29 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 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.

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 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 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 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 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 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.

This invention relates to the field of satellite testing and discloses a multi-satellite collaborative on-orbit testing system, method, medium, and product based on a physical satellite. The system includes: a satellite under test for performing preset operations; a ground station for sending macroscopic test commands to a master test satellite; a master test satellite for receiving macroscopic test commands, generating corresponding collaborative control strategies based on the macroscopic test commands, and then distributing the collaborative control strategies to collaborative test satellites; it also observes the satellite under test to obtain observation data, receives test data sent by the collaborative test satellites, and then generates test results based on the observation data and test data; and at least one collaborative test satellite for receiving the collaborative control strategies, forming a preset configuration around the satellite under test according to the collaborative control strategies to test the satellite, and also for collecting test data and sending the test data to the master test satellite. This invention improves the accuracy of on-orbit satellite testing.

A method for rapidly calibrating a micro-nano satellite magnetometer involves rotating the micro-nano satellite around the X, Y, and Z axes of the celestial body. Four static points are collected for each axis, with multiple sets of data collected each time. The average is taken as the magnetometer measurement value for that point. The hard iron magnetic field component error to be eliminated on each axis is calculated using the least squares method, thereby correcting the center of the sphere to the origin. This method utilizes the fact that the direction and magnitude of the Earth's magnetic field are constant. When the sensor rotates arbitrarily in space, the trajectory of the Earth's magnetic field theoretically lies on a sphere. An uncalibrated magnetometer would measure a sphere whose center is not at the origin of the coordinate system. In this case, the magnetometer data would not accurately reflect the direction and magnitude of the magnetic field. This method allows for rapid calibration of the micro-nano satellite magnetometer using the satellite itself after the satellite enters full-satellite testing, without the need for other high-precision magnetometers.

The invention relates to an automatic generation and auxiliary verification system for satellite test design. The automatic generation and auxiliary verification system comprises an information input module, a test sequence generation module, a spectral test sequence model library, a test rule interaction module, an auxiliary verification module and a rule evaluation and iteration module, the test rule interaction module transmits the test rule generated by the test sequence generation module to the auxiliary verification module for verification, and feeds back a verification result to the rule evaluation and iteration module; and the detailed rule evaluation and iteration module calls an optimization strategy according to a verification result to carry out iterative optimization on the test detailed rules, the optimized test detailed rules are transmitted to the auxiliary verification module again through the test detailed rule interaction module to be verified, closed-loop interaction is formed, and finally the test detailed rules meeting the requirements of coverage and time sequence correctness are output to an external system. According to the method, the problems of low test design efficiency, verification lagging and insufficient coverage in the prior art are solved, and rapid generation and dynamic optimization of test rules are realized.

The invention provides a satellite test star catalog plug device and a satellite test device for a high-grade device, and the device comprises a satellite-borne switching module which achieves the network switching of a whole satellite; the star catalogue plug support and the star catalogue plug are connected with a whole-satellite test cable, the test cable is connected with satellite test equipment to realize whole-satellite test, and the star catalogue network port plug is connected with a ground test switch through a network cable; and the ground test switch is connected with the star catalogue network port plug, and the ground test switch is connected with ground test equipment. By adding a satellite AIT test star catalogue network plug and in-satellite network switching module interaction technology, the problems of difficulty in software updating of high-grade devices of a satellite-borne operating system, difficulty in test data interaction and the like are solved, and the effect of interconnection, intercommunication and interoperation of a satellite information system and a ground test information system in an AIT stage is achieved.

The invention provides a satellite test data management system. The satellite test data management system comprises an infrastructure layer, a micro-service layer, an interface protocol layer and a business application layer. The infrastructure layer is used for storing and managing test data and managing internal service software, and the service software comprises a database software product, a message queue product and a service registration center product. And the micro-service layer concentrates the functions of the same type into services, and the services comprise data acquisition and storage services, satellite information management services and data query services. And the interface protocol layer is used for realizing data exchange and service calling between the micro-service layer and the business application layer and serves as a logic layer of various types of interface protocols. And the business application layer calls various services of the micro-service layer through the interface protocol layer, and interacts with a user through a browser. The problems that in existing satellite test data management, the data dispersion management efficiency is low, data sharing and interaction are difficult, and the system expansibility is poor are solved.

The invention relates to an automatic beam hopping wireless test method and system, and the method comprises the steps: S1, determining the angles of all QV antennas on a satellite and the beam angle of a phased-array antenna, making a test sequence through a satellite test system, setting the parameters of a single machine, which needs to be turned on, on the satellite in the sequence, and storing the test sequence; s2, a satellite needing to be tested is bound in a satellite test system of a computer end, and voltage and current of ground power supply equipment are set; s3, after confirming that the satellite state has no problem, calling the test sequence in the step S1, and clicking to start the test; s4, all instruction contents in the sequence are forwarded to on-satellite and ground test equipment through the geologic test box, and after the test sequence is executed, a test report is automatically generated in a satellite test system; and S5, automatically interpreting the test results by the report, dividing the test results into conformity and non-conformity, and when all the test results conform to the requirements, powering off the satellite and turning off all the test equipment.

The application provides a kind of ground equipment of high-speed telemetry remote control communication based on J30J interface satellite-ground measurement and control data transmission integration, comprising: telemetry interface: provide 2-way wired telemetry command signal, and the integrated electronic computer on satellite sends whole satellite telemetry data frame to ground equipment through star table connector two-wire synchronous RS422 interface;Remote control interface: provide 2-way wired telemetry command signal, and the interface adopts synchronous RS422 interface form;Self-closing loop interface: provide 2 self-closing loop cables or plugs, and carry out function check to all RS422 interface input and output.The application supports two kinds of communication modes of general measurement and control and measurement and transmission integration, connects directly through star table plug, switching cable and satellite, can carry out wired control, detection and state display to satellite in satellite ground test process, so as to check satellite function response and performance index, obtain satellite test data, and verify the correctness of satellite work.

This invention relates to a method and system for verifying the electromagnetic compatibility (EMC) of a SAR payload and satellite platform radio frequency (RF) equipment across an entire satellite. The method involves performing power-on self-tests on the satellite platform RF equipment, the integrated payload electronics, the SAR payload, and the system comprised of the satellite platform RF equipment and the integrated payload electronics. The method sets the beam pointing angle of the SAR payload and the beam scanning angle of the satellite platform RF equipment, records the received noise of the SAR payload, and determines the impact of the satellite platform RF equipment on the SAR payload based on the noise test results. By using a SAR antenna subarray instead of the full array, the impact of the satellite platform RF equipment on the SAR payload is quantitatively verified, thus solving the problem of the inability to quantify the impact of the SAR payload during whole-satellite testing. This ensures the verification of the entire satellite's RF compatibility, reduces the risks and costs of satellite development, and meets schedule requirements.

The invention relates to a satellite electric signal intelligent adaptation test system and an applicable test method thereof, and solves the technical problems that a satellite test system in the prior art is insufficient in the aspects of interface management automation, data interaction informatization and system integration intelligentization. The test system comprises a server, a main control computer and a plurality of single machines to be tested, the server is in data connection with the main control computer through the data interaction module; and the plurality of single machines to be tested are connected to the main control computer through a universal cable. According to the satellite electric signal intelligent adaptation test system and the applicable test method thereof, the digital switch matrix, the intelligent transfer box docking system, the digital test system integration technology and other technologies are utilized, the defects in the prior art can be effectively overcome, and the high efficiency of the test process, the informatization of data management and the flexibility of system expansion are achieved.

The invention relates to the technical field of satellite testing, and discloses a system, a method and a device for testing the orientation performance of GNSS orientation equipment, and a medium, and the system is characterized in that a slave antenna is arranged on a guide rail with a master antenna as a circle center, the output end of the master antenna is connected with a first passive power divider, and the slave antenna is connected with a second passive power divider; the output end of the first passive power divider is connected with the first active power divider and the first power attenuator, and the output end of the second passive power divider is connected with the third active power divider and the second power attenuator; the output end of the first power attenuator is connected with a second active power divider, and the output end of the second power attenuator is connected with a fourth active power divider; the first active power divider is connected with a main antenna input end of directional testing equipment, the second active power divider is connected with main antenna input ends of all directional equipment and slave antenna input ends of the directional testing equipment, and the fourth active power divider is connected with slave antenna input ends of all the directional equipment; the controller communicates with the orientation test device and each orientation device, and accurately tests the orientation performance of the plurality of orientation devices in a real environment.

This application relates to the field of satellite testing technology and discloses a GNSS orientation performance testing system, method, apparatus, and medium, including: a slave antenna mounted on a guide rail centered on a main antenna; the output of the main antenna connected to a first passive power divider, and the slave antenna connected to a second passive power divider; the output of the first passive power divider connected to a first active power divider and a first power attenuator; the output of the second passive power divider connected to a third active power divider and a second power attenuator; the output of the first power attenuator connected to the second active power divider, and the output of the second power attenuator connected to a fourth active power divider; the first active power divider connected to the main antenna input of the orientation testing equipment; the second active power divider connected to the main antenna input of each orientation device and the slave antenna input of the orientation testing equipment; and the fourth active power divider connected to the slave antenna input of each orientation device; a controller communicates with the orientation testing equipment and each orientation device to accurately test the orientation performance of multiple orientation devices in a real environment.

The invention belongs to the technical field of satellite testing, and particularly relates to a satellite electrical performance testing method, system and device and a storage medium. The technical problems that in the prior art, manual testing efficiency is low, cooperative work of multiple software systems is difficult, equipment is scattered and inconvenient to manage, and testing functions are limited are solved. Comprising an automatic test software platform used for generating a test task according to user operation; the central control module is used for generating a control instruction according to the test task; the ground equipment integration module is used for enabling the corresponding ground test equipment to enter a working mode according to the control instruction; the data acquisition and processing module is used for acquiring a data stream of the ground test equipment in real time, obtaining original data, preprocessing the original data, obtaining test preprocessing data and acquiring equipment state information of the ground test equipment; and the remote monitoring and diagnosis module is used for carrying out fault detection and diagnosis according to the test preprocessing data and the equipment state information and generating a test result.

The utility model belongs to the technical field of illumination simulation, and relates to a simulation illumination test device for a cubesat solar cell array, which comprises a light source, a bracket and an adjusting mechanism, the light source is arranged on the support through the adjusting mechanism. The light source comprises more than one lamp, the lamp has a travel moving relative to the bracket under the action of the adjusting mechanism, and the travels of different lamps are the same or different, so that different lamps are arranged at different positions of the bracket to generate different illumination conditions, and a simulation illumination test is carried out on the cubesat solar cell array. The device is simple in structure, convenient to operate, high in efficiency, low in cost and capable of perfecting the whole satellite testing process and meeting the production requirements of commercial microsatellites.

The invention relates to a satellite production line test data co-processing method and system based on edge calculation, and belongs to the technical field of satellite manufacturing and testing. According to the method, full-amount local storage and index uploading are carried out on satellite bus data through a station edge node, and classified and simplified uploading is carried out on ground single machine data according to dynamic characteristics of a switching value, a slow variable and a fast variable; during abnormal triggering, a fault diagnosis packet associated with the test steps is automatically generated; and after the test is completed, filing the total data to a central platform. The system adopts a three-level framework of edge node cluster-edge gateway-central platform to realize the functions. Intelligent simplification is realized from a data source, the uploaded data volume is reduced by more than 90%, the pressure of a central platform is greatly relieved, meanwhile, complete fault analysis data is provided through a fault snapshot mechanism, the automation level and efficiency of fault positioning are remarkably improved, and the fault positioning efficiency is improved. The contradiction between mass data processing and accurate fault tracing in batch satellite testing is effectively solved.

The application discloses a satellite test experiment system, relates to the technical field of satellite testing, and is used for satellite quality testing. In order to solve the problem of low efficiency in satellite test experiments, the application provides a satellite test experiment system, which comprises an EMC darkroom and a satellite conveying device. A glass steel walkway with a first distance higher than the ground is arranged in the EMC darkroom, so that the satellite conveying device can convey the satellite to a designated position for test experiments, and the inner walls on each side of the EMC darkroom are provided with wave-absorbing materials which do not need to be disassembled. Therefore, the wave-absorbing materials do not need to be arranged again every time the satellite is tested, and the satellite conveying device can replace the traditional manual satellite conveying. The satellite is conveyed to the designated position for experiments through the arranged glass steel walkway, so that the labor is saved, the test efficiency is improved, and the effect is more remarkable in large-scale satellite testing.