Open software and hardware cooperation multi-satellite on-orbit scheme verification system and method

Abstract

The invention provides an open software and hardware cooperation multi-satellite in-orbit scheme verification system and method. The system comprises at least two satellite-ground joint test devices connected through a distributed network, a distributed comprehensive test management module, a dynamics simulation module and a satellite-borne environment simulation module. The distributed comprehensive test management module is used for acquiring current states of the at least two satellite-ground joint test devices, determining a test instruction and sending the test instruction to the dynamics simulation module and the satellite-borne environment simulation module; the dynamics simulation module is used for receiving the test instruction for dynamics simulation to obtain dynamics simulation data and sending the dynamics simulation data to the satellite-borne environment simulation module; and the satellite-borne environment simulation module is used for receiving the dynamics simulation data and the test instruction to carry out satellite-borne environment simulation to obtain a simulation result, and sending the simulation result to the distributed comprehensive test management module. According to the scheme, parallel verification of multiple satellites is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of on-orbit verification, and particularly relates to an open software and hardware collaborative multi-satellite on-orbit scheme verification system and method. Background Art

[0002] The complexity of current space missions is gradually increasing, and many space missions cannot be completed by a single satellite. Therefore, it is necessary to jointly complete a certain complex space mission by multiple satellites. However, the controller structures of each satellite are not the same, such as single-machine structure, homogeneous multi-machine structure, heterogeneous multi-machine structure, etc. When the mission plan of the satellite consortium changes or a new mission is executed, it is necessary to conduct sufficient verification on the ground. However, the traditional scheme verification platform can only verify the single-satellite scheme and lacks the function of verifying the parallel scheme of the satellite consortium. In this state, there is coupling between satellites, and it is also necessary to fully verify the correctness of the operation of each individual satellite when verifying the parallel scheme of the consortium. Therefore, an open software and hardware collaborative multi-satellite on-orbit scheme verification system and method are needed. Summary of the Invention

[0003] The present invention provides an open software and hardware collaborative multi-satellite on-orbit scheme verification system and method, which can realize the parallel verification of the joint space mission plan of multiple satellites.

[0004] In the first aspect, the present invention provides an open software and hardware collaborative multi-satellite on-orbit scheme verification system, including:

[0005] At least two satellite-ground joint test devices connected by a distributed network, a distributed integrated test management module, a dynamics simulation module, and an on-board environment simulation module;

[0006] The distributed integrated test management module is configured to obtain the current states of at least two of the satellite-ground joint test devices and determine test instructions, and send the test instructions to the dynamics simulation module and the on-board environment simulation module;

[0007] The dynamics simulation module is configured to receive the test instructions to perform dynamics simulation, obtain dynamics simulation data, and send the dynamics simulation data to the on-board environment simulation module;

[0008] The on-board environment simulation module is configured to receive the dynamics simulation data and the test instructions to perform on-board environment simulation to obtain simulation results, and send the simulation results to the distributed integrated test management module.

[0009] Optionally, it further includes a bus monitoring module and a bus data distribution server;

[0010] The bus monitoring module is connected to the bus data distribution server via a 1553B bus; the bus data distribution server is connected to the dynamic simulation module via Ethernet; the bus monitoring module and the bus data distribution server are respectively connected to the on-board environment simulation module via a 1553B bus.

[0011] Optionally, the bus monitoring module is used to monitor the communication data of the 1553B bus.

[0012] The bus data distribution server is used to distribute the dynamic simulation data output by the dynamic simulation module to the on-board environment simulation module.

[0013] Optionally, the distributed integrated test management module includes a multi-satellite metadata server, a multi-satellite test application server, and at least two data storage servers; where the number of satellite-ground joint test devices is the same as the number of data storage servers, and each satellite-ground joint test device corresponds to a single satellite under the consortium.

[0014] The multi-satellite metadata server, the multi-satellite test application server, and the data storage servers are all connected via Ethernet.

[0015] Optionally, the multi-satellite metadata server is used to obtain the current status information of each satellite, set the test conditions of each satellite, and send the test conditions of each satellite to the multi-satellite test application server.

[0016] The multi-satellite test application server is used to receive the test conditions of each satellite and issue the test instructions.

[0017] The data storage server is used to store the test instructions, the current status information, and the telemetry data corresponding to the satellite.

[0018] Optionally, the on-board environment simulation module includes: at least one on-board computer, at least one full digital simulation platform, and a data management simulation computer.

[0019] The full digital simulation platform and the data management simulation computer are connected via Ethernet.

[0020] Optionally, the on-board environment simulation module includes: at least one on-board computer, at least one full digital simulation platform, and a data management simulation computer.

[0021] The on-board computer, the full digital simulation platform, and the data management simulation computer are connected via a 1553B bus.

[0022] Optionally, the sum of the number of the on-board computers and the number of the all-digital simulation platforms is the same as the number of the satellite-ground joint test devices.

[0023] Optionally, the digital management simulation computer is configured to send the test instructions to the on-board computer and the all-digital simulation platform.

[0024] Both the on-board computer and the all-digital simulation platform are configured to simulate the on-board environment of each satellite based on the dynamic simulation data and the test instructions to obtain the simulation results.

[0025] In a second aspect, the present invention provides an open software and hardware collaborative multi-satellite on-orbit scheme verification method, which is applied to the open software and hardware collaborative multi-satellite on-orbit scheme verification system described in the first aspect above, and includes:

[0026] Obtain the current state information of the multi-satellite consortium and determine the test instructions.

[0027] Perform dynamic simulation on each satellite based on the test instructions to obtain dynamic simulation data.

[0028] Perform on-board environment simulation based on the test instructions and the dynamic simulation data to obtain simulation results.

[0029] Determine the verification result under the test instructions according to the simulation results.

[0030] Optionally, the performing on-board environment simulation based on the test instructions and the dynamic simulation data to obtain simulation results includes:

[0031] Perform on-board environment simulation on each satellite by using at least one on-board computer and at least one all-digital simulation platform.

[0032] For the on-board computer or the all-digital simulation platform, the following operations are all performed:

[0033] According to the test instructions, obtain the target dynamic simulation data of the satellite corresponding to the on-board computer or the all-digital simulation platform from the dynamic simulation data and perform on-board environment simulation to obtain the target simulation results of the on-board computer or the all-digital simulation platform.

[0034] The embodiments of the present invention provide an open software and hardware collaborative multi-satellite on-orbit scheme verification system and method. The system uses a distributed network to connect multiple satellite-ground joint test devices, and based on a distributed integrated test management module, a dynamics simulation module, and a spaceborne environment simulation module, uses test instructions to verify the satellite-ground joint test devices, and realizes the parallel verification of multiple single-satellite under a consortium. In this way, this solution uses satellite-ground joint test devices based on hardware, a spaceborne environment simulation module based on software and hardware. Through the distributed network, it not only supports the independent verification of each single satellite, but also can jointly complete the test work of the multi-satellite consortium. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0036] Figure 1 is a schematic structural diagram of an open software and hardware collaborative multi-satellite on-orbit scheme verification system provided by an embodiment of the present invention;

[0037] Figure 2 is a schematic structural diagram of another open software and hardware collaborative multi-satellite on-orbit scheme verification system provided by an embodiment of the present invention;

[0038] Figure 3 is a schematic structural diagram of yet another open software and hardware collaborative multi-satellite on-orbit scheme verification system provided by an embodiment of the present invention;

[0039] Figure 4 is a flowchart of an open software and hardware collaborative multi-satellite on-orbit scheme verification method provided by an embodiment of the present invention;

[0040] Reference numerals: 10 - satellite-ground joint test device; 20 - distributed integrated test management module; 30 - dynamics simulation module; 40 - spaceborne environment simulation module; 50 - bus monitoring module; 60 - bus data distribution server; 201 - multi-satellite metadata server; 202 - multi-satellite test application server; 203 - data storage server; 401 - spaceborne computer; 402 - full digital simulation platform; 403 - digital management simulation computer. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0041] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0042] The following describes the specific implementation of the concept of this application.

[0043] Please refer to Figure 1 , the embodiments of the present invention provide an open software and hardware collaborative multi-satellite on-orbit scheme verification system, which includes: at least two satellite-ground joint test devices 10 connected by a distributed network, a distributed integrated test management module 20, a dynamics simulation module 30, and a spaceborne environment simulation module 40;

[0044] The distributed integrated test management module 20 is used to obtain the current status of at least two satellite-ground joint test devices 10 and determine test instructions, and send the test instructions to the dynamics simulation module 30 and the spaceborne environment simulation module 40;

[0045] The dynamics simulation module 30 is used to receive the test instructions for dynamics simulation, obtain dynamics simulation data, and send the dynamics simulation data to the spaceborne environment simulation module 40;

[0046] The spaceborne environment simulation module 40 is used to receive the dynamics simulation data and the test instructions to perform spaceborne environment simulation to obtain simulation results, and send the simulation results to the distributed integrated test management module 20.

[0047] In the implementation of the present invention, the system connects multiple satellite-ground joint test devices through a distributed network, and based on the distributed integrated test management module, the dynamics simulation module, and the spaceborne environment simulation module, uses test instructions to verify the satellite-ground joint test devices, and realizes the parallel verification of a certain multi-satellite consortium. In this way, this solution uses satellite-ground joint test devices based on hardware and a spaceborne environment simulation module based on software and hardware. Through the distributed network, it not only supports the independent verification of each single satellite, but also can jointly complete the test work of the multi-satellite consortium.

[0048] In the present invention, the system uses the interface of a highly reliable distributed network service system for real-time high-frequency data communication to realize the interconnection and intercommunication between the above-mentioned modules.

[0049] In a preferred embodiment, as Figure 2 shown, this solution further includes a bus monitoring module 50 and a bus data distribution server 60;

[0050] The bus monitoring module 50 is connected to the bus data distribution server 60 via a 1553B bus; the bus data distribution server 60 is connected to the dynamics simulation module 30 via Ethernet; the bus monitoring module 50 and the bus data distribution server 60 are respectively connected to the on-board environment simulation module 40 via a 1553B bus;

[0051] The bus monitoring module 50 is used to monitor the communication data of the 1553B bus;

[0052] The bus data distribution server 60 is used to distribute the dynamics simulation data output by the dynamics simulation module 30 to the on-board environment simulation module 40.

[0053] In the present invention, as Figure 3 shown, the bus data distribution server includes several 1553 boards, which can realize the distribution of the dynamics simulation data of different satellites, realize the distributed storage and access of data, thereby improving the performance, scalability, availability and fault tolerance of the database, and making the data transmission have high real-time performance and high reliability. The communication data of the 1553B bus includes all data transmitted through the 1553B bus. It should be noted that Figure 3 the satellite-ground joint test equipment is not shown in the figure.

[0054] In the present invention, the dynamics simulation data generated by the dynamics simulation module is transmitted to the bus data distribution server via Ethernet and then transmitted to the on-board environment simulation module via the 1553B bus. At this time, the dynamics simulation data includes the orbital data of each satellite, and the basic data of relevant sensors and thrust mechanisms; at the same time, other relevant data other than the dynamics simulation data in the dynamics simulation module is transmitted to the on-board environment simulation module via Ethernet, so that it can not only include the occasions of high reliability of data transmission and real-time control, but also improve the transmission efficiency of relevant data.

[0055] In a preferred embodiment, as Figure 2 shown, the distributed integrated test management module 20 includes a multi-satellite metadata server 201, a multi-satellite test application server 202, and at least two data storage servers 203; the number of satellite-ground joint test equipment 10 is the same as the number of data storage servers 203, and each satellite-ground joint test equipment 10 corresponds to a single satellite under the consortium;

[0056] The multi-satellite metadata server 201, the multi-satellite test application server 202, and the data storage servers 203 are all connected via Ethernet;

[0057] The multi-satellite metadata server 201 is used to obtain the current status information of each satellite, set the test conditions of each satellite, and send the test conditions of each satellite to the multi-satellite test application server;

[0058] The multi-satellite test application server 202 is used to receive the test working conditions of each satellite and issue test instructions.

[0059] The data storage server 203 is used to store the test instructions, current status information, and telemetry data of the corresponding satellite.

[0060] In the present invention, each satellite-ground joint test device corresponds to a single satellite of the consortium. The satellite-ground joint test device can receive the telemetry data transmitted by each satellite, and each data storage server fixedly stores the relevant data of a single satellite, thereby facilitating subsequent specific analysis of the satellite based on the data stored in the data storage service.

[0061] In the present invention, based on the current test working conditions of each satellite, the test instructions for any single satellite can be determined, and the test instructions for the combination of any two or more satellites can also be determined. Thus, when the dynamic simulation module and the on-board environment simulation module receive the corresponding test instructions, they can perform simulation for any single satellite or any combination of multiple satellites to obtain simulation results, and then the distributed integrated test management module analyzes based on the simulation results to obtain the verification results based on the test instructions.

[0062] It should be noted that the test instructions are set by the staff based on the test working conditions of each satellite. For example, it can be to verify the correctness of the data acquisition and instruction sending of the foreign satellites in the multi-satellite combination mode; to verify the feasibility of component replacement and mode switching (including sensor components and actuator components) caused by component failures; to verify the correctness of the pull-together operation after data exchange failures; to verify the effectiveness of the automatic switching function after bus failures; to verify the effectiveness of the bus control right switching function after single-unit failures; to verify the effectiveness of the data and instruction injection after the ground actively intervenes after various failures, etc.

[0063] In a preferred embodiment, as Figure 2 shown, the on-board environment simulation module 40 includes: at least one on-board computer 401, at least one full-digital simulation platform 402, and a data management simulation computer 403;

[0064] The full-digital simulation platform 402 and the data management simulation computer 403 are connected by Ethernet;

[0065] The on-board computer 401, the full-digital simulation platform 402, and the data management simulation computer 403 are connected by a 1553B bus;

[0066] The data management simulation computer 403 is used to send the test instructions to the on-board computer and the full-digital simulation platform;

[0067] The on-board computer 401 and the full-digital simulation platform 402 are both used to simulate the on-board environment of each satellite based on the dynamic simulation data and the test instructions to obtain simulation results.

[0068] It should be noted that, as Figure 3 shown, in the on-board environment simulation module, both an Ethernet connection and a 1553B bus connection are used between the all-digital simulation platform (i.e., the multi-computer all-digital simulation platform) and the data management simulation computer, enabling data between hardware to be connected via the 1553B bus and data between software to be connected via the Ethernet, achieving the combination of software and hardware and improving the reliability and scalability of the verification system.

[0069] In the present invention, the on-board environment simulation module is connected to both the semi-physical simulation test platform (i.e., the on-board computer) and the all-digital simulation platform. Therefore, in the case of multi-satellite combinations, the satellite simulation verification platforms of each satellite are "either hard or soft", enabling mixing to meet the verification requirements of various combined configurations.

[0070] The present invention adopts a distributed multi-system architecture, combining the semi-physical simulation test platform and the all-digital simulation platform to form a heterogeneous simulation system, solving the real-time problem of data transmission between large-scale distributed network nodes, supporting the flexible addition and deletion of communication nodes on the existing communication network, and reducing the integration and splitting costs. At the same time, it not only supports the independent verification of each satellite but also can jointly complete the test verification work of the multi-satellite consortium, realizing an iterative and incremental test verification process, and having the ability of software-hardware interconnection while conducting multi-system joint integration testing during the intermediate transition period. The verification system provided by the present invention is simple to implement, flexible to use, and has good scalability, and can be extended to other multi-satellite cooperation verification fields. Compared with the existing methods, it has strong market competitiveness, is effective, and has broad application prospects.

[0071] It should be noted that in Figure 2 and Figure 3 , the solid lines all represent Ethernet connections, and the dashed lines all represent 1553B bus connections. Figure 3 The bus monitoring module in

[0072] adopts a 1553B bus monitoring system, the dynamics simulation module adopts a dynamics simulation computer, and the bus data distribution server adopts a 1553 data distribution server.

[0073] As Figure 4 shown, the present invention also provides an open software-hardware collaborative multi-satellite on-orbit scheme verification method, including:

[0074] Step S0, obtaining the current state information including the multi-satellite consortium and determining the test instruction;

[0075] Step S2: Perform dynamic simulation on each satellite based on the test instruction to obtain dynamic simulation data;

[0076] Step S4: Perform on-orbit environment simulation based on the test instruction and the dynamic simulation data to obtain a simulation result;

[0077] Step S6: Determine the verification result under the test instruction according to the simulation result.

[0078] In the embodiment of the present invention, Step S0 and Step S6 are executed by the distributed integrated test management module, Step S2 is executed by the dynamic simulation module, and Step S4 is executed by the on-orbit environment simulation module.

[0079] Specifically, for example, in a consortium composed of four satellites, namely Satellite 1, Satellite 2, Satellite 3, and Satellite 4, if the current status information of Satellite 1 is a sensor failure, then determine that the test instruction is the effectiveness of the mode switch caused by the sensor failure, and then perform dynamic simulation on each satellite based on this test instruction to obtain dynamic simulation data; then perform on-orbit environment simulation on the dynamic simulation data according to the test instruction to obtain a simulation result, and determine the effectiveness of the mode switch caused by the sensor failure by analyzing the simulation result.

[0080] In Step S4, performing on-orbit environment simulation based on the test instruction and the dynamic simulation data to obtain a simulation result includes:

[0081] Perform on-orbit environment simulation on each satellite using at least one on-orbit computer and at least one full digital simulation platform;

[0082] For both the on-orbit computer and the full digital simulation platform, execute:

[0083] According to the test instruction, obtain the target dynamic simulation data of the satellite corresponding to the on-orbit computer or the full digital simulation platform from the dynamic simulation data and perform on-orbit environment simulation to obtain the target simulation result of the on-orbit computer or the full digital simulation platform.

[0084] For example, as described in the previous example, as Figure 3 shown, the on-orbit environment simulation module includes one on-orbit computer and three full digital simulation platforms. Satellite 1 uses the on-orbit computer to perform on-orbit environment simulation, and Satellite 2, Satellite 3, and Satellite 4 all use the full digital simulation platform to perform on-orbit environment simulation.

[0085] It can be understood that the structure illustrated in the embodiments of the present invention does not constitute a specific limitation on an open software and hardware collaborative multi-satellite on-orbit scheme verification system. In other embodiments of the present invention, an open software and hardware collaborative multi-satellite on-orbit scheme verification system may include more or fewer components than those illustrated, or combine certain components, or split certain components, or have different component arrangements. The illustrated components can be implemented in hardware, software, or a combination of software and hardware.

[0086] Regarding the information interaction, execution process, etc. between the various modules within the above-mentioned device, since they are based on the same concept as the method embodiments of the present invention, the specific content can be referred to the description in the method embodiments of the present invention and will not be elaborated here.

[0087] It should be noted that, moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements not only includes those elements but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising one..." does not exclude the presence of additional identical elements in the process, method, article or device comprising the said element.

[0088] Those of ordinary skill in the art can understand that all or part of the steps for implementing the above method embodiments can be completed by hardware related to program instructions. The aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it performs the steps including those of the above method embodiments; and the aforementioned storage medium includes various media such as ROM, RAM, magnetic disk or optical disc that can store program codes.

[0089] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An open software and hardware collaborative multi-satellite on-orbit solution verification system, characterized in that: include: At least two satellite-ground joint test equipment, a distributed comprehensive test management module, a dynamics simulation module, and a satellite-borne environment simulation module connected by a distributed network; The distributed integrated test management module is used to obtain the current status of at least two of the satellite-ground joint test equipment and determine the test instructions, and send the test instructions to the dynamics simulation module and the satellite-borne environment simulation module; The dynamics simulation module is used to receive the test instruction to perform dynamics simulation, obtain dynamics simulation data, and send the dynamics simulation data to the onboard environment simulation module; The onboard environment simulation module is used to receive the dynamic simulation data and the test instructions to perform onboard environment simulation to obtain simulation results, and send the simulation results to the distributed comprehensive test management module.

2. The system according to claim 1, characterized in that It also includes a bus monitoring module and a bus data distribution server; The bus monitoring module and the bus data distribution server are connected via a 1553B bus; the bus data distribution server and the dynamics simulation module are connected via Ethernet; the bus monitoring module and the bus data distribution server are connected to the onboard environment simulation module via a 1553B bus respectively.

3. The system according to claim 2, characterized in that The bus monitoring module is used to monitor the communication data of the 1553B bus; The bus data distribution server is used to distribute the dynamics simulation data output by the dynamics simulation module to the onboard environment simulation module.

4. The system according to claim 1, characterized in that The distributed integrated test management module includes a multi-satellite metadata server, a multi-satellite test application server, and at least two data storage servers; The number of the satellite-ground joint test equipment is the same as the number of the data storage servers, and each of the satellite-ground joint test equipment corresponds to a satellite; The multi-satellite metadata server, the multi-satellite test application server, and the data storage server are all connected by Ethernet.

5. The system according to claim 4, characterized in that The multi-satellite metadata server is used to obtain current status information of each of the satellites to set a test condition for each of the satellites, and send the test condition for each of the satellites to the multi-satellite test application server; The multi-satellite test application server is used to receive the test conditions of each of the satellites and issue the test instructions; The data storage server is used to store the test instructions, the current status information and telemetry data corresponding to the satellite.

6. The system according to claim 1, characterized in that The onboard environment simulation module includes: at least one onboard computer, at least one all-digital simulation platform and a digital tube simulation computer; The all-digital simulation platform and the digital tube simulation computer are connected via Ethernet.

7. The system according to claim 4, characterized in that The onboard environment simulation module includes: at least one onboard computer, at least one all-digital simulation platform and a digital tube simulation computer; The onboard computer, the all-digital simulation platform and the digital tube simulation computer are connected by a 1553B bus.

8. The system according to claim 6 or 7, characterized in that: The sum of the number of the onboard computers and the full digital simulation platforms is the same as the number of the satellite-ground joint test equipment; and / or, The digital tube simulation computer is used to send the test instruction to the onboard computer and the all-digital simulation platform; The onboard computer and the all-digital simulation platform are both used to simulate the onboard environment of multiple satellites based on the dynamic simulation data and the test instructions to obtain the simulation results.

9. An open software and hardware collaborative multi-satellite on-orbit solution verification method, characterized in that: Applicable to the open software and hardware collaborative multi-satellite on-orbit solution verification system as claimed in any one of claims 1 to 8, comprising: Acquire current status information including multiple satellites and determine test instructions; Performing dynamic simulation on each satellite based on the test instruction to obtain dynamic simulation data; Performing onboard environment simulation according to the test instruction and the dynamics simulation data to obtain a simulation result; According to the simulation result, a verification result under the test instruction is determined.

10. The method according to claim 9, characterized in that The performing of onboard environment simulation according to the test instruction and the dynamics simulation data to obtain a simulation result includes: Using at least one onboard computer and at least one fully digital simulation platform to simulate the onboard environment of each of the satellites; For the onboard computer or the all-digital simulation platform, the following steps are performed: According to the test instructions, the target dynamics simulation data of the satellite corresponding to the onboard computer or the all-digital simulation platform is obtained from the dynamics simulation data and the onboard environment simulation is performed to obtain the target simulation results of the onboard computer or the all-digital simulation platform.

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