58 results about "Satellite testing" patented technology

The invention provides a satellite fault diagnosis method and system based on multi-source information fusion. The satellite fault diagnosis method comprises the steps that firstly, a multi-source monitoring data set of platform system state data, load system working data and measurement and control link interaction data is generated in the satellite testing process based on an emergency fast response satellite testing system; then performing multi-source information association extraction processing on the multi-source monitoring data set to generate an association feature set reflecting a coupling relationship between systems; then inputting the associated feature set into a pre-trained satellite fault diagnosis model for fault mode analysis processing to obtain a fault feature description containing a fault trigger node and an influence link; a preset fault knowledge base is matched based on the fault feature description, and a fault diagnosis result containing a fault type identifier and a propagation path is generated; and finally, generating a satellite fault handling strategy according to a fault diagnosis result. The method can comprehensively and accurately diagnose the satellite fault and improve the satellite reliability.

The invention relates to an in-orbit calibration method for an uplink phased-array antenna of a low-orbit communication satellite, and belongs to the technical field of satellite testing. According to the method, pointing measurement and calibration of an uplink phased-array antenna of a low-orbit communication satellite are taken as input, and measurement and calibration of beam pointing of the uplink phased-array antenna are realized through test and data processing of G / T values of multiple beams of the uplink phased-array antenna. The method has the functions of calibration signal generation, beam G / T test, beam stereo directional diagram reconstruction, pointing deviation measurement and beam pointing adjustment. Simulation experiments show that the calibration method designed by the invention can effectively reduce the beam pointing deviation of the uplink phased-array antenna of the low-orbit communication satellite.

The invention relates to the technical field of satellite product testing, in particular to a space attitude adjusting device, system and method for satellite testing. The device comprises a rotary connecting seat, wherein the rotary connecting seat comprises an upper connecting plate, a lower connecting plate and a connecting column; the top surface of the upper connecting plate is rotatably connected with a rotating mechanism, and the upper surface of the lower connecting plate is fixedly connected with a hanging mechanism; the system further comprises a tilt angle sensor and a servo driving system. The method comprises the following steps: respectively connecting the free ends of the slings with different end parts of a test satellite; adjusting the length of each sling, and adjusting the pitch angle and the roll angle of the tested satellite; the rotation driving device is started to drive the rotation connecting seat to rotate integrally, and the azimuth angle of the test satellite is adjusted to the test azimuth angle; after the satellite to be tested is static, space attitude adjustment is completed. The problems that in the prior art, the attitude adjustment range is small, the testing efficiency is low, and the testing result error is large are solved.

The embodiment of the invention provides a satellite test control method and device, control equipment and a test box. The method comprises the following steps: setting a satellite in a test box in a normal pressure state, and determining a target temperature based on a temperature change rate of a satellite component in the test box in a process of operating the test box in advance; and then, in the process of controlling the test box to operate at the target temperature, obtaining operation data of the satellite in the test box, and obtaining a test result of the satellite. A normal-pressure thermal cycle test is provided, more equipment is not needed to maintain a vacuum environment for satellite test, and the cost of satellite test is reduced; under the normal pressure condition, the satellite can be tested conveniently and quickly, the satellite testing period is shortened, and the satellite testing time cost is reduced.

The invention provides a satellite test system, method and device, communication equipment and a storage medium, and relates to the technical field of satellite communication. The method comprises the following steps: based on a conduction integrated signal, obtaining a pseudo-range observed quantity between a target satellite and a conduction integrated signal receiver; on the basis of the pseudo-range observed quantity and the GNSS signal, obtaining on-satellite launching time delay of the target satellite; and testing the target satellite based on the on-satellite launching time delay. Therefore, the GNSS signal receiver and the conduction integrated signal receiver are arranged side by side according to a zero base line and are homologous in clock, so that time synchronization can be realized between the two receivers, the ground time-frequency reference can be unified, the influence of ground clock drift in the test process is eliminated, and the accuracy of satellite test is improved. Besides, on-satellite launching time delay can be considered, the target satellite is tested, the influence of time-frequency deviation between a communication system and a navigation system on satellite testing is greatly eliminated, and the accuracy of satellite testing is further improved.

The invention belongs to the technical field of satellites. The invention provides a simulated in-orbit test method and system for low-orbit satellite time-frequency equipment. According to the embodiment of the invention, a reference atomic clock provides a reference basis for a GNSS navigation signal simulator, a time interval counter and a phase noise analyzer; the GNSS navigation signal simulator provides a Beidou / GNSS analog signal and an SSR (Simple Sequence Repeat) correction number for the satellite time frequency equipment; the satellite time frequency device completes real-time precise orbit determination and clock correction calculation of the low-orbit satellite by using the received Beidou / GNSS analog signal and the SSR correction number, and controls and regulates a built-in local atomic clock according to a calculated clock correction sequence; and respectively carrying out time precision and frequency stability test and analysis on the second 1PPS signal and the second 10MHz signal through a time interval counter and a phase noise analyzer. The low-orbit satellite in-orbit test can be simulated in the initial stage, and real-time calculation of in-orbit satellite test data can be realized.

This application relates to a satellite attitude conversion device, belonging to the field of satellite testing devices, and includes a base, a plurality of push rods installed on the base, and a mounting plate installed on the plurality of push rods. The satellite is placed on the mounting plate. The satellite includes a flange, and a plurality of mating holes are formed in the flange. The diameter of the mating holes gradually decreases from bottom to top. An installation groove is formed in the mounting plate, and a support spring is fixedly connected to the bottom wall of the installation groove. A bottom column is slidably inserted into the installation groove, and the support spring is fixedly connected to the bottom column. The diameter of the bottom column is larger than the maximum diameter of the mating holes. A support rod is fixedly connected to the bottom column, and an installation block is fixedly connected to the upper end of the support rod. A plurality of grooves are formed in the side wall of the installation block, and a fixing spring is fixedly connected to the bottom wall of the groove. A fixing block is fixedly connected to the fixing spring, and the fixing block is slidably inserted into the groove. This application has the effect of improving the efficiency of satellite attitude conversion testing.

The present disclosure proposes a satellite test system, method, apparatus, communication equipment and storage medium, which relate to the field of satellite communication technology. The method includes: obtaining a pseudo-range observation between a target satellite and a communication and navigation integrated signal receiver based on a communication and navigation integrated signal; obtaining the on-board transmission delay of the target satellite based on the pseudo-range observation and the GNSS signal; and testing the target satellite based on the on-board transmission delay. As a result, the GNSS signal receiver and the communication and navigation integrated signal receiver are juxtaposed according to a zero baseline and have the same clock source, so that time synchronization can be achieved between the two receivers, the ground time and frequency reference can be unified, and the influence of the ground clock drift during the test process can be eliminated, thereby improving the accuracy of the satellite test. In addition, the target satellite can be tested taking into account the on-board transmission delay, which greatly eliminates the influence of the time and frequency deviation between the communication system and the navigation system on the satellite test, further improving the accuracy of the satellite test.

This utility model relates to the field of robotic arm technology and discloses a multi-degree-of-freedom robotic arm for satellite testing. It includes a base, a support frame on top of the base, a third motor for rotating the support frame fixed on one side of the base, and a first motor, a second motor, and a fifth motor fixed on one side of the support frame. A ninth connecting arm is fixed to the output shaft of the first motor, a first connecting arm is fixed to the output shaft of the second motor, and a fifth connecting arm is fixed to the output shaft of the fifth motor. A moving component for multi-station satellite testing is located at the bottom of the base. Through the combination of multiple motors and connecting arms, the mounting plate drives the satellite to move in six degrees of freedom in three-dimensional space, enabling the robotic arm to perform precise spatial positioning and attitude adjustment in complex environments. The fifth connecting arm simultaneously hinges to the fourth and sixth connecting arms, allowing the robotic arm to achieve complex composite movements and increasing its convenience.

The invention provides a priori knowledge-based satellite telemetering false alarm identification and processing method and system, and the method comprises the steps: obtaining the working condition, the false alarm influence range and the influence time of the satellite telemetering false alarm based on the priori knowledge accumulated in the early-stage design and acceptance of a satellite and in the development and test process in combination with the analysis and extraction of satellite telemetering data, and carrying out the recognition and processing of the satellite telemetering false alarm. And on the basis, the satellite telemetering false alarm is identified and processed. According to the method, the interference of telemetering false alarm on data interpretation is solved, the data interpretation efficiency and interpretation quality in the satellite test and on-orbit monitoring process are effectively improved, unnecessary treatment measures caused by false alarm are reduced, satellite abnormity can be found timely and accurately, faults can be removed timely and accurately, and the reliability of satellite test and on-orbit monitoring is improved. And guarantee is provided for better organizing satellite management activities and controlling satellites to complete tasks.

The invention provides a satellite test interpretation system based on scene recognition and temperature grading. The satellite test interpretation system comprises a data subscription service subsystem and a processing module. The data subscription service subsystem is used for receiving and forwarding satellite telemetry data; the processing module runs fine interpretation software and sequentially executes the following steps: detecting a whole satellite and single machine power-up state and a telemetering interruption state; an actual test scene is intelligently identified in combination with the thermistor mounting state; calling a preset three-level temperature range of storage, work and acceptance according to the scene to carry out grading interpretation; and finally, performing multi-level early warning such as color distinguishing, character prompting and voice alarming according to the interpretation result. Therefore, automatic and precise satellite temperature monitoring and fault early warning are realized.

The invention discloses a satellite feed source and wave-absorbing box beside-satellite testing device and an assembling method, and relates to the technical field of satellite electrical performance testing, the device is provided with a satellite feed source and a wave-absorbing box, and the device comprises a vehicle body, and the vehicle body is provided with a bottom plate and a supporting frame; the baffle assembly is distributed on the bottom plate; the wave-absorbing box is located on the bottom plate, and the periphery of the wave-absorbing box is attached to the baffle assembly so that position fixing can be achieved. The feed source tool is fixedly connected to the outer side of a satellite feed source; a feed source tool and a satellite feed source are hoisted to the position above the wave absorbing box, and the feed source tool is installed on the supporting frame; the guide assembly is provided with a first mounting plate part and a positioning pin; the positioning pin is vertically connected with the first mounting plate part; one part of the mounting plate is mounted on the supporting frame; the two ends of the feed source tool penetrate through the positioning pins and are in lap joint with the first mounting plate part. A gasket is arranged between the feed source tool and the first part of the mounting plate so as to adjust the height of the feed source tool and the satellite feed source; according to the device and the assembly method, the assembly reliability of the satellite feed source and the wave-absorbing box is improved, and the use safety is improved.

The embodiment of the utility model provides a satellite test device, which comprises a multi-core plug male head, a multi-core plug female head, a test board and a sensor assembly, and is characterized in that the multi-core plug male head is electrically connected with a BNC wire male head, the BNC wire male head is electrically connected with a control acquisition instrument, the control acquisition instrument is electrically connected with the test board, the test board is used for placing a satellite to be tested, the multi-core plug female head is electrically connected with a BNC wire female head, and the sensor assembly is electrically connected with the BNC wire male head. The BNC wire female head is electrically connected with the sensor assembly, and the sensor assembly is arranged on a satellite to be tested or a test board. The multi-core plug male head and the multi-core plug female head are arranged, the multi-core plug male head is electrically connected with the control acquisition instrument through the BNC wire male head, the multi-core plug female head is electrically connected with the sensor assembly through the BNC wire female head, and the sensor assembly can be electrically connected to the control acquisition instrument through the multi-core plug male head and the multi-core plug female head. The multi-core plug male head and the multi-core plug female head are separated, so that disconnection of the sensor assembly and the control acquisition instrument can be realized.

The invention discloses a parallel automatic intelligent integrated test system suitable for batch production of satellites. Belongs to the technical field of satellite testing. The technical problems of poor test case universality and difficulty in adaptive adjustment in the conventional satellite automatic test technology are solved. The system comprises a test architecture module, a test module and a data storage module, in the test architecture module, test cases are subjected to level-to-level management through a multi-level nested automatic sequence; the test module performs multi-satellite parallel test by adopting a test case through a multi-port configuration method based on a lookup table; and the data storage module performs mixed data sampling storage on the test result. The system can be applied to the technical field of satellite batch production testing.

A modular satellite testing platform system having an upper and a lower member along with a plurality of support members, intermediate members, and lower bar members that are interconnected to the upper member and the lower member. The system further includes a plurality of shelf members that are attached to the support members. The satellite also includes a plurality of bottom cover members that are attached to the lower member by a plurality of hinge members that allow the cover members to selectively rotated about an axis to be rotatably translated between an opened position and a closed position. The system yet further includes a thermal control system to allow maintaining the thermals of the satellite as desired.

The invention provides a method and a system for quickly interpreting, confirming and filing test data of batch-produced satellites. The method comprises a parameter setting step: setting parameters of an interpretation template, an interpretation model and a data state frequent monitoring model based on a test design sequence; a data interpretation step: monitoring and interpreting real-time data by using an interpretation template based on a test design sequence and recording the data; a test sequence execution real-time confirmation step: performing real-time confirmation on the completed test sequence according to the recorded data to generate a test confirmation table; and a test sequence data packet filing step: after completing the test confirmation table, naming the software and automatically packaging and associating the test data to form a complete data packet. According to the method, real-time rapid interpretation of batch-produced satellite test data is realized by adopting an interpretation template and a model based on a test design sequence, in order to avoid missed judgment of the test data, a satellite telemetry data state frequent monitoring interpretation method is introduced, and state jump monitoring of all telemetry data and stationarity monitoring of stateless data are realized.

The embodiment of the invention discloses an automatic test method for a satellite comprehensive test scheme, a medium and electronic equipment, relates to the technical field of satellite test, and aims to solve the problem of low satellite test efficiency in a satellite development process in the prior art. According to the method, the satellite test is automatically carried out by circularly reading the test cases in the test scheme table, firstly, whether the test cases exist in the test scheme table or not is judged, the test cases are called from the test scheme table one by one for execution under the condition that the test cases exist in the test scheme table, and when one test case is executed, the satellite test is automatically carried out. According to the method, whether the test cases exist in the test scheme table or not is judged, after all the test cases are executed, the test report is automatically generated finally according to the test results of the test cases, rapid execution of a large number of satellite test cases can be achieved, and the test efficiency is improved.

The invention provides a space delivery and recovery microgravity test system, and relates to the technical field of satellite testing, the space delivery and recovery microgravity test system comprises an air bearing platform, a marble platform and a lifting platform; an angle adjusting assembly is arranged above the air floating table, and the angle adjusting assembly is used for installing the child satellite main body and adjusting the deflection angle of the child satellite main body; an air floating assembly is arranged below the air floating platform and is used for enabling the air floating platform to float above the platform surface of the marble platform; the upper portion of the lifting platform is used for installing a delivery separation device, a mother satellite interface structure is arranged at the end, facing the child satellite body, of the delivery separation device, and a child satellite interface structure matched with the mother satellite interface structure is arranged at the end, facing the delivery separation device, of the child satellite body. Compared with the prior art, the space delivery and recovery microgravity test system effectively solves the problem that a child-mother satellite delivery and recovery device is difficult to simulate child satellite angle deviation and verify docking adaptability in ground verification.

The invention provides a portable docking test system and method based on a satellite equivalent comprehensive power system, and the system comprises a test terminal which is used for completing the receiving, processing and display of virtual comprehensive power collection data, transmitting a comprehensive power instruction and a docking instruction to virtual comprehensive power equipment, and completing the remote control of the virtual comprehensive power equipment. And implementing an actual docking test item. And the virtual comprehensive power equipment is used for simulating a satellite comprehensive power subsystem, and is directly and physically connected with the docking single machine to complete interface matching, signal conditioning and remote control telemetering communication with the docking single machine. The virtual comprehensive power equipment is used for replacing a real satellite subsystem, so that a satellite docking tester can complete docking under the condition that no real comprehensive power system exists, the problem of a large amount of preparatory work caused by repeated disassembly and assembly of the comprehensive power system after satellite installation is avoided, and the problem of resource conflict of the comprehensive power system for docking test and whole satellite test is solved.

The invention provides a non-contact satellite safety monitoring alarm system and device. The non-contact satellite safety monitoring alarm system comprises a dynamic and static thermal imager combination, a data processing and control module and a display alarm terminal. The static thermal imager combination is composed of a wide thermal imager and a two-dimensional directional variable-focus high-resolution thermal imager, and the wide thermal imager and a two-dimensional directional variable-focus high-resolution thermal imager base are integrated into a whole and used for achieving fixed-angle satellite panoramic thermal imaging and high-resolution thermal imaging at a satellite test station. The data processing and control module is composed of an image processing sub-module, a comprehensive control sub-module and a data storage and transmission sub-module, and is used for identifying the name and the temperature value of a satellite image hot spot region in real time, and comparing and analyzing the name and the temperature value with a satellite temperature reference value to form alarm information and the like; the alarm terminal is a mobile phone terminal or a computer terminal with a loudspeaker sound output function, and is used for carrying out data interaction with the data processing and control module and displaying temperature alarm information and the like to a terminal user.

The application relates to a kind of on-orbit calibration methods of low-orbit communication satellite downlink phased array antenna based on CDM, belonging to the field of satellite testing technology.The method takes the pointing measurement and calibration of low-orbit communication satellite downlink phased array antenna as input, and realizes the measurement and calibration of the beam pointing of the downlink phased array antenna through the test and data processing of multiple beams EIRP of the downlink phased array antenna.The method has the functions of calibration signal generation, beam EIRP test, beam three-dimensional directional diagram reconstruction, pointing deviation measurement and beam pointing adjustment.Simulation experiments show that the calibration method designed by the application can effectively reduce the beam pointing deviation of low-orbit communication satellite downlink phased array antenna.

The invention discloses a spacecraft GNSS simulation system based on a cloud architecture and a simulation test method. Comprising a multichannel spacecraft GNSS simulation source host which generates navigation satellite simulation signals and navigation simulation data; a main switch and a plurality of satellite test subsystems, wherein the main switch and the switches in the satellite test subsystems form a bidirectional communication network; a plurality of satellite test subsystems, wherein the satellite test subsystems determine a navigation satellite simulation signal receiving mode based on the working mode of the spacecraft GNSS simulation system; the power of the received navigation satellite analog signal is adjusted through an attenuator to obtain an input signal of the tested satellite navigation terminal, and the tested satellite generates related telemetering data based on the input signal of the tested satellite navigation terminal; and the switch sends the telemetry data and the navigation simulation data to the test master control processing equipment in the satellite test subsystem for closed-loop comparison and interpretation. According to the invention, the independent or joint analog signal function of the multi-user channel is realized.

The invention discloses a satellite-ground time synchronization system and method for a satellite comprehensive test. The system comprises a navigation signal simulation source, time frequency equipment, ground special test equipment, a satellite-borne navigation receiver and a satellite-borne computer. According to the method, the uniform satellite-ground time reference is established, accurate and comparable timestamps with consistent sources are printed on all satellite telemetry data and ground test data, and the problem of information islands caused by disorder of the timestamps is solved. A ground navigation signal simulation source is used as a unique time source of satellite and ground special test equipment, a satellite-borne navigation receiver and ground time frequency equipment are used for resolving navigation radio frequency or low frequency signals of the navigation signal simulation source in parallel, and an inherent error accumulation chain in a cascade transmission synchronization mode is cut off. According to the ground time synchronization scheme of NMEA serial port second giving and second pulse frequency calibration, high-precision time synchronization can be realized only by receiving and analyzing standardized NMEA data and second pulse signals by ground time frequency equipment, and the hardware cost and the development difficulty of a software algorithm are reduced.

This invention relates to the field of satellite simulation and testing technology, specifically to a multi-satellite parallel testing system for attitude and orbit control systems. The system includes a signal transfer unit subsystem, an I / O interface subsystem, a multi-core real-time simulator subsystem, a real-time simulation main control subsystem, a database server subsystem, and a power supply module subsystem. The multi-core real-time simulator connects to multiple I / O interface chassis via PCIe expansion components, with each chassis corresponding to the test resources of one satellite. The real-time simulation main control subsystem deploys the dynamic simulation models of multiple satellites onto different processor cores of the simulator, achieving multi-core distributed parallel simulation. Each satellite's onboard computer establishes a real-time data interaction link with its corresponding dynamic simulation model, forming a multi-satellite parallel real-time closed-loop testing state. This system solves the problem that traditional single-satellite testing systems cannot meet the requirements of mass production and parallel testing, offering advantages such as high testing efficiency, low hardware cost, and strong scalability.

The invention discloses an aviation monitoring load single machine and a whole satellite sensitivity test method. According to the method, a system is built in a microwave darkroom for stand-alone testing, and after link calibration, ADS-B signals with loads in different directions and in different formats are tested; in the whole satellite test, a satellite platform is deployed in a large darkroom, double transmitting antennas are arranged, a test signal is transmitted after link parameters are calibrated, and unpacked data are monitored. The test result shows that the load demodulation success rate is higher than 90%, and the sensitivity in the full state meets the index requirements. According to the method, coherent and accurate testing of the whole stage of load development is achieved, and a reliable method is provided for performance verification of a low-orbit satellite aviation monitoring system.

The utility model relates to satellite test equipment, comprising a test switching unit which comprises a plugging area and a test area, and the test area is provided with a plurality of test connection parts; the plugging area is provided with a plurality of electric connectors, the plurality of electric connectors comprise different electric connector types, and the plurality of electric connectors share a plurality of test connecting parts; the satellite equipment to be tested is connected with the electric connector through the adapter cable; and the test device is connected with the test connection part and is used for outputting test data of the to-be-tested satellite equipment. The satellite test equipment is convenient for workers to operate, and the test efficiency, the test safety and the test effect of the satellite equipment can be improved.

The application provides a satellite electric test resource scheduling method and system based on a directed acyclic graph, which comprises the following steps: a digital model of satellite test and assembly resources is established; for different types of satellites, unit cutting is performed on test items and assembly items, and the cutting is divided into independent units, which can complete a specific work; a directed acyclic graph is established by using the test items and the assembly items according to the sequence of the test items and the assembly items of the required developed satellite; a multi-level feedback queue scheduling algorithm is used to schedule and plan the resources of the satellite and the test process; and the resources of the satellite are dynamically adjusted according to the real-time process of the electric test, so as to ensure that the satellite electric test flow works at the maximum beat. The application can solve the problem that the satellite assembly and test segmentation cannot be considered as a whole in the past, solve the resource allocation and scheduling problem of different types of satellites, and has a certain significance for the resource scheduling management of satellite ground development.

The invention belongs to the technical field of test launch control, and relates to a mooring unmanned aerial vehicle RF optical fiber forwarding system without relying on a launching tower. The six-rotor unmanned aerial vehicle mooring system comprises a front-end RF optical fiber conversion unit, an airborne power supply conversion module, a six-rotor unmanned aerial vehicle platform, a mooring power supply signal transmission cable, a mooring control box, a rear-end RF optical fiber conversion unit and a power supply oil engine. According to the system, a front-end RF optical fiber conversion unit is mounted on a six-rotor unmanned aerial vehicle to approach a rocket launching platform, measurement and control and data transmission signals of a spacecraft are transmitted and received, and bidirectional signal forwarding between onboard load signals and a ground mooring control box is completed through a mooring power supply signal transmission cable; and signal transmission with the rear-end RF optical fiber conversion unit is completed through the signal transmission optical fiber, so that bidirectional communication of link signals between the front-end launching station and the rear-end satellite test equipment is ensured, and stable transmission of test signals before rocket launching without relying on a launching tower is realized.

The invention provides an equipment cabinet grounding device and method for a satellite standardized test system. The equipment cabinet grounding device comprises an equipment cabinet main grounding wire, an equipment grounding wire, an inter-equipment cabinet grounding wire, a grounding pile grounding wire and a grounding pile, the cabinet main grounding wire is used for grounding and gathering all test equipment in a single cabinet in a satellite standardized test system in the cabinet and mounting and fixing a gathered grounding network in the cabinet; the equipment grounding wire is used for connecting each test equipment grounding pole in the cabinet with a main grounding wire of the cabinet; the inter-cabinet ground wire is used for connecting cabinets of the satellite standardization test system; the grounding pile grounding wire is used for connection between a satellite standardization test system cabinet and a test system grounding pile. The grounding pile is used for connection between the satellite standardization test system and the satellite plant ground. According to the invention, reliable grounding between all satellite test equipment and the satellite plant ground is realized through a cascade connection mode, and the grounding device is high in expandability.

The application provides a satellite fault diagnosis method and system based on multi-source information fusion. First, a multi-source monitoring data set of platform system state data, load system working data and test control link interaction data generated in the process of testing the satellite based on an emergency quick response satellite test system is obtained. Then, multi-source information correlation extraction processing is performed on the multi-source monitoring data set to generate a correlation feature set reflecting the coupling relationship between systems. Then, the correlation feature set is input into a pre-trained satellite fault diagnosis model for fault mode analysis processing to obtain fault feature descriptions containing fault trigger nodes and influence links. Then, based on the fault feature descriptions, a pre-set fault knowledge base is matched to generate a fault diagnosis result containing fault type identification and propagation path. Finally, a satellite fault handling strategy is generated according to the fault diagnosis result. The method can comprehensively and accurately diagnose satellite faults and improve satellite reliability.