A networked spacecraft navigation system simulation test device and method based on real-time trajectory injection

Abstract

A device and method for simulating and testing a networked spacecraft navigation system based on real-time trajectory injection relates to the field of spacecraft testing technology. The device comprises a multi-channel navigation dynamic simulation source, a dual-network card computer, and several GNC test devices. The multi-channel navigation dynamic simulation source system simulation control computer establishes communication with each GNC test device by forwarding data via the dual-network card computer, transmitting information via the UDP communication protocol. The dual-network card computer is configured with multiple transceivers to enable forwarding of multiple UDP multicast addresses. During testing, the GNC test devices transmit trajectory points in real time to the multi-channel navigation dynamic simulation source device. This device and method can implement multi-spacecraft networked flight testing and is capable of testing the navigation functions of networked spacecraft in a variety of different scenarios, effectively expanding the capabilities of the spacecraft navigation test system.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft testing technology, and in particular to a networked spacecraft navigation system simulation test device and method based on real-time trajectory injection. Background Art

[0002] As spacecraft scale evolves from single-spacecraft to networked systems, spacecraft testing methods must also adapt to network characteristics. On the one hand, multi-spacecraft network testing tasks require simultaneous output of multiple satellites in different orbits. Traditional navigation simulation sources only support single / dual satellite testing and lack multiple synchronous external interfaces. Therefore, it is impossible to support multi-satellite collaborative concurrent testing by activating multiple devices.

[0003] Specifically, during the test of the multi-spacecraft networked navigation system, it is necessary to establish communication between the GNC (Guidance Navigation Control) ground test equipment and the multi-channel navigation simulation source. The traditional GNC orbit control working mode is aimed at a single spacecraft. The GNC front station and the multi-channel navigation dynamic simulation source system simulation control computer transmit information through the TCP / IP protocol. The multi-channel navigation dynamic simulation source system simulation control computer acts as the client and the GNC front station acts as the server. The GNC front station can only establish a connection with one navigation multi-channel navigation dynamic simulation source system simulation control computer at the same time, which cannot meet the testing needs of multiple spacecraft.

[0004] On the other hand, during multi-satellite network testing, the attitudes and orbits of each satellite are different, and it is impossible to determine high-dynamic scenes only by the six numbers at the starting moment. Summary of the Invention

[0005] The present disclosure provides a simulation test device and method for a networked spacecraft navigation system based on real-time trajectory injection, which uses a GNC test device, a dual-network card computer, and a multi-channel simulation source that can be simultaneously controlled as a test system. The network where the GNC test device and the multi-channel navigation simulation source are located communicates through a dual-network card computer based on the UDP multicast protocol, and transparently forwards the communication through the data gateway software on the dual-network card computer to achieve GNC real-time trajectory injection, accurately simulate the flight trajectory of each spacecraft, control the orbit of the networked spacecraft, and realize simulated network flight testing.

[0006] The present disclosure provides a networked spacecraft navigation system simulation test device based on real-time trajectory injection, which mainly includes: a multi-channel navigation dynamic simulation source, a dual-network card computer, and several GNC test equipment, wherein:

[0007] The multi-channel navigation dynamic simulation source system simulation control computer and each GNC test equipment establish communication through the dual network card computer forwarding data;

[0008] Each GNC test device and the multi-channel navigation dynamic simulation source system simulation control computer transmit information through the UDP communication protocol;

[0009] The dual-network card computer transparently forwards data through the data gateway software, which is equipped with multiple transceivers to achieve forwarding of multiple UDP multicast addresses;

[0010] During the test, the GNC test equipment sends trajectory points, which are multicast to the multi-channel navigation dynamic simulation source system through a dual-network card computer. The simulation source generates and outputs multiple navigation signals, which are broadcast to the networked spacecraft, enabling GNC to simultaneously control the orbits of the networked spacecraft.

[0011] The networked spacecraft navigation system simulation test method based on real-time trajectory injection using the above-mentioned device mainly includes the following steps:

[0012] S1, establishing a connection: the multi-channel navigation dynamic simulation source system simulation control computer and each GNC test device respectively establish a connection with the dual network card computer via a multicast address;

[0013] S2, Initialization: The simulation control computer of the multi-channel navigation dynamic simulation source system is initialized. During the initialization process, the receiving orbit starting point sent by the GNC test equipment is received. After the initialization is completed, the simulation is automatically started to receive the point data transmitted in real time by the GNC test equipment.

[0014] S3, data reception: After the connection is established, the multi-channel navigation dynamic simulation source system simulation control computer receives the user point data sent by the GNC test equipment at a set frequency; the multi-channel navigation dynamic simulation source system simulation control computer then sends the user point data to the simulation source at the same frequency at a fixed time;

[0015] S4, simulation extrapolation and stop: When the multi-channel navigation dynamic simulation source system simulation control computer determines that the GNC no longer sends data, it performs orbit extrapolation according to the simulation source simulation information until it receives the instruction to stop the simulation and stops the simulation.

[0016] Furthermore, in step S2, the track starting point is transmitted to the simulation source by the GNC test equipment in the form of a configuration file before the initialization operation.

[0017] Furthermore, in step S3, the GNC test device sends user point data at a frequency of 1 packet / 100ms.

[0018] Furthermore, in step S3, since the information packet sending cycle and the simulation cycle are not completely synchronized, the multi-channel navigation dynamic simulation source system sets a buffer area, and accesses the point data in the buffer area to ensure that the multi-channel navigation dynamic simulation source system performs data fitting and simulation calculations at a predetermined frequency.

[0019] Furthermore, in step S4, when the multi-channel navigation dynamic simulation source system simulation control computer detects that the buffer point data is less than the set number, it is considered that the GNC no longer sends data.

[0020] Compared with the prior art, the present disclosure has the following advantages: 1) While conventional test systems use a single-point connection between the GNC test equipment and the multi-channel navigation dynamic simulation source system simulation control computer, the test system disclosed herein utilizes a dual-network card computer equipped with multiple transceivers to achieve flexible multi-point connection between the GNC test equipment and the multi-channel navigation dynamic simulation source system, thereby supporting simultaneous testing of multiple spacecraft;

[0021] 2) Compared with traditional methods, the test method for networked spacecraft is highly scalable and flexible, capable of handling a large number of concurrent testing requirements. The test capability can be dynamically expanded according to mission requirements to meet the testing needs of networked spacecraft of different scales.

[0022] 3) The UDP multicast protocol is used. Compared with the TCP / IP protocol used in traditional testing methods, it does not require connection establishment and data confirmation during data transmission, reducing the overhead of establishing and releasing connections. It has low data transmission latency and does not require maintaining connection status. It has stronger real-time performance and can respond more quickly to changes in test scenarios or test tasks.

[0023] 4) It consumes less network resources, can achieve higher data transmission efficiency within limited bandwidth resources, has higher data processing accuracy, and can provide highly reliable simulation data for test tasks. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and other objects, features and advantages of the present disclosure will become more apparent through a more detailed description of exemplary embodiments of the present disclosure in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present disclosure.

[0025] Figure 1 is a diagram of a network topology according to an exemplary embodiment of the present disclosure;

[0026] Figure 2 A flow chart is shown for testing an exemplary embodiment. DETAILED DESCRIPTION

[0027] The preferred embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although preferred embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided to make the present disclosure more thorough and complete, and to fully convey the scope of the present disclosure to those skilled in the art.

[0028] When testing the multi-spacecraft networked navigation system, how to achieve communication between the GNC ground test equipment and the multi-channel navigation dynamic simulation source is the basis for conducting multi-spacecraft networked navigation system testing. In order to achieve communication between the GNC ground test equipment and the multi-channel navigation simulation source, the present disclosure proposes a networked spacecraft navigation system simulation test device and method based on real-time trajectory injection.

[0029] In an exemplary embodiment, the network topology of the networked spacecraft navigation system simulation test device based on real-time trajectory injection is as shown in the attached figure. Figure 1 As shown:

[0030] The test device consists of n GNC test devices, a dual-network card computer, and a multi-channel navigation dynamic simulation source;

[0031] Among them, the multi-channel navigation dynamic simulation source system simulation control computer is connected to the measurement and control network, and the GNC test equipment is connected to the test network. The two establish communication by forwarding data through a pair of network card computers;

[0032] Point data is transparently forwarded through data gateway software on a computer with dual network cards, and multiple transceivers are configured to achieve forwarding of multiple UDP multicast addresses;

[0033] The GNC test equipment and the navigation multi-channel navigation dynamic simulation source system simulation control computer transmit information through the UDP communication protocol, and the information transmission is carried out in accordance with the specified information packet format;

[0034] During the test, the GNC test equipment sends trajectory point data, which is multicast to the multi-channel navigation dynamic simulation source system through a dual-network card computer. The simulation source generates and outputs multiple navigation signals, which are broadcast to the networked spacecraft, enabling GNC to simultaneously control the orbits of the networked spacecraft.

[0035] The test process is as attached Figure 2 As shown, it mainly includes the following steps:

[0036] (1) Establishing a connection: After the GNC test equipment is started, it starts sending point data to the multicast address. The multi-channel navigation dynamic simulation source system simulation control computer establishes a connection with the multicast address and receives the point data sent by the GNC test equipment after the simulation is started.

[0037] (2) Initialization: The multi-channel navigation dynamic simulation source system simulation control computer needs to be initialized before the simulator starts the simulation. During the initialization process, the orbit starting point needs to be sent. This point is provided by the GNC subsystem before the initialization operation and written in the configuration file and passed to the simulation source in the form of a configuration file. After the initialization is completed, the simulation starts automatically and receives the real-time data transmitted by the GNC test equipment.

[0038] (3) Data reception: After the connection is established, the multi-channel navigation dynamic simulation source system simulation control computer can receive the user point data sent by the GNC test equipment. The specific format of the information packet is shown in Table 1. The frequency of information packet sending is preferably 1 packet / 100ms. The multi-channel navigation dynamic simulation source system simulation control computer then sends the user point data to the simulation source at a frequency of 1 packet / 100ms.

[0039] Since the information packet sending cycle and the simulation cycle are not completely synchronized, the multi-channel navigation dynamic simulation source system needs to establish a cache area. By accessing the point data in the cache area, it is ensured that the multi-channel navigation dynamic simulation source system performs data fitting and simulation calculations at the established frequency.

[0040] Table 1 Information packet format

[0041]

[0042] (6) Simulation stop: When the multi-channel navigation dynamic simulation source system simulation control computer detects that the buffer area is less than a certain amount (the specific value is configurable), it is considered that the GNC is no longer sending data and the orbit is extrapolated according to the simulation source simulation information. After receiving the "stop simulation" command, the simulation source stops simulation.

[0043] In this embodiment, a network topology structure of GNC test equipment and navigation simulation source is constructed: the GNC test equipment and navigation simulation source network communicate with a dual-network card computer based on the UDP multicast protocol, transparently forwarding the data through the data gateway software on the dual-network card computer, and configuring multiple transceivers to achieve forwarding of multiple UDP multicast addresses. This solves the problem of track control of GNC test equipment in networked spacecraft navigation simulation testing and achieves the purpose of networked spacecraft navigation simulation collaborative testing.

[0044] A data fitting strategy is proposed to solve the problem of asynchronous simulation cycles;

[0045] A simulation test method for networked spacecraft navigation systems based on real-time trajectory injection is proposed, which can realize multi-spacecraft network flight testing and has the ability to test the navigation functions of networked spacecraft in a variety of different scenarios, thus expanding the capabilities of the spacecraft navigation test system.

[0046] The above technical solutions are only exemplary embodiments of the present invention. For those skilled in the art, it is easy to make various types of improvements or modifications based on the application methods and principles disclosed in the present invention, and are not limited to the methods described in the above specific embodiments of the present invention. Therefore, the methods described above are only preferred and do not have a restrictive meaning.

Claims

1. A networked spacecraft navigation system simulation test device based on real-time trajectory injection, characterized in that: include: Multi-channel navigation dynamic simulation source, dual network card computer, and several GNC test equipment, including: The multi-channel navigation dynamic simulation source system simulation control computer and each GNC test equipment establish communication through the dual network card computer forwarding data; Each GNC test device and the multi-channel navigation dynamic simulation source system simulation control computer transmit information through the UDP communication protocol; The dual-network card computer transparently forwards data through the data gateway software, which is equipped with multiple transceivers to achieve forwarding of multiple UDP multicast addresses; During the test, the GNC test equipment sends trajectory points, which are multicast to the multi-channel navigation dynamic simulation source system through a dual-network card computer. The simulation source generates and outputs multiple navigation signals, which are broadcast to the networked spacecraft, enabling GNC to simultaneously control the orbits of the networked spacecraft.

2. A method for simulating and testing a networked spacecraft navigation system based on real-time trajectory injection using the apparatus of claim 1, comprising the following steps: S1, establishing a connection: the multi-channel navigation dynamic simulation source system simulation control computer and each GNC test device respectively establish a connection with the dual network card computer via a multicast address; S2, initialization: the multi-channel navigation dynamic simulation source system simulation control computer is initialized, and during the initialization process, the receiving orbit starting point sent by the GNC test equipment is received; After initialization, it starts the simulation automatically and receives the point data transmitted by the GNC test equipment in real time; S3, data reception: After the connection is established, the multi-channel navigation dynamic simulation source system simulation control computer receives the user point data sent by the GNC test equipment at a set frequency; the multi-channel navigation dynamic simulation source system simulation control computer then sends the user point data to the simulation source at the same frequency at a fixed time; S4, simulation extrapolation and stop: When the multi-channel navigation dynamic simulation source system simulation control computer determines that the GNC no longer sends data, it performs orbit extrapolation according to the simulation source simulation information until it receives the instruction to stop the simulation and stops the simulation.

3. The method according to claim 2, characterized in that In step S2, the track starting point is transmitted to the simulation source by the GNC test equipment in the form of a configuration file before the initialization operation.

4. The method according to claim 2 or 3, characterized in that In step S3, the GNC test device sends user point data at a frequency of 1 packet / 100ms.

5. The method according to claim 2, characterized in that In step S3, since the information packet sending cycle and the simulation cycle are not completely synchronized, the multi-channel navigation dynamic simulation source system sets a cache area, and accesses the point data in the cache area to ensure that the multi-channel navigation dynamic simulation source system performs data fitting and simulation calculations at a predetermined frequency.

6. The method according to claim 5, characterized in that In step S4, when the multi-channel navigation dynamic simulation source system simulation control computer detects that the number of point data in the buffer area is less than the set number, it is considered that the GNC will no longer send data.

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