44 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.

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 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 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.

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 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 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 relates to the technical field of satellite test and measurement, in particular to a photogrammetry plumbing device adjusting device, which comprises a fixing part, an adjusting part and a control part, and is characterized in that the fixing part comprises a bracket assembly and a rotating part rotationally connected with the bracket assembly; the position adjusting part comprises a supporting frame connected with the rotating piece and a driving adjusting assembly arranged at the bottom of one end of the supporting frame, and the driving adjusting assembly is connected with a gear of the rotating piece; the posture adjusting part is arranged at the top of the end, not connected with the fixing part, of the supporting frame. The fixing part is used for integrally fixing the adjusting device of the photogrammetric plummet, and the position adjusting part is used for adjusting the position of the photogrammetric plummet within a certain circumferential range; the posture adjusting part is used for adjusting the orientation and pitch posture of the photogrammetry plummet, and a focusing mechanism in the posture adjusting part is used for adjusting the focal length of the photogrammetry plummet. Automatic position adjustment and focusing of the photogrammetry plummet are achieved, manual adjustment is not needed, and the problem that the photogrammetry plummet cannot be arranged and adjusted during large-size photogrammetry is solved.

The present invention discloses an automatic testing method for satellite platform electronics and related components, which relates to the field of satellite testing. When receiving a user instruction, a test instruction is generated according to the user instruction. When it is determined that the test instruction is a correct instruction, a test task chain corresponding to the test instruction is generated, and the test task chain is sent to the platform electronics so that the platform electronics can execute all corresponding test tasks according to the test task chain. Finally, the test result data of the test tasks of the platform electronics is obtained for display. Since the test task chain is generated according to the test instruction and different platform electronics have different test instructions, different test task chains can be generated according to the types of platform electronics. After the test task chain is sent to the platform electronics, the platform electronics will automatically execute the test tasks, eliminating the need for manual testing, improving the testing efficiency, reducing the workload and testing threshold, avoiding the situation of accidental touch, and can also be applied to testing in special environments.

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.