Large-scale satellite single-machine test platform and test method

Abstract

The application provides a kind of large-scale satellite single machine test platform and test method, test platform includes: digital model unit, the digital model in which is formed by reference digital satellite decoupling the function module corresponding to the tested single machine, digital model is configured to simulate the signal flow between each functional module and each functional module of satellite, sends the state instruction of control tested single machine, receives the state information of tested single machine;Single machine access unit is connected with digital model unit, and is provided with the physical access interface of tested single machine, and is configured to carry out bidirectional signal interaction between digital model unit and tested single machine;Measurement and control unit is connected with digital model unit, and is configured to respond to the type of accessed tested single machine to call corresponding test case sequence, to digital model unit sends test case sequence.The application does not depend on traditional satellite physical hardware platform, can deploy multiple test systems in parallel, and can carry out batch multi-single machine test acceptance.

Description

Technical Field

[0001] This invention relates primarily to the field of satellite testing technology, and more particularly to a large-scale satellite single-unit testing platform and testing method. Background Technology

[0002] Currently, in the testing of single-satellite scientific research verification satellites and small-batch production satellites, after the individual satellite units are delivered by the manufacturer, the overall satellite system needs to conduct acceptance testing on the entire satellite, including receiving and storing the individual units. Existing acceptance testing mainly involves assembling a minimum satellite system to perform interface and functional acceptance testing with the delivered individual units. This involves building a complete satellite test hardware platform, placing all the physical units on a test bench, and connecting them via actual onboard cables. The unit to be tested is then disconnected and connected for testing.

[0003] Traditional testing methods have the following shortcomings during functional testing: 1. High resource requirements. Functional verification testing involves information flow, requiring the participation of other physical units that interact with the satellite. Basic systems such as power supply, satellite maintenance, and telemetry and control all need to provide support, and corresponding onboard cables are also required. Because all types of units on the entire satellite need to be connected for verification testing, the constructed test site requires the participation of all satellite units and all their cables, resulting in a large number of participating units and high resource consumption. 2. Complex test scenario construction. All types of unit testing and verification are connected, resulting in numerous onboard cables and operations in the entire acceptance test scenario. This leads to a large number of constituent elements in the overall test scenario and many variables that need to be controlled, making the construction of the entire verification test scenario complex. 3. Low verification testing efficiency. The large number of units involved, and the requirement for all types of units to be connected, necessitates the participation of the entire satellite in the constructed test site, resulting in a large number of participating units and complex construction. Due to the complexity of the verification test scenario and the large number of single-machine requirements, only one test scenario can be built at most. Based on the control variable method, single-machine acceptance testing in this scenario can only be performed on a small number of single machines at a time, which is relatively inefficient.

[0004] Therefore, overcoming the shortcomings of existing satellite single-unit acceptance testing, such as high demand for testing resources, complex test scenario construction, and low verification testing efficiency, has become an urgent technical problem to be solved in this field. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a large-scale satellite single-unit test platform and test method, which reduces the test resource requirements, simplifies the test scenario construction, and supports the parallel deployment of multiple test systems to improve the efficiency of large-scale satellite single-unit acceptance testing.

[0006] To address the aforementioned technical problems, in a first aspect, the present invention provides a large-scale satellite single-unit testing platform, comprising: a digital model unit, including at least one digital model, wherein the digital model is formed by decoupling the functional modules corresponding to the single unit under test from a reference digital satellite, and wherein the single unit under test is the hardware single unit under test; the digital model is configured to simulate the various functional modules of the satellite and the signal flow between the functional modules, send status commands to control the single unit under test, receive status information of the single unit under test, and simulate satellite status changes based on the received satellite control commands; a single-unit access unit, communicatively connected to the digital model unit, and provided with a physical access interface for the single unit under test, configured to perform bidirectional signal interaction between the digital model unit and the single unit under test; and a telemetry and control unit, communicatively connected to the digital model unit, configured to respond to the type of the accessed single unit under test by calling the corresponding test case sequence, sending the test case sequence to the digital model unit, and receiving satellite status change signals.

[0007] Optionally, the digital model formed by decoupling the functional modules corresponding to the tested unit from the reference digital satellite includes: decoupling the functional modules corresponding to the tested unit from the reference digital satellite, constructing an information flow middleware, and establishing timing synchronization between the tested unit and the decoupled digital satellite; wherein the information flow middleware is configured to receive control commands issued by the satellite management software and status information returned by the tested unit.

[0008] Optionally, the functional modules corresponding to the tested unit include one of the following: reaction wheel functional module, gyroscope functional module, propulsion functional module, power control functional module, SADA rotation functional module, and load functional module.

[0009] Optionally, the digital model in the digital model unit is also configured to simulate the self-management function of the satellite's own state changes.

[0010] Optionally, the stand-alone access unit is provided with at least one of the following interfaces: CAN interface, RS422 interface, RS232 interface, or TCP / IP interface.

[0011] Optionally, the digital model in the digital model unit includes a virtual digital chip, on which the satellite's operational software is loaded.

[0012] Optionally, the digital model unit includes multiple different types of digital models. The different types of digital models are adapted to the testing and acceptance of different single machines under test, and the multiple different digital models form a digital model library.

[0013] Secondly, the present invention provides a large-scale satellite single-unit testing method, applied to the large-scale satellite single-unit testing platform as described in the first aspect, comprising: connecting the single unit to be tested to the single-unit access unit; the digital model unit loading and running a digital model corresponding to the single unit to be tested according to the type of the connected single unit; the telemetry and control unit calling a corresponding test case sequence in response to the type of the single unit to be tested, the test case sequence including satellite control commands; the telemetry and control unit sending the test case sequence to the digital model unit and receiving satellite status signal changes transmitted by the digital model unit.

[0014] Optionally, the satellite control commands include predefined satellite control commands.

[0015] Optionally, before or during the test, the telemetry and control unit obtains the satellite control commands through human-computer interaction.

[0016] Compared with existing technologies, this invention has the following advantages: This testing platform replaces individual physical units of a real satellite with digital models, resulting in lower resource requirements and simpler test scenario setup. In terms of deployment and use, because it does not rely on traditional satellite physical hardware platforms, multiple testing systems can be deployed in parallel, enabling batch testing of various individual units and significantly improving the efficiency of acceptance testing for large-scale satellite unit acceptance testing. Attached Figure Description

[0017] The accompanying drawings are included to provide a further understanding of this application; they are incorporated into and constitute a part of this application. The drawings illustrate embodiments of this application and, together with this specification, serve to explain the principles of this application. In the drawings: Figure 1 This is a schematic diagram of the architecture of a large-scale satellite single-unit test platform according to an embodiment of the present invention; Figure 2 This is a flowchart illustrating a method for large-scale satellite single-unit testing according to an embodiment of the present invention. Detailed Implementation

[0018] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely some examples or embodiments of this application. For those skilled in the art, these drawings can be applied to other similar scenarios without creative effort. Unless obvious from the context or otherwise specified, the same reference numerals in the drawings represent the same structures or operations.

[0019] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0020] It should be understood that when a component is referred to as "on another component," "connected to another component," "coupled to another component," or "in contact with another component," it can be directly on, connected to, coupled to, or in contact with that other component, or there may be an intervening component. In contrast, when a component is referred to as "directly on another component," "directly connected to," "directly coupled to," or "directly in contact with" another component, there is no intervening component. Similarly, when a first component is referred to as "electrically contacting" or "electrically coupled to" a second component, there is an electrical path between the first and second components that allows current to flow. This electrical path may include capacitors, coupled inductors, and / or other components that allow current to flow, even if there is no direct contact between the conductive components.

[0021] Flowcharts are used in this application to illustrate the operations performed according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, various steps can be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more steps may be removed from them.

[0022] refer to Figure 1 As shown, the large-scale satellite single-unit test platform in this embodiment includes three main parts: a digital model unit, a single-unit access unit, and a telemetry and control unit.

[0023] The digital model unit includes at least one digital model, which is formed by modifying a benchmark digital satellite. Specifically, functional modules corresponding to a specific type of unit are removed from the benchmark digital satellite to create a digital model adapted for acceptance testing of that type of unit. For example, removing the reaction wheel functional module from the benchmark digital satellite creates a test digital model corresponding to a reaction wheel unit. Similarly, removing the gyroscope functional module creates a test digital model corresponding to a gyroscope unit, and so on. The interface nodes corresponding to the removed functional modules are retained in the digital model so that the physical unit under test can interact with the digital model through these interface nodes after connection.

[0024] It should be noted that the reference digital satellite is a complete digital satellite system that simulates all the individual functional modules of a real satellite and the signal flow between them in software by running a virtual digital chip on a computer and loading the satellite service code and the lower-level machine code of each unit. All individual functional modules in the reference digital satellite operate in the digital domain without being connected to external physical hardware. The reference digital satellite is the foundation for constructing the digital model in this embodiment. Removing a functional module corresponding to a certain type of unit from the reference digital satellite forms the digital model corresponding to that type of unit.

[0025] In some embodiments, the digital model formed by decoupling the functional modules corresponding to the unit under test from the reference digital satellite includes: decoupling the functional modules corresponding to the unit under test from the reference digital satellite, constructing an information flow middleware, and establishing timing synchronization between the unit under test and the decoupled digital satellite. The information flow middleware is configured to receive control commands issued by the satellite administration software and status information returned by the unit under test.

[0026] In this embodiment, the satellite can be designed to switch between fully digital and semi-digital (digital model) modes. In fully digital mode, all functional modules of the digital satellite operate in a simulated manner within the digital domain, without interacting with external hardware. In semi-digital (semi-physical) mode, the internal functional modules corresponding to the tested unit can be shut down, and its data interaction can be switched from the internal software channel to the hardware channel, transmitting signals with the external tested unit via the unit's access unit. The digital satellite retains its fully virtual operation capabilities while also being able to switch to semi-physical testing; the mode conversion can be completed simply by switching at the software level, significantly improving testing efficiency and flexibility.

[0027] In the original architecture, control commands were sent directly from the space station software to the virtual functional module, while status information was returned directly from the virtual functional module to the space station software. After introducing the information flow middleware, both control commands issued by the space station software and status information returned by the tested unit first pass through the information flow middleware. The middleware then determines, based on the current mode, whether to forward them to the virtual functional module or send them to the real hardware via the hardware driver channel. The information flow middleware, on top of the software, adds real hardware driver capabilities, enabling interaction with the real hardware in terms of control commands and status information.

[0028] Timing synchronization refers to the synchronization of the digital and physical domain timing of a satellite. Digital satellites use a built-up second timing mechanism, which inherently deviates from the physical clock of external hardware in a semi-physical mode. This embodiment uses a high-precision clock signal as a unified timing source, switching the digital satellite's timing calculation method from internal built-up second counting to an external clock source. The PPS (pixels per second) of the high-precision clock signal is used as the hardware timing source. At the arrival of each second pulse, the digital and physical domain clocks are aligned and calibrated to eliminate accumulated deviations, ensuring a precise correspondence between the control command transmission time and the response time of the tested unit, thus achieving virtual real-time synchronization.

[0029] The digital model is configured to simulate the various functional modules of the satellite and the signal flow between them. Based on software communication, the digital model simulates the internal information and data flow interactions of a real satellite, as well as the satellite's own state logic changes. After the tested unit is connected, the digital model (software) and the tested unit (hardware) together form a complete satellite system. The digital model is responsible for simulating other satellite functional modules and signal flows besides the tested unit, while the tested unit, as the physical entity, is responsible for generating realistic physical responses. During operation, the digital model sends status commands to the tested unit. The control commands generated by the satellite management software are transmitted to the lower-level control module via internal protocols. The lower-level control module converts these commands into direct control codes or unit-level protocol control codes before outputting them. Simultaneously, the digital model receives status information from the tested unit. Status data sent by the tested unit in the form of unit code packets is transmitted to the digital model via the unit access unit. The digital model then assembles these unit code packets into corresponding unit telemetry packets. In addition, the digital model simulates the changes in the overall satellite state based on the received satellite control commands. That is, after receiving the satellite control commands sent by the telemetry and control unit, the digital satellite simulates the changes in the overall satellite operating state under the action of the control commands, so as to reflect the satellite's own state changes and simulate the actual satellite more realistically.

[0030] The standalone access unit (hardware) communicates with the digital model unit and is equipped with a physical access interface for the unit under test. For example, the standalone access unit may be implemented as a data acquisition control board, deployed on a workstation running the digital model. The workstation may have multiple data acquisition control boards to provide various communication interfaces. The standalone access unit is configured to perform bidirectional signal interaction between the digital model unit and the unit under test. It converts control commands generated by the digital model into physical signals recognizable by the unit under test and sends them to the unit under test. It also converts the physical output signals of the unit under test into model information recognizable by the digital model and injects it into the corresponding interface node of the digital model. Through this bidirectional signal conversion, a complete closed-loop test path is formed between the digital model and the unit under test.

[0031] The telemetry, tracking, and command (TT&C) unit communicates with the digital model unit (DMU) and is configured to invoke the corresponding test case sequence in response to the type of the connected device under test. The test case sequence typically includes control commands sent to the DMU, ​​telemetry signals, expected thresholds for the telemetry signals, and the logic linking the commands and telemetry. The TT&C unit is generally a ground-based test system that sends satellite control commands to the DMU and receives satellite status change signals transmitted by the DMU. The TT&C unit performs automated testing based on uplink and downlink data, driving the DMU and the device under test to produce corresponding actions by sending satellite control commands and identifying the device under test's response by receiving satellite status change signals.

[0032] Based on the aforementioned large-scale satellite unit test platform, the telemetry, tracking, and command (TT&C) unit generates satellite control commands and sends them to the digital model unit. The digital model in the digital model unit simulates the overall satellite state changes under these commands and also transmits the control commands to the lower-level control module based on an internal protocol. The lower-level control module converts the control commands into direct control codes or unit-level protocol control codes, which are then sent to the unit under test via the unit access unit. The unit under test responds physically to these control codes, collecting its own state data through sensors and sending it to the digital model via the unit access unit in the form of unit code packets. The digital model assembles these unit code packets into corresponding unit telemetry packets and sends them to the TT&C unit. The TT&C unit identifies the unit under test's response to the satellite control commands by observing changes in the unit telemetry packets, thereby verifying the unit's performance under the overall satellite environment.

[0033] This embodiment transforms the benchmark digital satellite into a digital model lacking a single functional module. This digital model replaces the individual physical units of the real satellite for information flow simulation, while retaining the physical unit under test as the physical access point. This significantly reduces the need for physical resources such as satellite physical units. Furthermore, because it is not constrained by traditional satellite physical hardware platforms, multiple test systems can be deployed in parallel, enabling batch parallel testing of various units, greatly improving the efficiency of large-scale satellite unit acceptance testing.

[0034] In some embodiments, the functional modules corresponding to the tested unit removed from the digital model include one of the following: reaction wheel functional module, gyroscope functional module, propulsion functional module, power control functional module, SADA rotation functional module, and load functional module. Different types of tested units correspond to different functional modules, and their removal results in different test digital models to adapt to the acceptance testing requirements of various types of satellite units, thus broadening the applicability of the test platform.

[0035] In some embodiments, the digital model in the digital model unit is also configured to simulate the self-management function of the satellite's own state changes. The digital model not only simulates the signal flow interaction between various functional modules of the satellite, but also simulates the satellite's own state logic changes. After the digital model is loaded with real satellite management software based on a virtual digital chip, the autonomous operation management logic, on-board time management, fault detection and handling strategies, and other functions of the satellite management software are reflected in the digital model. When the digital model receives satellite control commands, the satellite management software simulates the real satellite's work management and control logic, parses and executes the control commands, and drives the overall satellite state changes. This ensures that the control commands, telemetry data processing logic, and fault diagnosis behavior generated by the digital model during the test are consistent with those of the real satellite, and the test results can directly reflect the working status of the tested unit in the real satellite system.

[0036] In some embodiments, the standalone access unit is equipped with at least one of the following interfaces: CAN interface, RS422 interface, RS232 interface, or TCP / IP interface. After pre-configuring these interfaces, the standalone device under test can directly connect to the standalone access unit via the corresponding communication bus. For most standalone devices using universal bus interfaces, no additional hardware adaptation is required to complete the connection. For some standalone devices using non-standard interfaces, a corresponding dedicated board can be purchased according to the interface specifications of the standalone device and inserted into the workstation expansion slot to achieve interface docking.

[0037] The communication connection between the measurement and control unit (TMU) and the digital model unit (DMU) is not limited to a specific physical connection. In one implementation, the TMU and DMU are deployed on the same workstation or local area network (LAN) and communicate via a wired network (such as Ethernet). In another implementation, the TMU is deployed on a remote terminal and communicates with the DMU via a wireless network to achieve remote test control. These communication methods make the deployment of the test platform more flexible and adaptable to different test sites and scenarios.

[0038] In some embodiments, the digital model unit includes a virtual digital chip, on which the satellite's operational software is loaded. By running the virtual digital chip on a computer—that is, simulating the processor and peripheral circuits of the satellite's onboard computer in software—and then loading and running a stable, validated version of the operational software corresponding to the satellite model being tested, the satellite's operational control and management functions are realized. The virtual digital chip provides the virtual hardware environment required for the operational software to run, including a processor, program memory, data memory, and necessary external interfaces. After the operational software runs on the virtual digital chip, its generated control commands, telemetry data processing logic, and fault diagnosis behavior are consistent with the operational behavior of the operational software on the real satellite. Therefore, the digital model does not write satellite simulation programs from scratch, but can directly load and run the operational software code used by the real satellite, enabling the digital model to have control and management behavior consistent with the real satellite, ensuring the consistency of the excitation and feedback signals provided by the test platform to the tested satellite.

[0039] In some embodiments, the digital model unit includes multiple different types of digital models. These different types of digital models are adapted to the testing and acceptance of different individual units under test, forming a digital model library. The reference digital satellite is sequentially modified using software into digital models that each lack one functional module. For example, removing the reaction wheel module from the reference digital satellite transforms it into a test digital model for a reaction wheel unit. Similarly, test digital models for gyroscope units, propulsion units, etc., can be created using the same method. These test digital models constitute a digital model library. During unit acceptance testing, the corresponding digital model is retrieved from the digital model library based on the type of unit under test and loaded and run. There is no need to rebuild the test platform for different units under test, enabling a single test platform to cover the acceptance testing requirements of multiple types of satellite units. When testing different units, the corresponding model is called and connected to the physical object, significantly shortening test preparation time and improving the testing efficiency of the test platform.

[0040] refer to Figure 2 As shown, another embodiment of the present invention provides a method for large-scale satellite single-unit testing, which can be applied to the testing platform as described in the foregoing embodiments, but is not limited thereto. Method 200 mainly includes the following steps: S210. Connect the device under test to the device access unit. Based on the interface type of the device under test (CAN, RS422 / 232, TCP / IP, etc.), select the corresponding standard interface on the device access unit for connection. If the device under test uses a non-standard interface, a dedicated board corresponding to the interface specification of the device under test can be installed on the device access unit before connecting the lines.

[0041] S220. The digital model unit loads and runs a digital model adapted to the type of the connected device under test. Based on the type of the device under test, it retrieves the corresponding digital model from the digital model library, loads the digital model onto the workstation, and runs it. This ensures that during simulation, the digital model only simulates satellite functional modules and signal flows other than those of the device under test, and reserves corresponding interface nodes for the device under test. After loading and running, the digital model and the device under test together form a complete satellite system.

[0042] S230. In response to the type of the unit under test, the measurement and control unit invokes the corresponding test case sequence. The test case sequence includes satellite control commands and corresponding command response status variables. Based on the type of the unit under test, the measurement and control unit invokes the test case sequence corresponding to that type of unit from a pre-set test case sequence library. Different types of units under test have different test case sequences, which contain various functional performance test items and verification steps for that type of unit under test.

[0043] S240. The telemetry and control unit sends the test case sequence to the digital model unit and receives satellite status signal changes transmitted by the digital model unit. The digital model simulates the overall satellite status changes under the control commands, and also transmits the control commands to the lower-level control module based on internal protocols. The lower-level control module converts these commands into direct control codes or single-machine-level protocol control codes, which are then sent to the tested single-machine unit via the single-machine access unit. The tested single-machine unit responds physically under the control codes, collects its own status through sensors, and sends it to the digital model via the single-machine access unit in the form of single-machine code packets. The digital model assembles the single-machine code packets into corresponding single-machine telemetry packets and sends them to the telemetry and control unit. The telemetry and control unit identifies the tested single-machine unit's response under satellite control commands by observing changes in the single-machine telemetry packets, verifying the performance of the tested single-machine unit under the overall satellite environment.

[0044] In some embodiments, the satellite control commands sent by the measurement and control unit to the digital model unit include predefined satellite control commands. Predefined satellite control commands refer to a standardized set of control commands pre-compiled according to the type of the device under test and the test case sequence. During the test case sequence design phase, corresponding satellite control commands are compiled and stored in the instruction library of the measurement and control unit for each functional performance indicator that needs to be verified by the device under test. During test execution, the measurement and control unit sequentially calls the predefined satellite control commands according to the definition of the test case sequence and sends them to the digital model unit, driving the digital model and the device under test to generate responses. Predefining the satellite control commands as standardized commands ensures that the content and timing of the commands sent in each test are consistent, guaranteeing the repeatability of the testing process and the comparability of the results.

[0045] In some embodiments, before or during testing, the measurement and control unit (TT&C) receives satellite control commands through a human-machine interface (HMI). For example, testers can view the test case sequence of the unit under test (UUT) through the HMI and select specific test case sequences or adjust test parameters as needed. During testing, testers can observe the test execution progress and the signal interaction status between the UUT and the digital model in real time through the HMI, and input operation commands, including selecting test case sequences and configuring test parameters. The TT&C responds to the testers' operation commands, dynamically adjusting the execution order and content of the test case sequences. This HMI mechanism allows testers to maintain control over the testing process throughout the entire testing process, flexibly adjust testing methods based on real-time feedback, and manually intervene in abnormal situations, thus improving the flexibility of the testing platform.

[0046] This embodiment of the large-scale satellite single-unit testing method realizes closed-loop testing based on digital models. Compared with the traditional all-physical testing method, it reduces the physical requirements of satellite single units, simplifies the test scenario construction, and supports the parallel deployment of multiple test systems to carry out batch testing.

[0047] The basic concepts have been described above. Obviously, for those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application, and therefore remain within the spirit and scope of the exemplary embodiments of this application.

[0048] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0049] Some aspects of this application can be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The aforementioned hardware or software may be referred to as a "data block," "module," "engine," "unit," "component," or "system." The processor may be one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. Furthermore, aspects of this application may manifest as computer products residing in one or more computer-readable media, including computer-readable program code. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, magnetic tapes, etc.), optical discs (e.g., compressed CDs, digital multifunction DVDs, etc.), smart cards, and flash memory devices (e.g., cards, sticks, key drives, etc.).

[0050] Although this application has been described with reference to specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, any changes or modifications to the above embodiments within the essential spirit of this application will fall within the scope of the claims of this application.

Claims

1. A large-scale satellite single-unit test platform, characterized in that, include: The digital model unit includes at least one digital model, which is formed by decoupling the functional modules of the test unit from the reference digital satellite, wherein the test unit is the hardware unit under test; the digital model is configured to simulate the various functional modules of the satellite and the signal flow between the functional modules, send status commands to control the test unit, receive status information of the test unit, and simulate satellite status changes based on the received satellite control commands. A stand-alone access unit is communicatively connected to the digital model unit and is provided with a physical access interface for the stand-alone unit under test. It is configured to perform bidirectional signal interaction between the digital model unit and the stand-alone unit under test. The telemetry and control unit, which is communicatively connected to the digital model unit, is configured to respond to the type of the connected test unit by calling the corresponding test case sequence, sending the test case sequence to the digital model unit, and receiving satellite status change signals.

2. The large-scale satellite single-unit test platform as described in claim 1, characterized in that, The digital model is formed by decoupling the functional modules corresponding to the tested unit from the benchmark digital satellite, including: The functional modules corresponding to the unit under test in the reference digital satellite are decoupled from the reference digital satellite, an information flow middleware is constructed, and time synchronization between the unit under test and the decoupled digital satellite is established; wherein the information flow middleware is configured to receive control commands issued by the satellite service software and status information returned by the unit under test.

3. The large-scale satellite single-unit test platform as described in claim 1, characterized in that, The functional modules corresponding to the tested unit include one of the following: reaction wheel functional module, gyroscope functional module, propulsion functional module, power control functional module, SADA rotation functional module, and load functional module.

4. The large-scale satellite single-unit test platform as described in claim 1, characterized in that, The digital model in the digital model unit is also configured to simulate the self-management function of the satellite's own state changes.

5. The large-scale satellite single-unit test platform as described in claim 1, characterized in that, The stand-alone access unit is provided with at least one of the following interfaces: CAN interface, RS422 interface, RS232 interface, or TCP / IP interface.

6. The large-scale satellite single-unit test platform as described in claim 1, characterized in that, The digital model unit includes a virtual digital chip, on which the satellite's operational software is loaded.

7. The large-scale satellite single-unit test platform as described in claim 1, characterized in that, The digital model unit includes various types of digital models. Different types of digital models are adapted to the testing and acceptance of different single machines under test, and various different digital models form a digital model library.

8. A method for large-scale satellite single-unit testing, characterized in that, Applied to the large-scale satellite single-unit test platform as described in any one of claims 1-7, comprising: The single device to be tested is connected to the single device access unit; The digital model unit loads and runs a digital model that is adapted to the type of the connected test unit; The measurement and control unit responds to the type of the unit under test by calling the corresponding test case sequence, which includes satellite control commands and corresponding command response status variables. The telemetry and control unit sends the test case sequence to the digital model unit and receives changes in satellite status signals transmitted by the digital model unit.

9. The method for large-scale satellite single-unit testing as described in claim 8, characterized in that, The satellite control commands include predefined satellite control commands.

10. The method for large-scale satellite single-unit testing as described in claim 8, characterized in that, Before or during the test, the telemetry and control unit obtains the satellite control commands through human-computer interaction.

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