37 results about "Space Science" patented technology

The invention provides a testing device for the radiation luminance gain of an ultraviolet image intensifier. The testing device comprises an optical platform and a guide rail arranged on the optical platform, wherein four sliding blocks are arranged on the guide rail, and a light source device, an integrating sphere, a testing dark box and a photometer are arranged on the four sliding blocks in sequence. The light source device emits ultraviolet light, the integrating sphere converts the ultraviolet light into uniform light, the tested image intensifier is arranged in the testing dark box, the uniform light irradiates the cathode surface of the image intensifier, and the photometer measures luminance of a fluorescent screen of the image intensifier; the set heights of the integrating sphere, the testing dark box and the photometer enable light in the testing dark box to be located in a straight line; the tested image intensifier is powered by an external power source. The testing device can detect the radiation luminance gain of the ultraviolet image intensifier, is simple in structure, and has significance on providing technical support for development of a novel detection imaging technology and offering help to the fields of power system detection, the space science and environmental protection research.

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 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 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 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 provides a frequency voltage converter with low additional noise. A phase-locked loop technology is used, a conversion relation of frequency voltage is established, a phase of a low-noise voltage-controlled oscillator is locked on measured signals, and a control end of the voltage-controlled oscillator is detected; low-noise frequency-to-voltage conversion of the measured signals with the frequency range greater than 100 kilohertz is realized, and requirements on measurement of ultra-stable laser frequency noise spectra can be met; and the frequency voltage converter can also be used for measuring frequency noise of a narrow-band laser. Compared with a method of measuring the line width of a laser to calibrate the frequency performance of the laser by using an optical fiber delaying method, the method for the frequency voltage converter is accurate. The measuring means for the level of the frequency noise of the ultra-stable laser is high in precision and is scientific. A noise source which affects the frequency stability of the laser is determined directly on the basis of a noise spectrum, so that a laser system is optimized in a targeted manner; the frequency noise of the laser is reduced; by the frequency voltage converter with the low additional noise, ultra-stable laser light and narrow-line-width laser light can be used for the fields of time frequency measurement, basic physical research, deep space detection, space science and the like; and the frequency voltage converter is significant.

The invention discloses a data processing method based on a multilayer information united index. The method comprises the steps that a data transmission data index comprising virtual channel frame counts, virtual channel identifiers and frame time is extracted from original data; virtual channel data is extracted according to the data transmission data index, and a virtual channel data index comprising the virtual channel frame counts, the virtual channel identifiers and the frame time is established; source packet data is extracted according to the virtual channel data index, and a source packet data index comprising the virtual channel frame counts, source packet counts, source packet identifiers and source packet time is established; and sequencing, splicing and repetition-removing operation are performed on the source packet data according to the source packet data index to generate continuous and complete source packet data. Through the method, the problem that the data with identical virtual channel frame counts and source packet counts will be deemed as repeated data and removed through traditional methods is avoided, the continuity and completeness of the data are guaranteed, and the processing demand of space science on satellite sounding data can be met.

A teaching and science popularization celestial globe of the invention relates to the fields of education technology, astronomy and science, school education and teaching of earth and space science, urban and rural science popularization, and celestial space research, and aims to solve the problem that astronomy and geography teaching in universities, middle schools and primary schools lacks planet space teaching instruments as well as design schemes and technologies for celestial globe manufacturing and using. The teaching and science popularization celestial globe is composed of a four-color map globe (1), a transparent celestial globe (2), an equatorial longitude large disc (3), a double-lug bow-shaped latitude half disc (4), a celestial axis (5), two metal circular-hole plain cushions (6), two rubber sleeves (7), and a base (8). The teaching and science popularization celestial globe is used for demonstrating the Tropic of Cancer and the Tropic of Capricorn of a globe, the celestial equator, the ecliptic, the moon's path, the celestial equator dividing line and the longitude and latitude space model on a celestial globe, the 24 solar terms in geography, 88 constellations in the starry sky, the approximate locations of stars and planets of 28 constellations of Chinese asterism, and teaching and science popularization of natural phenomena in knowledge of the 88 constellations in astronomy and earth and space sciences.

The invention discloses a non-momentum wheel satellite platform based on a magnetic buoyancy device control system. The non-momentum wheel satellite platform comprises a static cabin, a movable cabin and magnetic buoyancy devices, wherein a permanent magnet is arranged on each magnetic buoyancy device; the static cabin is connected with the magnetic buoyancy devices through the movable cabin; the static cabin comprises a load cabin body, a payload base, an attitude sensor, two gyroscopic sensors and a platform electronics sensor, wherein the load cabin body is fixed to the bottom of the static cabin; the platform electronics sensor is fixed to the static cabin; the two gyroscopic sensors are fixed to the surface of the load cabin body; and the attitude sensor is fixed to the right side of the load cabin body. The non-momentum wheel satellite platform based on the magnetic buoyancy device control system disclosed by the invention has the advantages of being low in cost, high in accuracy, long in life, and high in reliability; and the requirements of subsequent development of astronautical missions of comprehensive remote sensing to ground, communication, navigation, space science and the like can be better met.

The invention relates to a space science and application data retrieval method and system, a medium and a device, and the method comprises the steps of obtaining a fuzzy range coding set according toa retrieval range framed and selected in a map base map; acquiring data of Geohash codes of longitude and latitude of the central point in a fuzzy range code set from a database to form a fuzzy rangedata set; judging whether the longitude and latitude of the central point of each piece of data in the fuzzy range data set are within a retrieval range or not, and if yes, selecting the piece of datainto an accurate range data set; and screening the data in the accurate range data set according to a set retrieval condition to obtain a retrieval result data set. According to the method, the retrieval efficiency is improved, meanwhile, a large amount of storage resources and computing resources are saved, and the efficient conditional query of mass space science and application data is achieved.

The invention discloses a method and a device for improving the retrieval efficiency of space science and application data. The method comprises the following steps that: naming a data file to be stored, wherein the filename of the data file at least comprises at least two prefixes; when the data file is stored, through a way of filename analysis, constructing the search tree of the filename; storing one prefix of the filename into nodes except a root node of the search tree; enabling the leaf node of the search tree to correspond to the storage address of the data file; and when the data file is retrieved, through the comparison of retrieval condition and the branch of the search tree, obtaining the storage address of the data file so as to obtain the data file. The device comprises a naming module, a generation module and a retrieval module. By use of the method and the device, through a quick retrieval way of the filename, the quick retrieval of a space science and application data file can be realized, the occupation of calculation resources and storage resources is greatly reduced, so that retrieval time is greatly shortened, retrieval efficiency is improved, and user experience is better.

The invention discloses a method and device for dynamically adjusting space science and application data file storage. The method comprises the following steps that all data files on the storage medium are numbered; according to the degree of activity of each data file, the corresponding numbers of all the data files are sequenced; when the data files need to be cleaned, the data files are cleaned according to the sequencing result of the data file numbers. The device comprises a numbering module, a sequencing module and a cleaning module in sequence. By means of the method and device for dynamically adjusting space science and application data file storage, according to the activity degrees of the data files, the data files with low activity degrees are selectively processed offline, the data files which are not frequently used are eliminated, the time of the data files, which are always used, on a server is prolonged, the space science and application data sharing service requirement is met, and application and research value of data is given full play to greatly.

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 discloses a method for automatically gathering metadata of space science data facing a global change research and belongs to the technical field of information. The method comprises the following steps of: 1) selecting a data source, and regularly accessing the data source by a server to generate a download list and a download task; 2) accessing a data source server according to thecurrent download list and the download task to download a metadata file, and storing the metadata file to the server; 3) checking the quality of the downloaded metadata file, extracting a metadata item from the qualified metadata file, and calculating and converting; 4) storing a metadata file route and the metadata item into a metadata item database, and establishing an index; and 5) establishing a one-to-one corresponding mapping relation among the metadata file, the data of the metadata item database and the index data according to the file route, an id value of the metadata item database and an id value of an index item. By the method, massive global change space science data metadata resources which are distributed around the world can be queried in a one-stop manner.

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.

The invention belongs to the technical field of structural design of space experiment devices, and discloses a multilayer space experiment device with a high effective load mass ratio and a mounting method, aiming at solving the technical problems in the existing space science load design, a front vertical plate and a bottom plate are connected into an L-shaped structure through the bottom; a lower frame, a middle layer plate, and an upper frame are connected into a whole from bottom to top; the lower frame is connected with the bottom plate, the front end of the upper frame is connected withthe inner side of the front vertical plate, the bottom of a front ventilation structure is installed at the front end of the bottom plate, the upper portion of the front ventilation structure is connected with the outer side of the front vertical plate, and a notch-shaped skin is connected with the front vertical plate, the upper portion of the bottom plate, the lower frame and the upper frame ina surrounding mode. The upper cover plate is connected with the notch-shaped skin, the front vertical plate and the upper frame from the upper portion. Diversified functions and structural integrationand compact design are achieved, and the multilayer space experiment device is high in load structural mass ratio, compact in modular partition, convenient to assemble and debug, reliable in strength, rapid in iteration and low in cost.

The invention relates to a passive vibration reduction method of a space science experiment cabinet, which comprises the following steps of establishing a finite element simulation model of the spacescience experiment cabinet in pretreatment software, and carrying out sine sweep frequency analysis and solution to obtain acceleration response results of the whole and each component; obtaining theenergy distribution of the whole cabinet and each component on a resonant frequency point; laying a constraint damping layer at the position with large modal strain energy of the key assembly; and carrying out the sinusoidal sweep frequency analysis solution on the space science experiment cabinet after the damping vibration attenuation is laid, compairing the change conditions of structure responses before and after the additional constraint damping layer, and verifying the reliability of the passive vibration attenuation method. According to the passive vibration reduction method for the space science experiment cabinet, the existing structure does not need to be changed, the structural function of the cabinet body is not affected, the dynamic environment of instruments, equipment and effective loads is improved to a certain extent, the comprehensive performance index of the experiment cabinet is improved, and the method is high in reliability and high in robustness and is easy to achieve.

A Linear Tape Motors sequentially bends flexures to precisely position a payload within a large, linear range. Movement is backlash free. Flexure bending is also used to drive large forces, using efficient mechanical advantage, anchor the Tape Motor against back-slipping and prevent sticking and jamming malfunctions. Existing permanent magnet motor drive technology can be easily adapted to energize and control the flexure bending motions. Combining flexures with rare earth permanent magnets, provides ultra compact Linear Tape Motors with very high power and force densities that hold position with power off. Their operating range can be is as long as required. Thus, Linear Tape Motors are attractive for space science instruments, where precision positioning in ultra cold operating conditions is required and where low mass and low power are premium. But, they will be attractive to many other applications as well, especially where long range, safe, precise movements of large force payloads are required, where simplicity and reliability are important, where speeds are moderate to low and where operating temperatures are not so extreme as to demagnetize the permanent magnets. The Linear Tape Motor concept is novel but, it is simple and is easily adapted to modern permanent magnet motor technology, both the hardware materials and construction methods and the electronics and computer technology that controls the hardware. Development should be short and inexpensive, with high prospects of success.

The invention discloses an immersive spatial microgravity fluid telescience experiment parallel system and method. The system comprises a spatial experiment system; the parallel system further comprises a ground experiment system, and the ground experiment system comprises a remote analysis unit, a remote field unit, a remote operation unit and a remote prediction unit. All units of the space experiment system and all units of the ground experiment system coordinate with each other, and an immersive virtual environment is provided for ground operators. The system has the advantages that continuous multi-angle observation and accurate three-dimensional control of a remote space science experiment are realized, and a flexible, convenient and efficient environment is provided for space research; and through the method, the experiment in the space experiment system is controlled to be efficiently carried out, and meanwhile, the experiment in the space experiment system can also synchronously run with the prediction experiment of the ground experiment system outside the measurement and control area, so that the experiment efficiency of the space experiment system is greatly improved.

The invention discloses a semantic segmentation method and system for space science experiment data, and relates to the field of image processing. The method comprises the following steps: simulatinga space science experiment on the ground, acquiring ground experiment data, performing semantic segmentation annotation on the ground experiment data, and dividing the annotated ground experiment datainto a training set and a verification set; training a pre-adjusted UNet semantic segmentation network according to the training set and the verification set to obtain a semantic segmentation model;and obtaining space science experiment data, and inputting the space science experiment data into the semantic segmentation model to obtain a semantic segmentation result of the space science experiment data. According to the method, the problems of few space science experiment samples and non-uniform distribution are solved, accurate segmentation of space science experiment objects is realized, and the problem that real-time accurate semantic segmentation of small samples and small targets is difficult is solved.

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.