37 results about "Space Science" patented technology

The invention relates to a satellite-borne accelerometer nonconservative force data accurate calibrating method based on a novel dual-satellite adjacent energy difference principle in the technical field of crossing of satellite geodesy, geophysics, space science and the like. The satellite-borne accelerometer nonconservative force data accurate calibrating method comprises the steps of: on the basis of establishing a reference disturbing potential-free dual-satellite disturbing potential difference observation equation, by using priori information of a global gravitational field model, establishing a novel dual-satellite adjacent energy difference observation equation on the basis of the dual-satellite adjacent energy difference principle, and fitting a scale factor and an offset factor of calibration parameters so that satellite-borne accelerometer nonconservative force data is accurately calibrated. The method has high calibration precision and is suitable for rapid calibration of single-satellite and dual-satellite accelerometer data, thus earth gravitational field inversion precision can be effectively enhanced.

The invention discloses a guide control device and method for microgravity tower falling, and relates to the field of space science and application. The device comprises an active guide assembly, a passive guide assembly and a pose detection assembly, the active guide assembly comprises a guide device, a guide rail and a guide controller, the guide rail is installed on a load cabin, and the guidedevice and the guide controller are installed in a falling tower in the moving direction of the load cabin; the passive guide assembly comprises a permanent magnet array and a conductor plate, the conductor plate is installed on the load cabin, and the permanent magnet array is arranged in the falling tower in the moving direction of the load cabin; the pose detection assemblies are arranged in the falling tower in the moving direction of the load cabin. The guide control device provided by the invention is suitable for microgravity tower falling, solves the problems of traditional roller guide vibration and abrasion, realizes static and low-speed suspension through the optimal design between the active guide force and the passive guide force, and achieves the technical effects of miniaturization and light weight of a magnetic suspension guide system.

The invention relates to a space science task displaying system based on augmented reality. The displaying system specifically comprises a virtual displaying material manufacture module, a displayingmaterial management library and multiple pieces of augmented reality equipment, wherein the virtual displaying material manufacture module is used for collecting the displaying materials of differentspace science tasks, converting the displaying materials into the virtual displaying materials of a uniform data format, and sending the virtual displaying materials to the displaying material management library; the displaying material management library is used for carrying out storage and organization management on the virtual displaying materials according to a space science task category anda satellite category, and providing a corresponding access interface; the multiple pieces of augmented reality equipment are used for scanning and identifying the real world, obtaining the data information of a real scene in the real world, identifying the science task which needs to be displayed, and generating a real scene; meanwhile, virtual displaying materials corresponding to the science task which needs to be displayed can be obtained to generate a virtual scene; and the virtual scene and the real scene are subjected to registration positioning, perspective relationship and blocking relationship processing, and are blended and displayed to realize augmented reality display.

The invention relates to a practical burglar mesh. The practical burglar mesh specifically utilizes the scaling ladder climbing theory; window sashes can be flexibly dismantled, each window sash is provided with hooks and multiple window sashes can be fast combined to form a scaling ladder, thus the device which can be flexibly dismantled can be provided by the invention, the escaping time can be shortened and high-level inhabitants can escape. The design of the invention utilizes physics, ergonomics, environment space science, psychology and other theories.

The invention discloses a quick release device for a load of a space science experiment. The quick release device comprises a movable interface board assembly and a load pushing assembly, wherein the movable interface board assembly comprises a rectangular movable interface board, two opposite long edges of the movable interface board are respectively and correspondingly provided with a plurality of installation lugs which protrude and extend outwards, each installation lug is provided with an installation hole which penetrates through the upper side and the lower side of the installation lug, each installation lug is respectively and fixedly provided with a positioning ring in a corresponding mode, the center holes of the positioning rings correspond to the installation holes, a push ring is arranged on one side of each center hole in the circumferential direction, the push rings extend in the direction parallel to the axis of the center holes to the direction away from the installation lugs, a connector seat is arranged on the movable interface board, and the load pushing assembly comprises a standard load seat, a thrust wedge, a connecting rod assembly and a handle locking assembly. The quick release device has the advantages that an experimental load unit can be quickly and conveniently inserted, pulled, fixed and locked on orbit, and operation of astronauts is facilitated.

The invention relates to a satellite-borne accelerometer nonconservative force data accurate calibrating method based on a novel dual-satellite adjacent energy difference principle in the technical field of crossing of satellite geodesy, geophysics, space science and the like. The satellite-borne accelerometer nonconservative force data accurate calibrating method comprises the steps of: on the basis of establishing a reference disturbing potential-free dual-satellite disturbing potential difference observation equation, by using priori information of a global gravitational field model, establishing a novel dual-satellite adjacent energy difference observation equation on the basis of the dual-satellite adjacent energy difference principle, and fitting a scale factor and an offset factor of calibration parameters so that satellite-borne accelerometer nonconservative force data is accurately calibrated. The method has high calibration precision and is suitable for rapid calibration of single-satellite and dual-satellite accelerometer data, thus earth gravitational field inversion precision can be effectively enhanced.

The invention relates to a movable furnace body space crystal growth furnace, which belongs to the field of space material science. The device of the present invention comprises a furnace shell (1, 2) and a suspension shock-absorbing mechanism (3, 10), a heating furnace furnace body (4, 11, 12, 13), a furnace body moving mechanism (5), a sample lifting and indexing mechanism ( 6), heat insulation bottom plate (7) and sample ampoule (8). The space crystal growth furnace of the present invention has high working temperature, low average power consumption, and low vibration and noise of the whole machine, which is suitable for carrying out space material science experiment research on platforms such as returnable satellites or spaceships, and can realize multiple completions per cycle in flight tests. Crystal growth in the station, the maximum working temperature can reach 1350°C.

A frequency-to-voltage converter with low additional noise. The invention adopts phase-locked loop technology to establish the conversion relationship of frequency and voltage, lock the phase of the low-noise voltage-controlled oscillator to the measured signal, and then detect the control of the voltage-controlled oscillator. It realizes low-noise frequency-to-voltage conversion with the frequency range of the measured signal greater than 100 kHz, which can meet the measurement requirements of ultra-stable laser frequency noise spectrum; it can also be used to measure the frequency noise of general narrow-band lasers, which is better than measuring laser line by fiber delay method. The method of wide calibration laser frequency performance is more accurate, and the present invention provides a higher-precision and more scientific measurement method for the frequency noise level of ultra-stable lasers, and directly determines the noise source that affects the laser frequency stability based on the noise spectrum, so as to be targeted Optimizing the laser system and reducing the frequency noise of the laser is of great significance in the application of ultra-stable lasers and narrow linewidth lasers in time-frequency measurement, basic physics research, deep space exploration, space science and many other fields.

The invention discloses a global change research-oriented automatic space science data gathering method, belonging to the field of information technologies. The method comprises the steps of: (1) periodically accessing data sources and generating downloading tasks by a server; (2) according to current downloading tasks, downloading metadata files and storing in the server and carrying out qualityinspection, metadata item extraction, computation and conversion on the downloaded files; (3) storing metadata file routes and metadata items in a metadata item database and setting up indexes; (4) setting up a mapping relation among the metadata files, metadata item database data and index data and providing a retrieving interface; and (5) querying whether solid data to be queried exists or not according to a querying condition by the server, if not, generating a solid data downloading task to download according to a data reservation application and carrying out the quality inspection and metadata item updating on the downloaded data. The method can be used for querying and acquiring mass global change space science data resources which are distributed at all parts of the world in a single-stop-type manner.

The invention discloses a method for driving a nonmetal flyer with laser, which includes the step: enabling the laser generated by a laser device to enter an ablation layer on optical glass, enabling materials on the ablation layer to instantly evaporate, gasify and ionize so that high-temperature and high-pressure plasmas are generated, and under restraint of the optical glass, enabling high-pressure shock waves generated by the plasmas to act on the other face of the ablation layer and be positioned on a nonmetal film in front of an incident area, so that the residual non-metal film is sheared and driven at a high speed, and the high-speed flyer is formed. The method and an implementation device can make up the defect that a current laser-driven flyer can only emit metallic grits so that non-metal grits can be emitted, and can also be applied to the field of high-pressure physics, space science, material micro-forming technology, rapid initiation of explosives and the like. When a space debris environment is simulated in a laser-driven flyer manner in the space science, the debris environment can be efficiently simulated by alternately using various flyer materials.

The invention provides a novel HOM interference theory based gravity instrument. The instrument comprises an entangled source (1), a delayer (2), a first beam splitter (3), a stress sensor (4), a prism (5) to be dropped, a reference prism (6), a second beam splitter (7), a first detector (8), a second detector (9), a coincidence measurement logic calculator (10), an atomic block (11) and a controller; when in use, the delayer (2) is adjusted to delay to enable destructive interference between the idle light and signal light flowing through the initial position, then the prism (5) to be dropped freely falls down to the end position, the free falling time is recorded, the delayer (2) is adjusted to delay again to enable destructive interference between the idle light and the signal light flowing through the end position, and finally the gravity acceleration can be obtained through the controller according to the difference between two delay, and the difference between the initial time and the end time. According to the instrument, the HOM interference theory is utilized to achieve the high precision measurement of the gravity accelerator; the instrument can be widely applied to the fields of metering, surveying and mapping, physical geography, ocean exploration and space science.

The invention relates to the field of interleaving techniques such as satellite geodesy, geophysics, space science and the like, and provides a satellite gravity inversion method based on a two-star energy interpolation principle. In the method, the global gravity field is accurately and rapidly inverted by introducing high-accuracy inter-satellite distance interpolation of a satellite-loaded K waveband measuring instrument into two-star relative orbits kinetic energy and further establishing a two-star energy interpolation observation equation. The method has the advantages of high satellitegravity inversion accuracy, definite physical meanings of the observation equation, contribution to error analysis of a gravity satellite system, easiness for sensing high-frequency gravity field signals and low requirement on the computer performance. The sensing accuracy of a 120-step GRACE earth gravity field can be increased substantively, so that the two-star energy interpolation principle method provided by the invention is an effective method for establishing a new generation high-accuracy and high-space-resolution global gravity field model.

The invention relates to a method for measuring the distance of celestial bodies. The method comprises the following steps of setting angle measuring devices for measuring angles of the celestial bodies, selecting a first measuring point and a second measuring point on the same meridian on the surface of the earth, wherein the first measuring point and the second measuring point are respectively provided with the first angle measuring device and the second angle measuring device, and the first measuring point and the second measuring point are separated with a certain latitude; aiming at the same celestial body with the two measuring points, recording measuring angles, and computing angle difference of the two measuring points (the positions of a level point and a vertical point of the celestial body on the Earth take the centre of the earth as a base point, form a diagonal line with the celestial body, and form a triangle having three straight lines and the total degree of three internal angles of 180 DEG, the angle of the centre of the Earth is utilized for computing an radiation angle of the celestial body, and the condition that the angle of the centre of the earth is measurable is utilized for solving the difficult problem that the angle of the celestial body is immeasurable); subtracting latitude distance of the two measuring points from the angle distance of the two measuring points to obtain the radiation angle of the celestial body; and taking the radius of the earth as a radix, extrapolating that the angle distance per one second equals to 1,309,778,457 kilometers, and at last dividing the distance by the radiation angle of the celestial body to obtain the distance from a measured star to the earth's core. The invention is beneficial to the development needs of space science.