detection waveband into four channels, to therefore improve the detection resolution of the system, ensure measurement accuracy and realize compact volume of the whole optical system. The Offner imaging spectrometer has excellent imaging spectrum performance and reduced distortion. The invention facilitates miniaturization and weight reduction of the whole system, and is suitable for space technology.

The invention discloses a method for performing real-time measurement on the track and the position of a satellite or an aircraft, relating to space technology. The method comprises: A) establishing a database in a ground central station; B) transmitting ranging codes and telegraph texts by ground branch microminiature measurement terminals, forwarding by the satellite, receiving by heavy aperture antennae of the ground central station to obtain the telegraph text message and the pseudo ranges between the microminiature measurement terminals and the phase center of the heavy aperture antennae of the ground central station; C) subtracting two sections of pseudo ranges which are received by the antennae on the same side of the central station by the same satellite via two adjacent microminiature measurement terminals, using the pseudo range difference to solve the observation equation to obtain the high precision position or track solution of the satellite; D) using the measured values of the pseudo ranges from the same microminiature measurement terminal to different satellites to calculate to obtain the precision positions or pseudo ranges of the microminiature measurement terminals; and E) subtracting the obtain precision positions or pseudo ranges with the predetermined precision positions or pseudo ranges of the microminiature measurement terminals to obtain deviation values, using the deviation values to perturbate the observation equation to correct the track positions of the satellites to obtain the millimeter-level position coordinate values of the satellite track.

The invention belongs to the crossing field of space technology and computer vision, and discloses a monocular space target distance-measuring and angle-measuring method. The method comprises the following steps: (1) receiving a one-frame image of a space target shot by a single camera, namely a practically shot image Q; (2) pre-treating the practically shot image Q, extracting the space target from the background, thus obtaining a pretreated image S; and then detecting the target according to the pretreated image S, if the space target is completely located in the view field of the camera, entering the step (3), otherwise, entering the step (5); (3) extracting the feature of the space target and recognizing the posture of the space target; (4) computing the three-dimensional center distance Delta p and the posture angle of the space target; and (5) continuing processing until all images are completely processed. The method provided by the invention is simple in process; according to the method provided by the invention, only the three-dimensional structure and size information of the target are needed to be obtained, the target is not needed to be the cooperative target, and any star target is neither needed to be set on the target; and the method provided by the invention has the characteristics of wide distance-measuring range and high precision.

The invention discloses a polymer solid electrolyte membrane and preparation method thereof. The polymer solid electrolyte membrane comprises a polymer matrix and a composite ionic liquid, and the composite ionic liquid comprises lithium salt and N-containing heterocyclic compound. According to the invention, by introducing the ionic liquid into the polymer solid electrolyte membrane, the both advantages of the ionic liquid and the the polymer solid electrolyte membrane are achieved, and the self-supporting electrolyte with independent from water, high conductivity, good security, good ionic conductivity and high mechanical property is obtained. The invention can be widely used in the fields of lithium ion battery, and has a good application prospect in the fields of electronics, medical treatment, space technology, electrochrimic technique, photoelectricity, sensors and the like.

The invention relates to the space technology, and to the improvement of the star sensor calibration method. The invention uses the calibration system which including air cushion platform, single-star starlight simulator, star tracker, two-dimensional axial turntable platform and data-processing computer, its steps being: establishing point spread function model, establishing a centroid algorithm formula, establishing a centroid algorithm pixel frequency error model, and data acquisition. The invention provides a more practical point spread model; improving satellite sensor calibration precision; the calibration model is simple and easy to calculate.

An error detection and correction system for the data storage of a miniature satellite onboard spacecraft computer belongs to the technical field of the computer storage in a miniature satellite in the space technology. The system is characterized in that the system comprises a static memory storage unit assembly and a field programmable device FPGA, wherein the FPGA comprises a Hamming error correcting circuit, a triple modular redundancy decision circuit, two both-way tristate gates, an address logic circuit and a mode control circuit; according to the address contents of an external central processing unit, the mode control circuit selects any of the three modes of Hamming error correction, triple modular redundancy decision and error-free control; and according to the storage space configured by the address logic circuit controlled by the mode control circuit, the storage unit assembly consisting of 12 static memory storage units carries out the read-write operation of the data signal inputted by the central processing unit through the two both-way tristate gates. As the system respectively separates the memory space of the memory storage unit assembly into flexible and adjustable groups according to the three modes, the memory can be flexibly distributed according to the error correcting modes so as to be fully utilized.

The invention discloses an analysis and calculation method for orbital shading of a geostationary orbit satellite solar cell array and relates to the field of the space technology. The method includes the steps of 1, analyzing annual average change rules of solar illumination angle of a geostationary orbit satellite; 2, analyzing change rules of orbital shading of the satellite solar cell array by stars; 3, calculating and simulating orbital shade area of the cell array according to the analysis results. The analysis and calculation method has the advantage that the basis for the design of solar cell array substrate configuration is provided.

The invention relates to a crosslinkable, radiation-resistant, highly-flame-retardant, low-smoke, zero-halogen cable material and a preparation method of the cable material. The cable material comprises the following raw materials by weight parts of 5 to 30 parts of high density polyethylene, 20 to 60 parts of a polyolefin elastomer, 5 to 20 parts of modified ethylene-propylene diene copolymer, 160 to 200 parts of flame retardant masterbatches, 3 to 8 parts of a first antioxidant, 0 to 5 parts of a light stabilizer, 1 to 5 parts of a first lubricating agent, and 1.5 to 6 parts of a crosslinking sensitizer. The cable material provided by the invention can be used for the fields of electric wires and cables in the nuclear power industry, communication cables and sheathes in a space technology, irradiation disinfection products of medical instruments, and the like by adding the flame retardant masterbatches in combination with the high-efficiency antioxidant and radiation-resistant resin without additionally adding any anti-radiation agent. The preparation method of the crosslinkable, radiation-resistant, highly-flame-retardant, low-smoke and zero-halogen cable material provided by the invention has the advantages of being simple in process, easy to operate and low in cost.

The invention provides an unlocking device made of a shape memory material and belongs to the field of space technology. By the adoption of the unlocking device made of the shape memory material, the problems that impulse is high, potential pollution hazards exist, the structural size is large, and redundant matter is generated are solved. The unlocking device made of the shape memory material comprises a screw, a spring, an axial check ring, a split washer, a base and an elastic pin. The spring is compressed and fixed to the upper bottom surface of the screw. The spring is sleeved with the axial check ring. The inner diameter of the spring is larger than the radius of the screw. The split washer is located between the screw and the axial check ring and between locating shaft shoulder of the screw and the base. At least one of the matched surfaces between the base and the split washer is a conical surface, and at least one of the matched surfaces between the shaft shoulder on the head of the screw and the split washer is a conical surface. The spring exerts axial force on the axial check ring and the screw, the axial check ring moves upwards along the screw, the split washer is free of radial constraint, the locating shaft shoulder of the screw exert the axial force on the split washer, and then the split washer moves in the radial direction. By the adoption of the unlocking device made of the shape memory material, no redundant matter is generated, an extra collecting device is not needed, a small structure is achieved, no pollution is caused, smoke leakage is not caused, and the problem of hidden danger caused by smoke leakage of initiating explosive devices is avoided.

The invention discloses a low-orbit constellation disposition method based on assistance of martian atmosphere, and relates to a martian constellation disposition method under the martian atmosphere and a gravity system thereof. The low-orbit constellation disposition method belongs to the field of aeronautical and space technologies. According to the low-orbit constellation disposition method, a speed pulse which is applied for entering the atmosphere from an original orbit and a speed pulse that is applied for making an aircraft enter an objective orbit are solved through optimizing a control rate which satisfies an aerodynamic force requirement. A detector releases the carried aircraft at an apareon position and makes the aircraft enter the atmosphere through applying the speed pulse which is required for making the aircraft enter the atmosphere from the original orbit. In the atmosphere, aerodynamic-assisted orbit transferring is performed through optimizing the preset control rate. Furthermore the orbit of the aircraft is fixed to the objective orbit through applying the speed pulse which is required for making the aircraft enter the objective orbit. A plurality of constellation aircrafts are disposed to the objective tracks which correspond with the constellation aircrafts in a one-to-one manner, thereby realizing disposition of a whole constellation. The low-orbit constellation disposition method has advantages of low energy consumed in the disposition process, no rigid requirement for the objective orbit, and flexible disposition process.

The invention provides an overweight compensating guidance method and trajectory reshaping guidance method conducting correction based on a pseudo-spectral trajectory optimization result, and belongsto the field of the space technology, the weapon technology and guidance control. The overweight compensating guidance method and trajectory reshaping guidance method specifically comprises the stepsthat firstly, a fight model is established, and guided missile pneumatic parameters and atmosphere model parameters are determined; secondly, a guided missile motion equation is established, and an optimal control problem is established; thirdly, the pseudo-spectral method is used for solving the optimal control problem; fourthly, polynomial fitting and other manners are used for fitting the pseudo-spectral optimal result; and fifthly, according to the pseudo-spectral optimal result, the typical trajectory reshaping guidance rule and the typical gravity compensation guidance rule are corrected. The overweight compensating guidance method and trajectory reshaping guidance method has the advantages that the final velocity of a guided missile is increased, and the attacking effect of the guided missile is greatly improved; through fitting of the pseudo-spectral optimal result, the guidance rule is segmented, the guided missile flight speed is increased in a front section, the guidance parameters are adjusted in a rear section, and the guidance rule conforms to the fall angle constraint; and the black hole phenomenon of the typical gravity compensation guidance rule is avoided, and important significance is achieved for actual application.

The invention provides a subscription method of satellite data compatible with multiple data formats. The multiple data formats are characterized in that with the development of the space technology, ground communication device protocols or telemeasuring data types can change due to the change of a telemeasuring system, and the formats of different satellite test data on different platforms are diversified. The subscription method of the satellite data compatible with the multiple data formats mainly includes the steps that variable configuration content of the ground communication device protocols, the test data types and the like is stored through an extensible markup language, after the satellite test data are received, matched communication protocol templates are automatically found, analyzed and distributed to subscribers through packaging components, then a program is separated from configuration information, and the problem of inconvenience that subscription logic of the satellite data needs to be rechanged when the data formats change is solved. According to the method, the satellite test data of different formats can be compatible, subscription requests of different subscribers can be met, and subscription universality and subscription extensibility of the test data between different satellites of different models and user data customizability are achieved.

An apparatus includes at least one boom including a tip and a foot and being designed and arranged to be rolled up to form a roll. The tip is located in a radial inward region of the roll and the foot being located in a radial outward region of the roll. The apparatus further includes a unit being designed and arranged to unfold the at least one boom and including a bearing being designed and arranged to cooperate with the foot in a way that the boom in the region of the bearing at the beginning of the unfolding process has an enlarged cross section. Especially, the apparatus may be used in space technology for unfolding a solar sail.

A multi-wavelength LD (laser diode) array pumped solid laser with low power consumption and a wide temperature operating range relates to a laser, in particular to a laser without water-cooling and with the wide temperature operating range. The laser is capable of stably working within the wide temperature range while complete machine plug efficiency is effectively improved. Bars with different working center wavelengths are selected according to required operating temperature range and by referring to different absorption coefficients of laser crystals on light different in wavelength to form a multi-wavelength LD array by arraying according to optimal light field distribution principle. The Nd:YAG laser capable of stably working within the temperature range of 10-40 DEG C is designed, and the structural model of the laser is shown in figures. The plug efficiency of the laser can also be effectively improved. A method has the advantages of stability, energy saving, convenience and the like, and is applicable to laser research. The laser can be applied to the field of military, national defense, space technology, laser detection and the like.

The present invention discloses a multi-protocol interface data collection device based on a SpaceFibre interface, belonging to the field of space technology application. The device comprises an FPGAmodule, a SpaceFibre interface, a Serdes serial-parallel conversion module, a 1394b physical layer module, a CAN control receiving and dispatching module, a RS232 level conversion module, a 1394b interface, a CAN interface and a RS232 interface. The FPGA module comprises a data collection module, a FIFO cache module, a protocol conversion module and a SpaceFibre IP node module. The present invention further provides a multi-protocol interface data collection method based on a SpaceFibre interface which achieves data compatibility among the external 1394b interface device, the CAN interface device and the external RS232 interface device and the SpaceFibre network or a SpaceFibre device to enrich the application ranges of the external 1394b interface device, the external CAN interface device, the external RS232 interface device and the SpaceFibre network or the SpaceFibre device and meet the development trends of the miniaturization and the intelligence of a current space electronic communication system.

The invention discloses a SpaceFibre bus data acquisition method based on a PCIe interface, belonging to the application field of space technology. The invention divides a plurality of virtual channeldata buffers received by a SpaceFibre bus from a SpaceFibre network, By analyzing the data of SpaceFibre network broadcast channel, the scheme of collecting the virtual channel data is established, and then the data of each virtual channel is collected to the computer through PCIe interface. The method provided by the invention solves the incompatibility problem of the interface between the traditional computer and the SpaceFibre bus. The data acquisition of SpaceFibre bus by traditional computer is realized, which provides a reliable basis for the debugging of SpaceFibre on-board network, and increases the application range of SpaceFibre on-board network.

The invention discloses a laser beam-combined space debris removal system based on a separated multiple-telescope form, relates to the field of space technology and solves the problem that elements in optical paths are deformed due to heating in the process of space debris removal by the conventional ground high-energy laser emission system. According to the system, multiple beams of high-power lasers are emitted to space debris from the ground, and an ablation effect on the space debris is realized through the superposition of energy of the multiple laser beams. In order to improve the action effect of the laser beams on the space debris, the adaptive optical technology is adopted to correct optical element thermal deformation and disturbance caused by atmosphere in the system; meanwhile, the laser star guiding technology is used in the system, so that the action effect on faint space targets is improved. The space debris removal system is a manner for realizing the removal of space debris on the earth surface; the principle of energy superposition is used in the system, and multiple beams of lasers are used for emission, so that space debris at different orbit altitudes can be processed, the technology realization difficulty of each key unit is reduced, the maintenance is convenient and the cost is reduced correspondingly.

The invention discloses a quick-response heat flow meter for non-contact measurement of heat flow density. The heat flow meter comprises multi-sensitive-surface measuring heads, a heat sink body, a heat sink body temperature thermocouple, a data acquisition device and a data processing and displaying device. As the temperatures of two identical materials with different absorption rates are different under the action of radiation heat flows with the same intensity, the temperature difference relations between radiation heat flow density and two sensitive surfaces are established. Meanwhile, system errors are further avoided. Accordingly, the developed high-accuracy transient radiation heat flow meter has the advantages that the heat flow meter can meet space technology requirements and be used in a vacuum environment and can also be used in a ground convection environment; the heat flow meter is simpler in structure; the heat flow meter can work continuously and can be connected in series to form a thermopile so that temperature difference thermoelectric force can be increased, and errors in the measuring process are reduced.

The invention discloses a microcrystalline graphite purification preparation process which comprises the following steps: adding 40-50 parts by weight of natural microcrystalline graphite of which the granularity is 200-3000 meshes and the purity is 80-90% into 30-42 parts by weight of pure water which is free of impurity ions such as Ca<2+>, Mg<2+> and CL<->, uniformly stirring till paste is formed, further adding 4-8 parts by weight of strong acid, heating to 40-100 DEG C, performing stirring reaction for 4-6 hours, filtering, washing filter cakes with water till the pH value is neutral, and drying, thereby obtaining the natural graphite of which the purity is greater than or equal to 99.990%. The high-purity natural graphite which is 99.990-99.998% after being purified according to a liquid-phase chemical method can meet use requirements of high-tech fields such as the atomic energy industry and the space technology, and is low in cost and stable in quality.

A wide-area enhancement method for forwarding satellite navigation systems, involving space technology, building 25-100 forwarding satellite navigation wide-area reference stations, 10-50 receiver monitoring stations, 2 data processing centers and 3 - 4 earth uplink stations. The data processing center centrally processes the code and carrier phase measurement data from the wide-area reference station dual-frequency receiver, and also processes the measurement data from the receiver monitoring station to generate satellite ephemeris vector corrections and master control station signal uplink time delays Correction number, completeness, reliability and other information. The data processing center generates wide-area augmentation system navigation messages from the generated information, arranges them on the original navigation messages, or modulates them on other uplink frequencies in the C-band, and broadcasts them to the augmentation systems in each region with synchronous orbit satellites and inclined orbit satellites. Users, so that users of the forwarding satellite navigation wide area augmentation system can obtain high navigation accuracy, integrity and reliability.