390 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 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 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 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.

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.

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 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 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 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 relates to a ladder type bidirectional folding and unfolding solar wing system based on a shear fork mechanism. The system comprises a satellite platform; the two connecting rods are arranged on the two sides of the satellite platform and are symmetrically distributed; the bidirectional folding and unfolding solar wing connected with the connecting rod comprises a foldable fixed sailboard assembly which is connected with the connecting rod and is folded and unfolded in the transverse direction and a foldable turnover sailboard assembly which is rotationally connected with the foldable fixed sailboard assembly and is folded and unfolded in the longitudinal direction, and the foldable fixed sailboard assembly comprises a plurality of fixed sailboards which are hinged end to end; the foldable turnover sailboard assembly comprises a plurality of turnover sailboards which are hinged end to end; the scissor fork mechanism is connected with the foldable fixed sailboard assembly and comprises a supporting assembly rotationally connected with the foldable fixed sailboard assembly and a scissor fork unfolding assembly rotationally connected with the supporting assembly and capable of being folded or unfolded. Compared with the prior art, the invention has the advantages of light weight, simplified structure, high storage ratio, high reliability and stable and controllable deployment process.

The invention belongs to the technical field of spaceflight on-orbit services, and particularly relates to a complex environment target recognition approaching method based on dual-band imaging under a satellite platform, which is based on three common sensors, namely an infrared camera, a visible light camera and a laser range finder, and is characterized in that an image information source adopts infrared and visible light multi-spectrum fusion; software time synchronization and an image registration mode are introduced into a synchronization mode, infrared fast mean value judgment suitable for on-satellite embedding is introduced, an earth background suppression technology and a target information enhancement scheme are added, fusion tracking and ranging cooperation of vision and a laser range finder is adopted, and meanwhile, a laser range finder start-stop strategy is designed according to on-satellite power consumption. According to the invention, the defect of insufficient robustness of a single sensor facing an earth complex background observation target in the view field change process of a satellite platform is overcome.

The invention belongs to the field of remote sensing satellite general assembly design, and particularly relates to a load assembly and a general assembly method. The load assembly comprises a satellite platform assembly, a main feedback electric assembly and an auxiliary reverse arm unfolding assembly, the main feedback electric assembly is formed by integrating a main reverse assembly and a feed receiving calibration assembly, and the auxiliary reverse arm unfolding assembly is formed by integrating an auxiliary reverse arm unfolding assembly and an auxiliary reverse arm unfolding assembly. The main feedback electric combination body is formed by integrating a main reverse combination body and a feed receiving calibration combination body, and the auxiliary reverse unfolding arm combination body is in linkage unfolding / folding with a satellite platform through a mechanical interface. According to the method, satellite structure assembly, load supporting structure assembly, load combination system assembly and butt joint of the load combination and the satellite platform are implemented in stages and steps, multi-attitude adjustment and zero-gravity installation are combined, and ground adjustment accurate measurement and high-precision installation of the load combination and the platform are ensured.

According to the capturing and tracking integrated space laser communication terminal and the inter-satellite laser communication method, a capturing mechanism and a tracking mechanism of the laser communication terminal adopt the same mechanism assembly, when capturing and link building are carried out in orbit, a large-stroke fast reflecting mirror is used for carrying out directional scanning, and after an opposite satellite laser communication terminal receives a light beam of the satellite laser communication terminal of the opposite party, the capturing and tracking are carried out; the laser communication terminals of the two parties immediately switch to fine tracking link establishment; and if the satellite position of the opposite side exceeds the scanning range of the satellite laser communication terminal of the local side, pre-pointing and angle unloading correction are carried out by using a satellite platform of the local side. The design that receiving communication light and transmitting communication light of receiving and transmitting optics of the laser communication terminal share one optical assembly is simple and reliable, a large divergence angle is adopted, a large scanning area is achieved, the capturing time is shortened, and the capturing probability is improved. According to the invention, a capturing and tracking integrated design scheme is adopted, so that the system complexity, weight, size and power consumption of the laser communication terminal are reduced.

The invention relates to an on-orbit fault diagnosis and health management method and system based on a satellite-borne photoelectric slip ring. The method comprises the steps that a photoelectric conversion system is constructed, the photoelectric conversion system comprises a photoelectric slip ring, a baseline conversion module and a platform conversion module, the baseline conversion module is located in a satellite rotating cabin, and the platform conversion module is located in a satellite platform cabin; performing state monitoring on the platform conversion module and the baseline conversion module by using a platform integrated electronic and load management unit; state monitoring and safety management are carried out on a CAN bus between the satellite rotating cabin and the satellite platform cabin; and executing independent power distribution on the platform conversion module and the baseline conversion module, and autonomously controlling power-on and power-off according to a health criterion. According to the method provided by the invention, the dynamic threshold is designed for the secondary power supply, and seamless switching of the main power supply and the standby power supply is realized; the problems of delay and error codes of CAN bus communication between a satellite rotating cabin and a satellite platform cabin are solved by combining strategies such as double-bus handshake and FPGA reset.

A relay satellite platform communication device for space-ground networking belongs to the field of relay satellites, and is formed by system-level integration of four core technologies including a structure-electrical integrated central bearing frame, an integrated three-surface pluggable modular system, a conformal antenna integrated multifunctional shell and an internal and external cooperative heat pipe heat dissipation network. A framework-module-skin three-layer deep coupling system framework is constructed, six faces of a center bearing structure are divided into a movable area and a static area, the movable area is used for achieving function reconfiguration and on-orbit maintenance, and the static area is used for deploying a high-reliability platform foundation system which is fixed once launched. According to the invention, the problems of difficulty in on-orbit maintenance, low reliability and efficiency bottleneck caused by discrete architecture and functional coupling of a traditional relay satellite are solved, and a high-reliability, high-flexibility and easy-to-maintain satellite platform foundation is provided for constructing a dynamic reconfigurable space-ground integrated information network.

The invention provides a satellite temperature field grouping mapping method and system, and the method comprises the steps: building a finite element model of a whole satellite, carrying out the grouping of a satellite platform model and an external load model, and exporting a corresponding. Bdf file; reading information of nodes, units and groups in the. Bdf file, and writing the information into the. Inp file; simulating satellite in-orbit temperature distribution, outputting temperature field data of a satellite platform and an external load, and respectively storing the temperature field data in corresponding. Csv files; importing a. Csv file of the temperature field data and a. Inp file of the finite element model into Abaqus software; establishing a grouping mapping working condition of the temperature field data; the temperature field data are grouped and mapped to a finite element model; and reading the mapped node information and node temperature value, and writing the node information and node temperature value into a. Bdf file. According to the method, temperature field mapping among different models can be realized, the automation degree is high, the temperature field mapping time is greatly shortened, the pretreatment steps are reduced, and the working efficiency is greatly improved.

An inter-satellite laser terminal capturing method without a rough capturing and tracking device comprises the following steps: calculating and adjusting a satellite platform to a target attitude according to position information of a target satellite and the satellite and an attitude real-time value of the satellite, and determining a target value of an optical axis pointing vector at the same time; dividing the captured uncertain region (parent region) into a plurality of sub-regions, and numbering the sub-regions according to a rectangular spiral track; enabling the optical axis to point to the first sub-region for light beam scanning, detecting the light spot intensity to recognize an effective light spot, and calculating the angle pointing to the target vector according to the miss distance and the galvanometer angle; if the preset capturing frequency threshold value is reached, the scanning range is narrowed and scanning is continued; when effective light spots are detected again in the reduced scanning area, it is judged that capturing is completed, and a tracking state is switched to; and if all the sub-regions are scanned and are still not captured, ending. According to the invention, efficient and accurate capturing of the inter-satellite laser terminal under the condition of no rough capturing and tracking device is realized, and the reliability and stability of inter-satellite communication are improved.

The invention discloses a satellite-borne high-integration emission phased-array antenna, which is characterized in that an antenna radiation unit array, a secondary feed network and a power supply and control circuit of a T component array are integrated in a PCB (Printed Circuit Board) sub-array, and a phase shift and attenuation control channel, a power amplifier and a primary feed network are integrated in each T component; a minimum function unit of the phased-array antenna is formed by one PCB sub-array and a T assembly array installed on the PCB sub-array, and a plurality of minimum function units are combined through a radio frequency expansion mother board, so that modular connection and signal distribution are realized, and different emission requirements are met; the minimum function unit, the radio frequency expansion mother board and the thermal control board are longitudinally arranged in a vertical stacking mode, the wave control power supply module, the up-conversion amplification module and the vertical stacking module group are transversely arranged in the same plane, and a heat conduction path is greatly shortened. According to the invention, the longitudinal profile height, the overall size and the system weight of a traditional brick type phased-array antenna are obviously reduced, and the antenna can better meet the application requirements of a low earth orbit flat plate type satellite platform.

The invention discloses a satellite integrated electronic system. According to the system, a heterogeneous FPGA architecture is adopted, a satellite service management module is deployed on a first FPGA chip, and a measurement and control module and an encryption and decryption module are integrated on a second FPGA chip. The system realizes fault isolation through the design of an independent power domain and a reset domain of the measurement and control and encryption and decryption module, ensures that a measurement and control link is not interrupted through a hardware bypass channel in the second FPGA chip, and improves the reliability of the system. The encryption and decryption module adopts an encryption mode mapping graph and management system, supports a dynamic key management mechanism triggered based on three events of periodic switching, mapping graph updating and periodic parameter updating, can flexibly configure an encryption strategy according to an on-orbit task demand, and improves the security and adaptability of the system. The problems that in the prior art, chip performance and cost are difficult to balance, the integration level is low, and a whole machine fails due to a single-point fault are effectively solved, and the method is particularly suitable for a microsatellite platform with strict requirements for cost, size and reliability.

The invention discloses a strabismus mode ground interference source positioning method and system based on a satellite platform, a storage medium and electronic equipment, and the method comprises the following steps: firstly, carrying out the range pulse compression of a received interference signal according to the related parameters estimated by the prior information of an orbit and the time-frequency relation; constructing a matched filter, realizing linear range migration correction, and eliminating a first-order component of range migration in a range frequency domain-azimuth time domain; a CTF search algorithm is used, and under different search distances, distance direction search is achieved through a cooperation mechanism of global search and step length constraint local optimization; constructing matched filters at different distances to realize quadratic term range migration correction, and eliminating a range migration quadratic term in a two-dimensional frequency domain; azimuth distance compression is carried out at different distances, so that signals are focused; and obtaining a two-dimensional positioning position opposite to the interference source through coordinate transformation. According to the invention, the problem of signal defocusing caused by the distance-orientation strong coupling effect is solved in the squint mode, and the interference source positioning precision is significantly improved.

The application discloses a general service method and system applied to a satellite platform and belongs to the field of remote sensing / communication satellite platforms, and solves the technical problems that in the prior art, due to the need of new load access for new adaptability development and test work, a long development cycle is caused, and under the condition that test is not comprehensive, there is a risk of load service failure, and maintenance is difficult. Step 1, a general service template table is constructed; step 2, after the general service template table is filled in, the general service template table is converted into satellite on-service instructions; and step 3, a general service program is designed and is used for executing the satellite on-service instructions. The application is used for realizing the general service method without special customization development for different loads.

The application provides a satellite-borne multi-viewing-angle polarization spectrum imaging system for aerosol optical parameter measurement, and belongs to the technical field of optical imaging. The system is loaded on a satellite platform and comprises a telescope objective, a multi-slit assembly, a light-splitting prism, a collimating lens group, a plane grating group, an imaging lens group, a depolarization light-splitting prism group, a polaroid group and a detector group. The system is based on static multi-viewing-angle synchronous observation design, and realizes high-precision detection of aerosol optical parameters through multi-viewing-angle, hyperspectral and full-polarization multi-dimensional information fusion.