Digital whole-satellite-level spaceborne computer software testing system

Abstract

The invention provides a digital whole-satellite-level spaceborne computer software testing system which comprises a virtual testing platform and a ground testing subsystem, the virtual testing platform is used for simulating the running state of a real satellite and space environment dynamic data, and the ground testing subsystem and the virtual testing platform conduct information interaction. And the test module is used for sending a test instruction to the virtual test platform, receiving a telemetry data packet which is fed back by the virtual test platform and contains a simulation result, executing an automatic test based on the telemetry data packet and carrying out test recording and test interpretation. Therefore, a virtuality and reality combined testing environment is established, limitation of a hardware single machine is avoided, software testing efficiency is improved, testing time is shortened, testing quality is improved, human input is reduced, testing risks are avoided, and the problem that software testing is limited by equipment, sites, environments, time and the like in the prior art is solved.

Description

Technical Field

[0001] The invention relates to the field of integrated testing of a spacecraft star system, and in particular to a digital onboard computer software testing system for a star system. Background Art

[0002] With the rapid development of aerospace technology in recent years, the logical functions of onboard computer software have become increasingly complex, which has also put forward higher requirements for software function verification.

[0003] In the past, the verification of onboard computer software was done by directly using real stand-alone or equipment product identification parts, combined with ground test equipment, to form a test verification system. In the absence of a stand-alone or equipment product identification part, the traditional method will not be able to build the test system, and some test items will not be able to be executed. It is necessary to wait until all equipment from all parties is complete before testing can begin. In addition, even if a stand-alone device has been installed on the satellite, if the entire star software test poses a security risk to the stand-alone hardware device, such a test project is often difficult to carry out.

[0004] In the actual scientific research and production process, we often have to face the situation of frequent updates of software status and frequent loading and unloading of equipment. If we always have to wait for all parties to be fully ready before starting testing, it will seriously slow down the progress of satellite development and there will also be a risk of insufficient software verification. Summary of the invention

[0005] The purpose of the present invention is to provide a digital whole-star onboard computer software testing system, which can improve test efficiency, avoid the single-machine safety risks involved in traditional test systems, and reduce test costs.

[0006] In order to achieve the above object, the present invention provides a digital star-level onboard computer software test system, including a virtual test platform and a ground test subsystem, wherein:

[0007] The virtual test platform includes a digital simulation CMU simulator for actually running the onboard computer software, a sensor module for simulating the working conditions of the analog sensor, an actuator module for simulating the output control torque of the onboard instrument, a dynamics simulation module for solving the operating state of the satellite according to the control torque and providing signal excitation to the sensor module according to the solved state, a telemetry and remote control module for simulating the satellite-to-ground link when the satellite is in orbit, and a satellite service simulator for simulating power management and bus interface management;

[0008] The ground test subsystem exchanges information with the virtual test platform to send test instructions to the virtual test platform, receive telemetry data packets containing simulation results fed back by the virtual test platform, and perform automated testing based on the telemetry data packets and perform test records and test interpretation.

[0009] Furthermore, the ground test subsystem includes:

[0010] A remote control front-end module, which is in communication with the telemetry and remote control module of the virtual test platform, so as to send the test instruction to the virtual test platform;

[0011] A telemetry front-end module, which is in communication with the telemetry remote control module of the virtual test platform, and is used to receive a telemetry data packet containing simulation results fed back by the virtual test platform;

[0012] A main control module, used to unpack the telemetry data packets and distribute them to corresponding modules, and to receive and transmit instruction information;

[0013] A data subscription service module is used to receive the telemetry data distributed after being unpacked by the main control module, and broadcast it to the lower terminals;

[0014] A data storage service module, used to store the telemetry data distributed by the main control module after unpacking into a database, and provide a data interface for data query;

[0015] A measurement and control interface module, which exchanges information with the dynamics simulation module, is used to receive parameters transmitted by the dynamics simulation module and forward them to the main control module, and transmit the main control instructions from the main control module to the dynamics simulation module;

[0016] The automated testing module is used to receive the test instructions triggered by the user and to perform test interpretation on the telemetry data.

[0017] Furthermore, the ground test subsystem also includes a display module, and the display module is used to display the telemetry data in a preset form.

[0018] Furthermore, the modules of the virtual test platform exchange information with each other in the form of a dynamic link library.

[0019] Furthermore, the satellite service simulator is specifically used for:

[0020] Simulate the software initialization parameters when the satellite is powered on;

[0021] Simulating a satellite bus format for information exchange; wherein the satellite bus format includes a telemetry format and a remote control format;

[0022] Receive and respond to satellite center machine instructions and satellite service setting instructions, simulate the execution changes of corresponding instructions, and feed back the corresponding simulation results in the telemetry data packet;

[0023] The telemetry data packet is transmitted to the CMU simulator at a regular interval.

[0024] Furthermore, the remote control front-end module and the telemetry front-end module use a preset verification platform communication protocol to exchange information with the virtual test platform; wherein, in the compilation of the verification platform communication protocol, direct instruction code words, indirect instruction code words, command issuance process and telemetry processing process are simplified, and new ground setting parameter fault value instructions and virtual platform operation multiple setting instructions are added.

[0025] Furthermore, the virtual test platform is equipped with a simulation acceleration program for realizing the simulation acceleration function.

[0026] The digital whole-star onboard computer software testing system described in the present invention uses a virtual testing platform instead of a real satellite platform. Software testing is no longer dependent on a single hardware machine, so testing is no longer constrained by hardware, site, environment, etc. The simulation acceleration function can greatly save the physical time of software testing and improve testing efficiency. Testers are allowed to control the entire system at will without worrying about safety hazards, effectively avoiding the single-machine safety risks involved in traditional testing systems. The method of use is no different from that of traditional ground testing systems, which reduces the learning cost of testers and the resistance to the promotion of testing systems. A new feasible solution is provided for the scientific research and production of whole-star software, supporting long-life, high-reliability software verification testing, and supporting the digital twin research of electrical satellites and scientific research satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 A structural block diagram of the digital star-level onboard computer software testing system provided by an embodiment of the present invention;

[0028] Figure 2 A schematic block diagram of the specific structure of the digital star-level onboard computer software testing system provided by one embodiment of the present invention;

[0029] Figure 3 A schematic diagram of the system structure connection of the digital star-level onboard computer software testing system provided in one embodiment of the present invention;

[0030] Figure 4 A schematic diagram of the system structure of using the digital star-level onboard computer software test system provided by an embodiment of the present invention to perform closed-loop functional testing of the attitude and orbit control software of the entire star;

[0031] Figure 5 The present invention is a schematic diagram of the system structure for executing the function test of the whole-star satellite service software by using the digital whole-star satellite-borne computer software test system provided by one embodiment of the present invention. DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0033] It should be noted that references to "one embodiment", "embodiment", "example embodiment", etc. in this specification refer to the embodiment described, which may include specific features, structures or characteristics, but not every embodiment must include these specific features, structures or characteristics. In addition, such expressions do not refer to the same embodiment. Furthermore, when describing specific features, structures or characteristics in conjunction with an embodiment, whether or not there is an explicit description, it has been shown that it is within the knowledge of those skilled in the art to combine such features, structures or characteristics into other embodiments.

[0034] In addition, certain words are used in the specification and subsequent claims to refer to specific components or parts. Those with ordinary knowledge in the relevant field should understand that manufacturers can use different nouns or terms to refer to the same component or part. This specification and subsequent claims do not use differences in names as a way to distinguish components or parts, but use differences in the functions of components or parts as the criteria for distinction. "Including" and "including" mentioned throughout the specification and subsequent claims are open-ended terms and should be interpreted as "including but not limited to". In addition, the word "connected" here includes any direct and indirect electrical connection means. Indirect electrical connection means include connection through other devices.

[0035] In view of the fact that traditional spacecraft onboard computer software verification uses a real single machine, which results in the test being restricted by equipment, site, environment, time and other issues, the present invention provides a digital whole-star onboard computer software testing system, which solves the technical problems faced by the prior art by creatively building a virtual test platform and a test environment for a ground test subsystem.

[0036] Figure 1 The digital whole-star onboard computer software test system 100 provided by an embodiment of the present invention is shown, which includes a virtual test platform 10 and a ground test subsystem 20. Specifically, the virtual test platform 10 is used to simulate the actual satellite operation status and the use of the control subsystem dynamics, and then the ground test subsystem 20 is used to prepare for the test, implement the test, record the test, and interpret the test. The specific system structure of the virtual test platform 10 and the ground test subsystem 20 is as follows: Figure 2 As shown, where:

[0037] The virtual test platform 10 includes a digital simulation CMU (Communication Management Unit) simulator 101 for actually running the onboard computer software, a sensor module 102 for simulating the working conditions of the sensor, an actuator module 103 for simulating the output control torque of the onboard instrument, a dynamic simulation module 104 for solving the operating state of the satellite according to the control torque and providing signal excitation to the sensor module according to the solved state, a telemetry and remote control module 105 for simulating the satellite-to-ground link when the satellite is in orbit, and a satellite service simulator 106 for simulating power supply management and bus interface management. In specific implementation, the simulation functions to be realized by each functional module of the virtual test platform 10 are carried out by a set of The virtual test platform 10 is implemented by the application software on the computer, that is, the virtual test platform 10 can be a set of application software running on the computer; after receiving power-on, the corresponding module of each simulation function module of the virtual test platform 10 receives and responds to the satellite center computer command, simulates the state change that the command should produce, and feeds back the simulation structure in the telemetry data packet; for example, as the core of the entire virtual test platform, the CMU simulator 101 can digitally simulate the satellite-borne computer software originally running on the real CMU, and the simulation content includes but is not limited to attitude and orbit control software, satellite service software, energy software, thermal control software and FDIR (Fault Detection, Isolation and Recovery) software, etc.; the CMU simulator 101 can simulate the specific functions of the real CMU in the test environment, but the CMU simulator 101 belongs to the module in the virtual system where the program code executes the corresponding function, and is not a real specific physical module; similarly, each functional module on the virtual test platform 10 is a module where the program code executes the corresponding function, and is not a real specific physical module.

[0038] Each functional module on the virtual test platform 10 receives and responds to satellite central machine instructions according to the functions of the object to be simulated (i.e., the real single machine). During the test, it simulates the state changes that the instructions should produce and feeds back the simulation results in the telemetry data packet.

[0039] Specifically, the sensor module 102 of this embodiment can simulate the working conditions of real star sensors, sun sensors, ground sensors, gyroscopes and other sensors to analyze the body or space information; after analysis, the single machine transmits information such as attitude angle and angular velocity to the CMU simulator 101.

[0040] The onboard equipment of this embodiment includes but is not limited to reaction wheels, thrusters and other power equipment, that is, the actuator module 103 is specifically used to simulate the process of reaction wheels and thrusters outputting control torque; when the actuator module 103 receives the control request of the CMU simulator 101, it performs the corresponding simulation operation according to the control request shown, thereby outputting the control torque.

[0041] The dynamics simulation module 104 is the core of the closed-loop test of the control subsystem. On the one hand, the module can solve the operating state of the satellite according to the control torque output by the actuator module 103, and on the other hand, it can also provide signal excitation for the sensor module 102 according to the solved state.

[0042] The telemetry and remote control module 105 (TC / TM module) can specifically simulate the working status of the command uplink channel and the telemetry downlink channel.

[0043] The satellite service simulator 106 of this embodiment has a more detailed simulation of the 1553B lower computer PCU, BIMU and other mounted devices. It can not only simulate the working conditions of each simulation module when it is powered off, but also simulate the process of a single machine communicating with the CMU software in the 1553B protocol data format. The satellite service simulator 106 is also designed with an interface module for command reception, through which the ground test subsystem 20 can send commands to set the status of the lower computer.

[0044] The modules of the virtual test platform 10 of this embodiment use dynamic link libraries for information exchange. In specific implementation, the entire virtual test platform 10 does not have a software interaction interface, and all command controls and data packets can communicate with the external ground test subsystem via Ethernet.

[0045] Preferably, the virtual test platform 10 is equipped with a simulation acceleration program for realizing the simulation acceleration function. That is, the virtual test platform 10 has a simulation acceleration function, and the relevant program software can speed up the running process of the software on the simulation satellite by a certain multiple (such as 4 to 8 times), which can not only save a large amount of process data for analysis, but also shorten the time required for project testing. Based on the simulation acceleration function, long life cycle assessment testing is carried out, which is conducive to discovering software random problems and stack overflow problems.

[0046] The ground test subsystem 20 exchanges information with the virtual test platform 10 to send test instructions to the virtual test platform 10, receive telemetry data packets containing simulation results fed back by the virtual test platform 10, and perform automated testing based on the telemetry data packets and perform test records and test interpretations.

[0047] The ground test subsystem 20 may also execute corresponding functions by a set of program codes loaded on a computer.

[0048] Further, such as Figure 2 As shown, the ground test subsystem 20 includes a telemetry front-end module 201 (TCF), a telemetry front-end module 202 (TMF), a main control module 203 (MTP), a data subscription service module 204 (RTS), a data storage service module 205, a measurement and control interface module 206 and an automated test module 207, wherein:

[0049] The remote control front-end module 201 is communicatively connected with the telemetry and remote control module 105 of the virtual test platform 10 to send the test instruction to the virtual test platform 10; in specific implementation, when a valid request is received from the lower terminal, the remote control front-end module 201 will send the instruction codeword in the protocol format, and if the instruction is sent successfully, a success message will be returned.

[0050] The telemetry front-end module 202 is communicatively connected to the telemetry remote control module 105 of the virtual test platform 10 to receive the telemetry data packet containing the simulation results fed back by the virtual test platform 10; the telemetry data packet received from the virtual test platform 10 will be forwarded to the main control module 203 according to the ground protocol.

[0051] The main control module 203 is used to unpack the telemetry data packets and distribute them to the corresponding modules, as well as to receive and transmit command information; the main control module 203, as the core of the ground test subsystem 20, has two main functions. One is to unpack the telemetry data packets received from the telemetry front-end module 202 and distribute them to the corresponding modules; the other is to receive command information from other modules and transmit it to the corresponding modules.

[0052] The data subscription service module 204 is used to receive the telemetry data distributed after unpacking by the main control module 203, and broadcast it to the lower terminal; the lower terminal here is a user terminal connected to the data subscription service module 204, specifically refers to a user terminal that subscribes to related services through the data subscription service module. The data subscription service module 204 of this embodiment can support personalized customization services, and users can choose to subscribe to only some of the required telemetry parameters.

[0053] The data storage service module 205 is used to store the telemetry data distributed after unpacking by the main control module 203 into the database, and provide a data interface for data query; that is, the data storage service module 205 provides database storage and access services, which can not only store the telemetry data unpacked by the main control module 203 into the database, but also provide a data interface for users to query historical data.

[0054] The measurement and control interface module 206 exchanges information with the dynamics simulation module 104, and is used to receive the parameters transmitted from the dynamics simulation module 104 and forward them to the main control module 203, as well as transmit the main control instructions from the main control module 203 to the dynamics simulation module 104; specifically, the measurement and control interface module 206 serves as an interface module for enabling the dynamics simulation module 104 to exchange information with the main control module 203. It can receive the parameters transmitted from the dynamics simulation module 104 and forward them to the MTP according to the ground master control protocol, and can also transmit the received MTP instructions to the dynamics simulation module 104 according to the dynamics protocol.

[0055] The automated test module 207 is used to receive the test instruction triggered by the user and to perform test interpretation on the telemetry data. Specifically, the automated test module 207 can enable the tester to conveniently execute the test sequence while also having the data interpretation function.

[0056] Preferably, the ground test subsystem 20 further includes a display module 208, which is used to display the telemetry data in a preset form. The preset form can be a curve chart form, a bar chart form, etc. This embodiment specifically uses a curve chart form, that is, the display module 208 is used to display the telemetry data in the form of a curve to assist the tester in interpretation. The display module 208 can also have a curve data recording function.

[0057] The specific system structure of the digital star-level onboard computer software testing system 100 of this embodiment is as follows: Figure 3 As shown, the satellite service simulator 106 includes a PCU module, a BIMU module and an interface module. The satellite service simulator 106 exchanges information with the CMU simulator 101, and the CMU simulator 101 exchanges information with the telemetry and remote control module 105. The CMU simulator 101, the actuator module 103, the dynamics simulation module 104 and the sensor module 102 are connected in sequence to form a closed loop; the main control module 203 on the ground test subsystem 20 exchanges information with other modules in the ground test subsystem respectively, and realizes information exchange of instructions and telemetry data with the virtual test platform through the test front-end module 201 and the telemetry front-end module 202, and realizes information exchange of dynamic instructions and dynamic parameters with the dynamics simulation module 104 through the test interface module 206; the main control module 203 also unpacks the telemetry data packet and distributes it to the data subscription service module 204 (RTS), the data storage service module 205 and the automatic test module 207, etc. During the test, the tester operates the ground test subsystem 20 to send test instructions, the virtual test platform 10 receives the instructions and feeds back data to the ground test system in combination with the simulation operation status, and the ground test subsystem 29 unpacks the data for the tester to interpret.

[0058] In order to keep the system test environment consistent with the actual hardware test to the greatest extent possible, the ground test subsystem 20 of this embodiment only needs to make partial adaptive modifications based on the traditional test software.

[0059] The digital star-level onboard computer software testing system 100 provided in this embodiment not only opens up the interface between virtual and real testing, but also has proper compatibility. Testers can adapt to the system without having to change their previous operating habits too much, and can be fully recognized during promotion and use.

[0060] In order to make the virtual test platform 10 more perfect in simulating the digital information flow of the whole satellite and better integrate with the ground test subsystem 20, this embodiment specifically designs and implements the telemetry and remote control interface of the satellite service simulator 106 of the virtual test platform 10 and the ground test subsystem 20. In this regard, the specific functions of the satellite service simulator 106 configured in this embodiment are as follows:

[0061] 1. Simulate the software initialization parameters when the satellite is powered on; after the satellite is powered on, each satellite service unit includes: power supply and distribution, battery pack interface management unit, payload integrated business unit, platform integrated business unit, etc.; in this regard, the satellite service simulator 106 simulates the software initialization parameters when the satellite is powered on according to actual conditions, that is, initializes the satellite status.

[0062] 2. Simulate the satellite bus format to exchange information; wherein, the satellite bus format includes telemetry format and remote control format; specifically, after the satellite service simulator 106 is powered on, the satellite bus format is simulated to receive the instructions sent by the satellite center computer, and the instruction information is transmitted to each stand-alone module.

[0063] 3. Receive and respond to satellite center machine instructions and satellite service setting instructions, simulate the execution changes of corresponding instructions, and feed back the corresponding simulation results in the telemetry data packet; that is, after the satellite service simulator 106 is powered on, each stand-alone module receives and responds to satellite center machine instructions, simulates the changes that the instructions should produce, and feeds back the simulation results in the telemetry data packet; and each stand-alone module receives and responds to instructions set by the ground test subsystem 20, sets instructions for simulating various fault conditions, simulates the changes that the instructions should produce, and feeds back the simulation results in the telemetry data packet.

[0064] 4. Regularly transmit the telemetry data packets to the CMU simulator 101. Specifically, after the satellite service simulator 106 is powered on, each stand-alone simulates the telemetry downlink state, packages the stand-alone data into a PK packet, and transmits the PK packet to the satellite center.

[0065] The uplink and downlink interfaces between the virtual test platform 10 and the ground test subsystem 20 of this embodiment are different from those of a real physical stand-alone machine. Specifically, the remote control front-end module 201 and the telemetry front-end module 202 use a preset verification platform communication protocol to exchange information with the virtual test platform 10; wherein, in the compilation of the verification platform communication protocol, the direct instruction codewords, indirect instruction codewords, command issuance process and telemetry processing process are simplified, and the ground setting parameter fault value instruction and the virtual platform operation multiple setting instruction are added.

[0066] For the telemetry and remote control front-end interfaces, this embodiment makes the remote control front-end module 201 and the telemetry front-end module 202 interact with Cortex, and the soft platform version interacts with the simulation software system. The protocol is converted from the Cortex protocol to the "Verification Platform Communication Protocol".

[0067] In the uplink and downlink data processing, the direct instruction codewords are simplified when editing the "Verification Platform Communication Protocol", such as sending instruction No. 1 corresponds to the AA codeword; the indirect instruction codewords are simplified, and the digital test system sends only data blocks, and the data blocks are consistent with the content of the whole satellite test; the command issuance process is simplified, and the self-loop, large loop, command encryption and other command sending processes are cancelled; the telemetry processing process is simplified, and the whole format data that complies with the "Verification Platform Communication Protocol" is converted to the protocol and sent to the main control system; new ground parameter setting fault instructions are added, and new virtual platform operation multiple setting instructions are added.

[0068] Two application examples of using the digital whole-star onboard computer software testing system 100 to perform testing will be introduced below.

[0069] like Figure 4 As shown in the figure, the first application example is the closed-loop function test of the whole star attitude and orbit control software, and the test process is as follows:

[0070] After the virtual test platform is started, the ground test personnel operate the automated test software to send test instructions. The instructions are parsed by the main control module MTP and sent to the telemetry front-end module TCF. TCF converts the instructions into corresponding instruction codes according to the instruction protocol and sends them to the virtual test platform. The virtual test platform processes the instruction codes by the telemetry remote control module TC / TM module and forwards them to the CMU simulator. The CMU simulator responds to the instructions according to the actual running status of the software. According to the satellite communication protocol, the CMU software will regularly package and transmit telemetry parameters. The telemetry parameters are processed by the TC / TM module and transmitted to the ground test subsystem according to the 1553B communication protocol. After receiving the data, the telemetry front-end module TMF in the ground test subsystem sends the data to the main control module MTP according to the ground master control protocol. MTP unpacks the data according to the real satellite communication protocol and distributes it to the lower terminal. The lower terminal data storage service module stores the data in the database. The lower terminal data subscription service module RTS broadcasts and distributes telemetry data according to the client's needs. The display module on the client (such as curve software) draws a curve chart based on the telemetry data. The client automated test module interprets the telemetry data, and the tester performs the next step according to the interpretation result.

[0071] The dynamics simulation module on the virtual test platform is used to realize the closed loop of satellite attitude and orbit control. After the module passes the excitation data to the sensor module, the corresponding module of the sensor solves the satellite's current attitude, angular velocity and other data according to the excitation information and passes it to the CMU simulator. The CMU simulator makes attitude / orbit adjustment decisions based on the attitude, angular velocity and other information combined with software logic and controls the execution of the actuator module. After receiving the execution command, the actuator module simulates the jet and wheel speed changes to generate control torque. This information will be collected by the dynamics simulation module. The dynamics simulation module updates the satellite dynamics model according to the collected information and sends an excitation signal to the sensor module according to the solution result. During the entire closed-loop control process, ground test personnel can send dynamics instructions through the ground test subsystem to adjust the dynamics operation status, and can also receive dynamics telemetry in real time to understand the current dynamics operation status.

[0072] The entire test process described above can be implemented through automated test software, and the test operation is no different from the real test. The closed-loop functional test of the entire star-level attitude and orbit control software tests the operating logic of the onboard attitude and orbit control software. Since it does not involve hardware, the test results are no different from the real results. In addition, making good use of the acceleration function of the virtual test platform can shorten the physical time of the test process.

[0073] like Figure 5 As shown, the second application example is the function test of the whole star service software, and its test process is as follows:

[0074] After the virtual test platform is started, the test data flow is basically the same as the first application example. The difference is that when sending the satellite service setting command, the command does not pass through the telemetry and remote control module TM / TC, but is sent directly to the satellite service simulator. During the test, the ground test personnel adjust the operating status of the single machine mounted in the satellite service simulator by sending commands, so that the CMU simulator makes corresponding decisions, thereby verifying whether the logical function of the satellite service software is correct.

[0075] The whole-star satellite service software functional test assesses the operating logic of the on-board satellite service software. Since it does not involve hardware, the test results are no different from the actual results. In addition, the test can also use the acceleration function of the virtual test platform to improve test efficiency.

[0076] Other application examples of the digital whole-star onboard computer software testing system 100 for executing tests described in this embodiment may specifically refer to the execution logic in the traditional testing system, which will not be described in detail here.

[0077] It should be noted that the present application can be implemented in software and / or a combination of software and hardware, for example, can be implemented using an application specific integrated circuit (ASIC), a general purpose computer or any other similar hardware device. In one embodiment, the software program of the present application can be executed by a processor to implement the above steps or functions. Similarly, the software program of the present application (including relevant data structures) can be stored in a computer-readable recording medium, for example, a RAM memory, a magnetic or optical drive or a floppy disk and similar devices. In addition, some steps or functions of the present application can be implemented using hardware, for example, as a circuit that cooperates with a processor to perform each step or function.

[0078] The method according to the present invention can be implemented on a computer as a computer-implemented method, or implemented in dedicated hardware, or implemented in a combination of the two. The executable code or part thereof for the method according to the present invention can be stored on a computer program product. The example of a computer program product includes a memory device, an optical storage device, an integrated circuit, a server, online software, etc. Preferably, the computer program product includes a non-temporary program code component stored on a computer-readable medium so as to perform the method according to the present invention when the program product is executed on a computer.

[0079] To sum up, the digital whole-star onboard computer software testing system described in the present invention uses a virtual testing platform instead of a real satellite platform. Software testing is no longer dependent on a single hardware machine, so testing is no longer constrained by hardware, site, environment, etc. The simulation acceleration function can greatly save the physical time of software testing and improve testing efficiency. Testers are allowed to control the entire system at will without worrying about safety hazards, effectively avoiding the single-machine safety risks involved in traditional testing systems. The method of use is no different from that of traditional ground testing systems, which reduces the learning cost of testers and reduces the resistance to the promotion of the test system. It provides a new feasible solution for the scientific research and production of whole-star software, supports long-life, high-reliability software verification testing, and supports the digital twin research of electrical satellites and scientific research satellites.

[0080] Of course, the present invention may have many other embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art may make various corresponding changes and modifications based on the present invention, but these corresponding changes and modifications should all fall within the scope of protection of the claims attached to the present invention.

Claims

1. A digital star-level onboard computer software testing system, characterized in that: It includes a virtual test platform and a ground test subsystem, including: The virtual test platform includes a digital simulation CMU simulator for actually running the onboard computer software, a sensor module for simulating the working conditions of the analog sensor, an actuator module for simulating the output control torque of the onboard instrument, a dynamics simulation module for solving the operating state of the satellite according to the control torque and providing signal excitation to the sensor module according to the solved state, a telemetry and remote control module for simulating the satellite-to-ground link when the satellite is in orbit, and a satellite service simulator for simulating power management and bus interface management; The ground test subsystem exchanges information with the virtual test platform to send test instructions to the virtual test platform, receive telemetry data packets containing simulation results fed back by the virtual test platform, and perform automated testing based on the telemetry data packets and perform test records and test interpretation.

2. The digital star-level onboard computer software testing system according to claim 1 is characterized in that: The ground test subsystem includes: A remote control front-end module, which is in communication with the telemetry and remote control module of the virtual test platform, so as to send the test instruction to the virtual test platform; A telemetry front-end module, which is in communication with the telemetry remote control module of the virtual test platform, and is used to receive a telemetry data packet containing simulation results fed back by the virtual test platform; A main control module, used to unpack the telemetry data packets and distribute them to corresponding modules, and to receive and transmit instruction information; A data subscription service module is used to receive the telemetry data distributed after being unpacked by the main control module, and broadcast it to the lower terminals; A data storage service module, used to store the telemetry data distributed by the main control module after unpacking into a database, and provide a data interface for data query; A measurement and control interface module, which exchanges information with the dynamics simulation module, is used to receive parameters transmitted by the dynamics simulation module and forward them to the main control module, and transmit the main control instructions from the main control module to the dynamics simulation module; The automated testing module is used to receive the test instructions triggered by the user and to perform test interpretation on the telemetry data.

3. The digital star-level onboard computer software testing system according to claim 2 is characterized in that: The ground test subsystem also includes a display module, which is used to display the telemetry data in a preset form.

4. The digital star-level onboard computer software testing system according to claim 1 is characterized in that: The modules of the virtual test platform exchange information with each other in the form of dynamic link libraries.

5. The digital star-level onboard computer software testing system according to claim 1 is characterized in that: The star service simulator is specifically used for: Simulate the software initialization parameters when the satellite is powered on; Simulating a satellite bus format for information exchange; wherein the satellite bus format includes a telemetry format and a remote control format; Receive and respond to satellite center machine instructions and satellite service setting instructions, simulate the execution changes of corresponding instructions, and feed back the corresponding simulation results in the telemetry data packet; The telemetry data packet is transmitted to the CMU simulator at a regular interval.

6. The digital star-level onboard computer software testing system according to claim 2 is characterized in that: The remote control front-end module and the telemetry front-end module use a preset verification platform communication protocol to exchange information with the virtual test platform; wherein, in the compilation of the verification platform communication protocol, direct instruction code words, indirect instruction code words, command issuance process and telemetry processing process are simplified, and new ground setting parameter fault value instructions and virtual platform operation multiple setting instructions are added.

7. The digital star-level onboard computer software testing system according to claim 1 is characterized in that: The virtual test platform is equipped with a simulation acceleration program for realizing the simulation acceleration function.

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