465 results about "Satellite bus" patented technology

The invention discloses a morning orbit computing power satellite, and belongs to the field of aerospace technology and space infrastructure. The satellite comprises a satellite platform and a computing force load arranged on the satellite platform. The satellite platform is provided with a condensation type energy system and a space pump drive fluid loop system. The condensation type energy system adopts an expandable condensation type solar cell array to generate power, switches a power supply mode according to an illumination period and an earth shadow period of a morning and night orbit, and supplies power to computing force loads and platform equipment. The space pump drive fluid loop system adopts an expandable flexible radiation cooling plate for heat dissipation, heat dissipation is conducted on computing force loads through a fluid loop, and a heating assembly is arranged to prevent a working medium from being frozen under the low-temperature working condition. Through the expandable structure and the orbit environment adaptability design, continuous energy supply and effective heat management are provided for the computing power load in the morning and night orbit environment, and high-power-consumption computing power load in-orbit stable operation is supported.

The invention discloses a high-performance satellite platform based on a real-time operating system and a wireless bus and a working method of the high-performance satellite platform, and belongs to satellite communication technologies, future deep space exploration and low-orbit satellite constellations. On the basis of an original structure of a satellite platform, a real-time operating system is effectively combined with a wireless bus system, and the real-time operating system comprises a kernel module, a communication module, an equipment driving module, a file system module, an application interface module, a safety module and a fault management module. The wireless bus system comprises a physical layer, a data link layer, a network layer, a transmission layer and an application layer. According to the invention, efficient and reliable communication and task execution capabilities are provided for a satellite platform, the requirements of real-time performance and reliability of a satellite in a complex environment are effectively met through modular design and tight work of the system, and meanwhile, complex lines and interfaces brought by a wired system are avoided.

The invention belongs to the technical field of space remote sensing surveying and mapping, and particularly relates to a monitoring system and method for a front and rear view visual axis included angle and absolute direction of a surveying and mapping camera. The method comprises the following steps: S1, through side sway of a satellite platform, taking a time for sky imaging calibration as a reference time; s2, calculating a rotation matrix from a front and rear view ground camera measurement coordinate system to a star camera coordinate system at a reference moment; s3, calculating respective thermal deformation matrixes of the star camera coordinate system, the front-view camera measurement coordinate system and the rear-view camera measurement coordinate system; s4, obtaining a real-time rotation matrix from the measurement coordinate system of the front-view camera to the coordinate system of the star camera and a real-time rotation matrix from the measurement coordinate system of the rear-view camera to the coordinate system of the star camera at the measurement moment; and S5, carrying out arc cosine calculation on the two absolute pointing vectors to obtain a visual axis included angle between the front-view camera and the rear-view camera at the measurement moment. According to the invention, while the geometric accuracy of the surveying and mapping camera is ensured, the real-time performance of measurement and the comprehensiveness of subsystem monitoring are realized at the same time.

The invention discloses a heaven and earth integrated multi-domain fused automobile high-level automatic driving system, which realizes more comprehensive and non-blind area sensing and positioning of an automatic driving automobile through multi-domain information fusion of a satellite platform, a cloud platform, an automobile end platform and the like, and promotes comprehensive upgrading of comprehensive efficiency of an intelligent traffic system. Based on cloud error broadcasting and a high and low orbit satellite fusion enhancement technology, the problem of automobile communication loss caused by the fact that single ground communication is limited by base station coverage is solved; based on a cloud reinforcement learning architecture, the communication network stability of the space-ground integrated system is improved through adaptive switching of a communication network; a road semantic map and a decision control experience pool are established based on vehicle high-precision trajectory data collected by a platform, and the limitation of the perception ability of a bicycle is made up through cloud federal learning scene experience sharing; the vehicle end dynamically updates a cloud road semantic map through local map matching; and information support is provided for realizing a chassis multi-domain fusion technology based on high-precision positioning.

The invention relates to the technical field of hydrological data measurement, in particular to a sky-ground-water integrated hydrological monitoring system. The system comprises the following modules: a space-based monitoring module, an air-based monitoring module, a foundation monitoring module, a water-based monitoring module and a hydrological early warning module. Specifically, a hydrological monitoring area is patrolled through a satellite platform, and terrain height data is monitored in a dot-matrix mode; and scanning the hydrological monitoring area along the sine wave path through the unmanned aerial vehicle, and generating a three-dimensional topographic image in combination with the topographic height data. According to the invention, through a data processing technology, a real-time monitoring technology and a deep learning technology, three-dimensional, real-time and accurate monitoring of water level, flow, terrain and sediment hydrological elements is realized; scientific, reliable and comprehensive data support is provided for the fields of water resource management, flood control and disaster reduction and ecological environment assessment; meanwhile, a hydrological early warning model is constructed, and hydrological abnormal conditions are captured in time.

The invention relates to the technical field of construction site monitoring, in particular to a construction site monitoring system and equipment based on a remote sensing image technology, and the system comprises a remote sensing image collection module, an unmanned aerial vehicle platform, a low-orbit satellite platform and a ground mobile platform which all acquire remote sensing images of a construction site through sensors; the multi-modal fusion module is used for performing data fusion processing according to the remote sensing image to obtain multi-modal data; when the system is used, the unmanned aerial vehicle platform, the low-orbit satellite platform and the ground mobile platform are used for collecting remote sensing image data, various targets on a construction site are conveniently and accurately recognized, misrecognition is reduced, and the system is beneficial for images under complex environments such as different illumination and weather conditions and images under the complex background of urban buildings. The construction site target is identified and positioned, and in a data-deficient and new construction site environment, the self-supervised learning and transfer learning technology can effectively improve the learning ability of the model, reduce the dependence on annotated data, and quickly adapt to new task requirements.

The invention discloses a super-large plane array type space computing power center, and belongs to the field of space technologies and space infrastructures. The space computing power center is deployed in a morning and evening orbit and comprises a plurality of computing power satellites which are physically docked in orbit through a docking mechanism. Each computing power satellite comprises a satellite platform, and a computing power load, a condensation type energy system and a space pump drive fluid loop system which are arranged on the satellite platform, and a docking mechanism for inter-satellite in-orbit physical docking is also assembled on the satellite platform. A plurality of computing power satellites form a planar array type rigid whole body through the docking mechanism, and energy scheduling among the light condensation type energy systems is realized based on the docking mechanism. According to the space computing power center, through multi-satellite physical docking and energy collaborative scheduling, the energy utilization efficiency and the power supply reliability of the system are improved.

The invention discloses a spinning spacecraft nutation characteristic analysis method and an active suppression system. The spinning spacecraft nutation characteristic analysis method comprises the following steps: step 100, decomposing a whole satellite system into a satellite platform body, a three-axis superconducting magnet system, a rotary separation device, a momentum exchange device and a separable load according to the structural characteristics of the whole satellite system; and step 200, based on the orbit and structural characteristics of the satellite, proposing a derivation hypothesis about a whole-satellite kinetic equation so as to construct an ideal modeling environment. According to the nutation characteristic analysis method of the partial spinning spacecraft, mass mutation is added, the analysis method can be used for on-orbit delivery spacecrafts and can also be used for other spacecrafts with mass mutation characteristics, a fuzzy pid control method is adopted in the control method, parameter adjustment is conducted on pid through a fuzzy rule base, the parameter adjustment efficiency is high, and the parameter adjustment accuracy is high. The executing mechanism is a superconducting magnetic moment device, control moment is generated through interaction of superconducting magnetic moment and a geomagnetic field for active suppression, and regulation and control are flexible.

The invention discloses a platform micro-vibration measurement method based on a laser inter-satellite link, which can be applied to measurement of in-orbit satellite platform micro-vibration and has the advantages of no occupation of satellite resources and simple system structure compared with a traditional mode of adopting an accelerometer for measurement. By accurately analyzing the spectrum characteristics of the micro-vibration, the source of the micro-vibration can be determined and the micro-vibration can be compensated, so that the communication reliability is improved. The platform micro-vibration measurement method based on the laser inter-satellite link comprises the following steps: 1) determining a laser terminal conversion relation according to the architecture of a laser terminal light beam pointing mechanism; 2) eliminating an environment measurement error, and fitting and eliminating a platform motion track; and 3) micro-vibration characteristic parameters are extracted.

The invention relates to a satellite rotating cabin radio frequency signal transmission system and method based on a photoelectric slip ring, and the system comprises a baseline conversion module which is located in a satellite rotating cabin and is used for converting a radio frequency signal into an optical signal or converting the optical signal into the radio frequency signal; the photoelectric slip ring is located in the rotary table, the photoelectric slip ring comprises a smooth slip ring and an electric slip ring, the photoelectric slip ring is driven by the rotary table to rotate, and the photoelectric slip ring is used for non-contact transmission of optical signals or radio frequency signals; and the platform conversion module is located in the satellite platform cabin, and the platform conversion module is used for converting the radio frequency signal into an optical signal or converting the optical signal into the radio frequency signal. According to the satellite rotating cabin radio frequency signal transmission system based on the photoelectric slip ring provided by the invention, the photoelectric slip ring is used for realizing single-channel or multi-channel transmission of multiple radio frequency signals, and light weight and miniaturization of complex signal transmission of a satellite-borne system are facilitated.

The invention discloses an ozone precursor monitoring and early warning method and system based on satellite remote sensing recognition, particularly relates to the technical field of environment monitoring, and is used for solving the problem that in the prior art, a remote sensing satellite is difficult to capture daytime dynamic changes of ozone precursors due to limitation of orbits and observation time periods. The method comprises the following steps: acquiring remote sensing image data of a plurality of satellite platforms in different observation periods, and executing target recognition and pixel separation by adopting a spectral unmixing algorithm; calculating and correcting the signal deviation of the track overlapping region by using the cross consistency; generating continuous ozone precursor distribution data in combination with a multi-period interpolation algorithm; performing emission source analysis through an atmospheric chemical equilibrium model to generate concentration evolution information; an abnormal value is marked based on a dynamic monitoring threshold value, and a monitoring and early warning signal is generated by combining a geographic information system, so that high-precision dynamic monitoring and real-time early warning of the ozone precursor are realized.

The invention provides a whole bus-based agile satellite platform and a construction method thereof. The whole bus-based agile satellite platform comprises a bus, an integrated electronic computer, a power supply controller, a data server and subsystems, the bus comprises a satellite control bus, a satellite power bus and a high-speed information bus; a comprehensive electronic computer serves as a control center management satellite control bus, a power supply controller serves as an energy control center management satellite power bus, and a data server serves as a data interaction center management high-speed information bus. Each subsystem of the satellite platform carries out interaction between a remote control instruction and telemetering data through a control bus, carries out energy supply and instruction pulse output through a power bus, and carries out mass data distribution and interaction through a high-speed information bus. According to the invention, a satellite platform realizes satellite interface generalization and standardization by using a full-bus design, platform single-machine rapid integration and whole-satellite efficient test are supported, the supported load type can be flexibly configured, and the method has agility and engineering value.

A remote sensing satellite proximity search subsystem testing system and method relates to the field of remote sensing satellite ground testing, and comprises a satellite platform and a ground testing system, and the ground testing system comprises a server, a general control system and interpretation analysis software; the satellite platform comprises an on-satellite comprehensive electronic subsystem and a distributor; the master control system sends a remote control instruction to the server, obtains satellite telemetry information and satellite data from the server and sends the satellite telemetry information and the satellite data to the interpretation analysis software; the server sends a remote control instruction to the comprehensive electronic subsystem, and satellite telemetry information and satellite data are obtained from the comprehensive electronic subsystem; the comprehensive electronic subsystem sends a remote control instruction to the proximity search subsystem and receives satellite telemetry information and satellite data of the proximity search subsystem; the proximity search subsystem carries out state setting according to the remote control instruction and feeds satellite telemetry information and satellite data back to the comprehensive electronic subsystem. The method is suitable for ground testing of the remote sensing satellite proximity search subsystem.

The invention relates to the technical field of space optics, in particular to a low-impact separation device between an optical camera and a satellite platform, which comprises a controller and at least six separation supports, and the at least six separation supports are uniformly arranged at intervals in the direction of the outer envelope circumference of the satellite platform and the optical camera. The at least six separation supports are divided into a plurality of separation support sets, and the separation supports of each separation support set are adjacent to the separation supports of at least one other separation support set. The separation support comprises two supports which are connected and symmetrically arranged, one support is connected to the optical camera, and the other support is connected to the satellite. The support comprises a shell, a support butt joint end and an explosive bolt. The explosive bolt is connected to the support butt joint end and located in a containing space defined by the support butt joint end and the shell. And the controller is used for receiving a detonation signal to activate the explosive bolts, so that the explosive bolts of different separation support groups are detonated at different time, and the explosive bolts of the same separation support group are detonated simultaneously.

The invention provides a method and a system for improving the precision of an on-orbit SAR antenna pattern of a light and small satellite. The method comprises the following steps: S1, establishing an SAR antenna mechanical flatness field model; s2, establishing a thermal deformation field model of the SAR antenna; s3, establishing an SAR antenna T / R active channel amplitude-phase data field model; s4, SAR antenna machine, thermal and electrical errors are converted into a unified phase coordinate system; s5, establishing a satellite attitude pointing error model, and performing unified physical field conversion; and step S6: respectively carrying out sensitivity analysis on the direction of the antenna pattern aiming at the satellite attitude and the SAR antenna mechanical, thermal and electrical errors. According to the method, ground test and on-orbit data are adopted to compensate for SAR antenna mechanical, electrical and thermal phase errors and satellite platform attitude errors, so that the precision of an SAR antenna pattern model is further improved, and the on-orbit image quality is practically guaranteed.

An inter-satellite communication time synchronization integrated system based on a laser microwave composite antenna comprises an electronics unit which is in communication connection with a satellite platform; the laser microwave composite antenna unit is in communication connection with the electronics unit; wherein the electronics unit, the laser microwave composite antenna unit and the satellite platform cooperate with each other to realize establishment of an inter-satellite laser communication link or an inter-satellite microwave communication link and synchronization of high-speed communication measurement time. Technical characteristics of a microwave communication system and a laser communication system are comprehensively considered, meanwhile, a laser-microwave composite link receiving and transmitting system is utilized, the problems that the communication rate of an inter-satellite microwave link is low and the time synchronization precision is difficult to improve are solved, high-precision time synchronization and inter-satellite relative position information can be provided, the communication efficiency can be improved, and the time synchronization precision is improved. And the autonomous navigation capability and the communication service providing capability of the satellite system are enhanced.

The present disclosure provides a method, device, equipment and medium for calculating right ascension and declination based on Euler angles, which relates to the field of aerospace technology. The method includes: obtaining the initial observation pointing parameters of a satellite camera, the first rotation Euler angle of the coordinate system unit basis vector corresponding to the initial observation pointing to the body coordinate system unit basis vector corresponding to the satellite platform, and the second rotation Euler angle of the coordinate system unit basis vector corresponding to the satellite platform to the coordinate system unit basis vector corresponding to the final observation pointing; calculating the final observation pointing parameters of the satellite camera according to the initial observation pointing parameters, the first rotation Euler angle and the second rotation Euler angle; calculating the right ascension and declination of the satellite camera according to the final observation pointing parameters. The method can quickly and accurately solve the celestial right ascension and declination from the initial pointing of the camera, and can fully consider various rotation sequences of aerospace engineering, with a wide range of applications and strong applicability.

The invention discloses a satellite-borne SAR (Synthetic Aperture Radar) radar target real-time guiding method based on ADS-B (Automatic Dependent Surveillance-Broadcast) signals, which relates to the technical field of radar control, and comprises the following steps: receiving Beidou dual-band signals and global ADS-B signals in real time, resolving by adopting a carrier phase double-difference ionosphere elimination combinatorial algorithm, and obtaining a satellite-borne SAR generating satellite platform pose data including satellite position component data, satellite speed component data and satellite attitude component data; inputting the airspace target point cloud data set into an adaptive airspace clustering algorithm, dynamically adjusting a clustering neighborhood radius by using satellite speed component data, and outputting central geographic coordinates of a target dense area; fusing the beam pointing vector and the angular velocity data through a beam-attitude dynamic coupling controller, and generating a phase shifter code value adjustment instruction; the neighborhood recognition range is dynamically adjusted through the real-time motion state of the satellite, and the positioning precision and timeliness of the dynamic airspace target dense area are remarkably improved. And the continuous monitoring capability and the guiding precision of the time-sensitive target are improved.

The invention discloses an antenna layout method for a communication satellite. The antenna layout method comprises the following steps: S1, determining directions of antennas in an unfolded state and a spatial relationship between the antennas; s2, adjusting the relationship between the assembly and the satellite platform, and ensuring that the field of view of the antenna is not shielded in an unfolded state; s3, the relation between the antennas and the satellite platform in the folded state is adjusted, and it is guaranteed that no interference exists between the antennas and between the antennas and the satellite platform in the folded state; s4, solving a rotation axis unit vector and a rotation angle of the antenna; if the first constraint judgment condition is not met, returning to the step 2; if yes, executing the step 5, and rotating according to the rotating shaft unit vector and the rotating angle to obtain a corrected layout position; 6, if the second constraint judgment condition is not met, returning to the step 2; and if yes, outputting a result. According to the method provided by the invention, the antenna layout which meets the use requirements of an antenna system, the internal space envelope of a fairing and the size limitation of a satellite platform can be obtained.

The invention provides a moon orbit formation navigation microsatellite inter-satellite measurement system and method, and relates to the technical field of deep space exploration, the system comprises a master satellite and a slave satellite, and a Ka inter-satellite link is established between the master satellite and the slave satellite; the master satellite and the slave satellite both send timing inter-satellite measurement signals, receive timing inter-satellite measurement signals from the opposite side, measure the time difference between a local timing signal and the received timing signal of the opposite side to obtain the pseudo-range of the satellite, and the two satellites exchange the pseudo-range through an inter-satellite link to solve the inter-satellite distance and the time difference. Accurate time synchronization of two satellites is not needed, a measurement result can be directly obtained on the satellites, ground calculation is not needed, and ground resources are saved; the satellite platform and the antenna design of the slave satellite are simplified, and the weight and the cost of the satellite are reduced.

A progressive local rolling optimization inter-satellite cooperative task autonomous planning method comprises the following steps: defining a satellite constraint model according to satellite platform resource constraint and load working capability; receiving an inter-satellite cooperation task window annotated by a user, and planning and generating an inter-satellite cooperation task; receiving a data transmission task window uploaded by a user, and planning and generating a data transmission playback task; in an inter-satellite cooperative task window time period, receiving a guiding task from an inter-satellite link in real time, and defining the guiding task as an inter-satellite situation task; performing task preprocessing on the inter-satellite situation task received in the inter-satellite cooperative task; determining the position of the task inserted into the existing task execution sequence by adopting a greedy algorithm, and generating a new task sequence; carrying out data transmission task insertion; performing task constraint condition check to generate a final to-be-executed task; and after a new task is received, rolling planning is performed according to the rolling planning frequency to update the task sequence in real time.

The invention discloses a satellite-borne space-based measurement and control method based on a non-ground network and related equipment. The method is used for a satellite-borne space-based measurement and control device, the satellite-borne space-based measurement and control device is arranged on a low-orbit satellite platform, and the method comprises the following steps: respectively obtaining real-time orbit parameters of a low-orbit satellite, GNSS positioning information and a pre-stored high-orbit satellite coverage information table; based on the current orbit parameter, the GNSS positioning information and a high-orbit satellite coverage information table of a high-orbit satellite pre-stored or periodically updated from a satellite service computer, calculating a space-time relationship between the low-orbit satellite and a cell coverage range; and under the condition that it is predicted and determined that the cell coverage of the target high-orbit satellite is about to enter according to the time-space relationship obtained through calculation, waking up in advance and initiating cell search and a control flow of accessing at any time. The problems that an existing space-based measurement and control technology is high in construction cost, limited in multiple access capacity and poor in dynamic adaptability can be solved.

An integrated spaceborne SAR satellite platform, belonging to the field of spacecraft technology, solves the problems of poor temperature uniformity of existing satellite platform mounting plates, large SAR antenna envelope, inability to meet high-precision single-unit installation requirements, and low structural strength. The platform comprises: a SAR antenna, a feed assembly, a single-unit mounting plate, an external single-unit device, an internal single-unit device, a platform main frame, and a solar sail; the platform main frame, single-unit mounting plate, and solar sail constitute the cabin; the solar sail is located below the platform main frame; the SAR antenna, feed assembly, and external single-unit device are mounted on the outer surface of the single-unit mounting plate; the internal single-unit device is mounted on the inner surface of the single-unit mounting plate; the single-unit mounting plate includes a honeycomb panel, metal gaskets, and pre-embedded heat pipes; the honeycomb panel includes a honeycomb core and a honeycomb panel skin; the metal gaskets are connected to the pre-embedded heat pipes. This invention is applicable to satellite platform spacecraft platforms, spacecraft configuration and layout design, spacecraft structural thermal control design, spacecraft on-orbit monitoring, and SAR satellite on-orbit active compensation.

The invention relates to a satellite rotating cabin signal transmission system and method based on a photoelectric slip ring, and the system comprises a baseline conversion module which is located in a satellite rotating cabin and is used for converting a digital signal and an optical signal into a coupled optical signal or converting the coupled optical signal into a digital signal and an optical signal; the photoelectric slip ring is located in the rotary table, the photoelectric slip ring comprises a smooth slip ring and an electric slip ring, the photoelectric slip ring is driven by the rotary table to rotate, and the photoelectric slip ring is used for non-contact transmission of optical signals or electric signals; and the platform conversion module is located in the satellite platform cabin, and the platform conversion module is used for converting the digital signals and the optical signals into coupled optical signals or converting the coupled optical signals into the digital signals and the optical signals. According to the satellite rotating cabin signal transmission system and method based on the photoelectric slip ring, satellite-borne high-speed electric signals, digital signals and optical signals are transmitted in a rotating mode through the photoelectric slip ring, and lossless and high-speed transmission of data can be achieved.

The utility model belongs to the technical field of spacecraft ground tests, and particularly discloses a space gravitational wave detection satellite formation physical simulation verification device which comprises a main console, three satellite simulation modules, a vision measurement module and a simulation module. Each satellite simulation module comprises a satellite simulator; the satellite simulator comprises a satellite platform and two laser interferometers, the two laser interferometers are arranged above the satellite platform, and a preset included angle is formed between the laser emitting directions of the two laser interferometers; the satellite simulator is arranged above the air suspension assembly; the simulation module comprises a plurality of board cards, the board cards are electrically connected, the pose and disturbance of the space gravitational wave detection satellite are simulated and calculated, and a simulation result is fed back to the main console; the main console sends a control instruction to the satellite simulation module; and the vision measurement module tracks and positions the pose of the satellite simulation module in real time and feeds back the pose to the main console. According to the invention, physical simulation verification can be carried out on the performance of the space gravitational wave detection satellite formation.

The invention discloses a satellite-borne ultrahigh-resolution SAR (Synthetic Aperture Radar) system and a working method thereof. The system comprises a signal processor, a frequency multiplication unit, a receiver, a synthesis network front end, a traveling wave tube amplifier group, an amplitude limiting low noise amplifier, a magic T, a waveguide switch, a circulator, a waveguide load and an umbrella antenna, the system is loaded on an agile satellite platform, and large-angle scanning imaging of a target area is achieved by means of maneuvering of the platform. Various working methods are provided through combination of output signals of different ports of the magic T. The ultra-high resolution imaging system has the advantages that ultra-high resolution imaging superior to centimeter-level resolution is realized, the working mode is flexible, the reliability is good, the system composition is simple, the volume and the weight of the product are reduced through centralized transmitting and receiving, the weight is light, the heat consumption is small, and the engineering development cost and difficulty are reduced.

The embodiment of the invention discloses a mountain fire detection method and device based on satellite processing and electronic equipment, and can solve the problems of how to improve the mountain fire recognition precision and meet the real-time requirement of power grid mountain fire monitoring. The method comprises the following steps: acquiring satellite remote sensing image data; detecting the satellite remote sensing image data through a preset target detection model in the satellite platform to obtain initial forest fire data included in the satellite remote sensing image data, the initial forest fire data being used for indicating a suspected forest fire-containing area determined through the target detection model; multi-dimensional feature extraction is carried out on the initial mountain fire data to obtain target features, and the target features comprise at least one of color features, texture features and shape features; the target features are detected through a preset decision tree classification model in the satellite platform, target forest fire data are determined, and the target forest fire data are used for indicating the forest fire-containing area determined through the decision tree classification model.

The invention relates to the technical field of satellites, in particular to a three-super platform actuator eddy current sensor fault autonomous reconstruction method. Comprising the following steps: according to a parallel mechanism kinematics relationship of each actuator, determining a first relationship between axial displacement measured by an actuator eddy current sensor and a load relative to a six-degree-of-freedom pose of a satellite platform; determining a parallel mechanism kinematics relationship of the fault-free eddy current sensor, and determining a second relationship between the axial displacement and the load measured by the fault-free eddy current sensor and the six-degree-of-freedom pose of the satellite platform; according to the first relation and the second relation, matrix reconstruction is carried out on the remaining fault-free actuator eddy current sensors, and an autonomous reconstruction matrix is obtained; and according to the autonomous reconstruction matrix and the measurement of the fault-free actuator eddy current sensor, obtaining all actuator eddy current measurement values of the actuator where the fault eddy current sensor is located. According to the method, when the eddy current sensor has a fault, the eddy current sensor distribution array is reconstructed, and three-super control is recovered.

The invention discloses an expansion multiplexing type satellite ground support system and a working method. The method comprises the following steps: S1, the satellite ground support system accepts a work task demand; s2, analyzing and planning a specific task to form a specific task plan; s3, according to the task plan, realizing deduction of a task plan scheme through simulation of an environment situation and a satellite flight situation; s4, generating a control instruction for the satellite, and verifying the control instruction; s5, sending the verified control instruction to a ground measurement and control system, and uploading the instruction by the ground measurement and control system; and S6, performing real-time monitoring and evaluation on a satellite task execution process, and performing alarm processing on abnormal conditions in the task execution process. The method can be expanded and reused for ground support of multi-model new technology test series satellite platforms, can continuously expand the computing power according to requirements, and provides a simulation verification platform for new technology test verification.

The invention relates to an agile satellite relay real transmission method and device based on attitude extrapolation and a medium. The method comprises the steps that S1, a servo controller receives a relay satellite orbit sent by a satellite platform and extrapolates the position and speed of a relay satellite; s2, receiving GPS broadcast data, and determining the position and speed of a satellite platform; s3, attitude broadcast data are received, and satellite platform attitude extrapolation is completed; and S4, the relay antenna is driven to track the relay satellite through coordinate conversion and antenna limiting judgment. According to the method, relay link resources can be effectively utilized, the data return efficiency can be improved, meanwhile, the agile satellite can realize multifunctional and fast-response imaging efficiency by utilizing fast maneuvering, and the timeliness of data acquisition can also be ensured.