Simulation verification method for small-thrust orbital transfer strategy of all-electric propulsion satellite platform

Abstract

The invention discloses a simulation verification method for a small-thrust orbital transfer strategy of an all-electric propulsion satellite platform, and relates to the technical field of spacecraft orbit control and simulation. In order to solve the defect that a technical means for realizing high-precision simulation and verification of a small-thrust orbital transfer strategy of an all-electric propulsion satellite is lacked on the premise of comprehensively considering multi-perturbation influence in the prior art, the technical scheme provided by the invention comprises the following steps: acquiring a preset input model, inputting six orbital elements, thruster parameters and orbital transfer strategies of the satellites; based on a preset input model, an orbital transfer stage is judged, and an orbital transfer strategy is generated; acquiring a preset orbit dynamics model, calculating a thrust vector according to an orbit transfer strategy, and updating orbit parameters and mass consumption of the satellite; a preset attitude control model is collected, the attitude quaternion of the current satellite is solved, and whether the satellite attitude is stable or not is judged according to the solving result. The method is suitable for design and verification work of a small-thrust long-period orbital transfer strategy of an all-electric propulsion satellite platform.

Description

Technical Field

[0001] The invention relates to the field of spacecraft orbit control and simulation technology, and specifically to the simulation verification of the low-thrust orbit change strategy of the all-electric propulsion satellite platform. Background Art

[0002] In recent years, all-electric propulsion technology has gained wide attention in spacecraft propulsion systems, especially in the field of geosynchronous orbit (GEO) satellites. Compared with traditional chemical propulsion systems, all-electric propulsion systems have greatly improved propulsion efficiency through high specific impulse propulsion technologies such as ion electric propulsion or Hall electric propulsion, thereby reducing the total launch mass and development cost of satellites. The core advantage of this technology is that it can significantly reduce the amount of propellant carried, thereby significantly improving the payload ratio. For example, Boeing Satellite Systems, Orbital Sciences Corporation and Space Systems Loral have successfully developed all-electric propulsion satellite platforms, which are widely used in communication satellites and navigation satellites. Germany's OHB company has also conducted in-depth research in this field and launched a commercial satellite platform based on all-electric propulsion technology.

[0003] Compared with international advanced technologies, my country is also accelerating the application and development of all-electric propulsion technology. Relevant research focuses on ion electric propulsion systems, Hall thruster optimization design, and efficient orbit transfer strategies, and has made significant progress. However, satellite platforms based on all-electric propulsion technology usually have the characteristics of small thrust, long orbit change time, and a large number of flight circles, which makes its orbit change strategy more complicated than that of chemical propulsion systems. In specific applications, satellites need to go through a long-period orbit change process from geosynchronous transfer orbit (GTO) to GEO orbit, and are also affected by multiple factors such as atmospheric drag, the earth's non-spherical gravitational field, solar radiation pressure, and gravitational perturbations of the moon and the sun. Therefore, the precise design and verification of the orbit change strategy has become a key technical problem.

[0004] In existing research, there are some methods for orbit change strategies for limited thrust satellites, such as classic orbital dynamics modeling and thruster design, but they mainly focus on short-period chemical propulsion orbit change processes. For all-electric propulsion satellite platforms, existing methods cannot fully adapt to their long-period, multi-stage, multi-perturbation complex orbit change processes. For example:

[0005] Limitations of strategy design: It is difficult for existing methods to systematically optimize the direction control and size distribution of the thrust vector in multiple orbit change stages, resulting in low orbit change efficiency.

[0006] Insufficient simulation accuracy: There is still much room for improvement in high-precision long-period simulation technology, especially in the comprehensive modeling and processing of multiple perturbation factors.

[0007] Attitude control coupling problem: The attitude control coupling between the thruster operating state and orbital dynamics has not yet formed a complete solution, which may affect the stability of orbit change.

[0008] The above problems not only limit the further application of all-electric propulsion technology, but also increase the complexity and uncertainty of orbit transfer.

[0009] Therefore, how to achieve high-precision simulation and verification of the low-thrust orbit change strategy of all-electric propulsion satellites under the premise of comprehensively considering the influence of multiple perturbations has become a technical problem that needs to be solved urgently in this field. Summary of the invention

[0010] In order to solve the problem existing in the prior art, the prior art lacks technical means for realizing high-precision simulation and verification of low-thrust orbit change strategy of all-electric propulsion satellite under the premise of comprehensively considering the influence of multiple perturbations, the technical solution provided by the present invention is as follows:

[0011] A simulation method for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, comprising:

[0012] The steps of collecting the preset input model and inputting the six orbital numbers, thruster parameters and orbit change strategy of the satellite;

[0013] Based on the preset input model, a step of determining the track change stage and generating a track change strategy;

[0014] A step of collecting a preset orbital dynamics model, calculating a thrust vector according to the orbit change strategy, and updating the orbital parameters and mass consumption of the satellite;

[0015] The steps of collecting a preset attitude control model, solving the attitude quaternion of the current satellite, and judging whether the satellite attitude is stable according to the solution result.

[0016] Furthermore, a preferred embodiment is provided, wherein the orbital dynamics model updates the orbital parameters of the satellite by combining the thrust vector, the current position and velocity of the satellite through an orbital recursive model.

[0017] Furthermore, a preferred embodiment is provided, wherein the orbital dynamics model calculates the propellant mass consumption based on the thrust magnitude and specific impulse of the satellite.

[0018] Furthermore, a preferred embodiment is provided, wherein the attitude control model solves the attitude quaternion in the orbital coordinate system and converts it into an attitude quaternion in the inertial coordinate system.

[0019] Based on the same inventive concept, the present invention also provides a simulation verification device for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, comprising:

[0020] A module that collects preset input models and inputs the satellite's six orbital numbers, thruster parameters, and orbit change strategies;

[0021] A module for determining the track change stage and generating a track change strategy based on the preset input model;

[0022] A module for collecting a preset orbital dynamics model, calculating a thrust vector according to the orbit change strategy, and updating the orbital parameters and mass consumption of the satellite;

[0023] A module that collects the preset attitude control model, solves the attitude quaternion of the current satellite, and determines whether the satellite attitude is stable based on the solution result.

[0024] Based on the same inventive concept, the present invention also provides a simulation verification method for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, comprising:

[0025] The simulation results of the simulation method are outputted, and the simulation accuracy is verified by multi-perturbation factor modeling.

[0026] Based on the same inventive concept, the present invention also provides a simulation verification device for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, comprising:

[0027] A module that outputs the simulation results of the simulation method and verifies the simulation accuracy through multi-perturbation factor modeling.

[0028] Based on the same inventive concept, the present invention also provides a computer storage medium for storing a computer program. When the computer program is read by a computer, the computer executes the described method.

[0029] Based on the same inventive concept, the present invention also provides a computer, including a processor and a storage medium. When the processor reads a computer program stored in the storage medium, the computer executes the method described.

[0030] Based on the same inventive concept, the present invention also provides a computer program product, which is a computer program. When the computer program is executed, the method described above is implemented.

[0031] Compared with the prior art, the technical solution provided by the present invention is beneficial in that:

[0032] The low-thrust orbit change input model of the all-electric propulsion satellite platform realizes the comprehensive input of orbit parameters, thruster parameters and orbit change strategies, so that the simulation process can accurately reflect the actual mission requirements. In existing methods, the input model is often unable to refine the switch state and working parameters of the thruster, but provides more accurate strategy input, which significantly improves the credibility and adaptability of the simulation model.

[0033] Through the low-thrust orbit change strategy interpretation model, the current orbit change stage can be automatically determined and the corresponding instructions can be pushed according to the six orbit numbers and propulsion stage judgment conditions. Compared with the existing fixed strategy model, this dynamic interpretation model optimizes the orbit change efficiency by adjusting the thrust direction and size in real time, especially in long-term, multi-stage orbit changes.

[0034] The orbital dynamics model adopts a high-precision thrust vector calculation method, incorporates orbital perturbation factors into the model, and realizes accurate calculation of thrust direction, orbital parameters and mass changes. Compared with the problem of insufficient modeling of multiple perturbation factors in existing research, the accuracy of long-term orbit change simulation results is significantly improved, and the simulation error is better than 1‰, which has higher application value in actual satellite orbit change missions.

[0035] The attitude control model effectively avoids the trajectory change error caused by attitude instability by accurately calculating the stable attitude quaternion of the satellite platform when the thrusters are ignited and turned off. In existing methods, attitude control and thrust calculation are usually performed independently, while this method achieves the coupled optimization of the two, ensuring the high consistency of thrust direction and attitude control.

[0036] The strategy interpretation model, orbital dynamics model and attitude control model are integrated into a complete simulation framework and embedded in the SpaceSim simulation software. Through the visual display module, not only can the orbit change process be presented intuitively, but also high-precision orbit six-element comparison data can be output, which is highly consistent with the real satellite telemetry data. Compared with the scattered single simulation tools, this integrated design improves user operation convenience and system efficiency and reduces the complexity of mission planning.

[0037] During the simulation, the thruster status was judged by combining the historical thruster switch status and the real-time sun exposure, and the energy efficiency of the thruster was optimized. Existing studies usually have a low time resolution for thruster status control, but achieve more sophisticated energy management, thereby further improving the economy and feasibility of the orbit change process.

[0038] It is suitable for the design and verification of low-thrust and long-period orbit change strategies for all-electric propulsion satellite platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 It is a flow chart of a simulation verification method for a low-thrust orbit change strategy of an all-electric propulsion satellite platform;

[0040] Figure 2 The comparison results of the six orbital elements in the orbit change process, among which (a) is the comparison result of the semi-major axis, (b) is the comparison result of the eccentricity, (c) is the comparison result of the orbit inclination, (d) is the comparison result of the right ascension of the ascending node, (e) is the comparison result of the argument of perigee, and (f) is the comparison result of the mean anomaly;

[0041] Figure 3 It is a schematic diagram for setting orbital parameters of satellite platform;

[0042] Figure 4 This is a schematic diagram of thruster parameter settings;

[0043] Figure 5 Set up a schematic diagram for the track change strategy;

[0044] Figure 6 for Figure 1 Schematic diagram of the implementation in SpaceSim software;

[0045] Figure 7 A schematic diagram showing the visualization of the simulation process;

[0046] Figure 8 This is a schematic diagram of the output of the simulation results. DETAILED DESCRIPTION

[0047] In order to make the advantages and benefits of the technical solution provided by the present invention more clearly reflected, the technical solution provided by the present invention is now further described in detail with reference to the accompanying drawings, specifically:

[0048] Implementation method 1: This implementation method provides a simulation method for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, including:

[0049] The steps of collecting the preset input model and inputting the six orbital numbers, thruster parameters and orbit change strategy of the satellite;

[0050] Based on the preset input model, a step of determining the track change stage and generating a track change strategy;

[0051] A step of collecting a preset orbital dynamics model, calculating a thrust vector according to the orbit change strategy, and updating the orbital parameters and mass consumption of the satellite;

[0052] The steps of collecting a preset attitude control model, solving the attitude quaternion of the current satellite, and judging whether the satellite attitude is stable according to the solution result.

[0053] Implementation method 2. This implementation method is a further limitation of the simulation method of the low-thrust orbit change strategy of an all-electric propulsion satellite platform provided in implementation method 1. The orbital dynamics model updates the orbital parameters of the satellite through an orbital recursive model combined with the thrust vector, the current position and speed of the satellite.

[0054] Implementation method three: This implementation method further limits the simulation method of the low-thrust orbit change strategy of an all-electric propulsion satellite platform provided in implementation method one. The orbital dynamics model calculates the propellant mass consumption based on the thrust size and specific impulse of the satellite.

[0055] Implementation method 4. This implementation method is a further limitation of the simulation method of the low-thrust orbit change strategy of an all-electric propulsion satellite platform provided in implementation method 1. The attitude control model solves the attitude quaternion in the orbital coordinate system and converts it into the attitude quaternion in the inertial coordinate system.

[0056] Embodiment 5: This embodiment provides a simulation verification device for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, including:

[0057] A module that collects preset input models and inputs the satellite's six orbital numbers, thruster parameters, and orbit change strategies;

[0058] A module for determining the track change stage and generating a track change strategy based on the preset input model;

[0059] A module for collecting a preset orbital dynamics model, calculating a thrust vector according to the orbit change strategy, and updating the orbital parameters and mass consumption of the satellite;

[0060] A module that collects the preset attitude control model, solves the attitude quaternion of the current satellite, and determines whether the satellite attitude is stable based on the solution result.

[0061] Embodiment 6: This embodiment provides a simulation verification method for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, including:

[0062] The simulation results of the simulation method provided in the first implementation mode are output, and the simulation accuracy is verified by multi-perturbation factor modeling.

[0063] Specifically, they include:

[0064] Step 1: Construction of low-thrust orbit change input model for all-electric propulsion satellite platform

[0065] The orbital parameters, thruster parameters and orbit change strategy of the satellite platform are set by inputting the model to provide complete initial conditions for simulation verification.

[0066] Detailed description: Based on the visual human-computer interaction interface of the simulation software, the user inputs the six orbital parameters of the all-electric propulsion satellite platform (including semi-major axis, eccentricity, orbital inclination, right ascension of ascending node, argument of perigee and horizontal anomaly), the total mass of the satellite platform, and the dynamic model parameters. At the same time, set key parameters such as the number, thrust, and specific impulse of thrusters, and clarify the judgment conditions and participating thrusters of the propulsion phase in the orbit change strategy. In this step, all input data are verified by the software to ensure its integrity and rationality. After completing this step, a complete input model file is generated as the initial data source for the subsequent simulation process.

[0067] Step 2: Implementation of low-thrust orbit change strategy interpretation model

[0068] According to the input model and six orbital numbers, the current orbit change phase is interpreted in real time and the corresponding task execution instructions are generated.

[0069] Detailed description: The interpretation model is used to analyze the six elements of the satellite orbit to determine the current orbit change stage, including the in-orbit propulsion stage, the inclination adjustment stage, and the eccentricity adjustment stage. According to the stage characteristics, the mission execution instructions are generated and pushed to the orbital dynamics model and the attitude control model. At the same time, it is determined in real time whether the satellite is in the shadow area and the on / off status of the thrusters to ensure the energy efficiency of the thrusters. In the second and third stages of the orbit change, by calculating the latitude argument, it is determined whether the thrust direction needs to be changed, and the result is pushed to the orbital dynamics model. The output of this step is the mission instructions, thruster status, and thrust direction adjustment results at the current moment, which serve as the input of the orbital dynamics model.

[0070] Step 3: Construction and operation of orbital dynamics model

[0071] Based on mission instructions and thruster status, thrust vector calculation, orbit recursion and mass consumption solution are performed.

[0072] Detailed description: Receive the mission instructions and thruster on / off status pushed by the interpretation model, and calculate the thrust vector according to different orbit change stages. In the orbit propulsion stage, the thrust vector is along the velocity direction; in the inclination adjustment stage, the thrust vector is at a fixed angle with the orbital plane and contains a component along the velocity direction; in the eccentricity adjustment stage, the thrust vector is perpendicular to the eccentricity vector and has a fixed angle with the orbital plane. Through the high-precision orbit recursion model (HPOP), combined with the thrust vector, the current position and velocity of the satellite, the orbital parameters and mass consumption of the satellite at the next moment are calculated, and updated to the simulation system for use in subsequent steps.

[0073] Step 4: Establishment and application of attitude control model

[0074] Based on the mission instructions and thrust vector, the satellite's attitude quaternion is solved to ensure the accuracy of the thrust direction.

[0075] Detailed description: Receive the attitude control instructions of the interpretation model, solve the satellite's attitude quaternion in the orbital coordinate system according to different attitude control requirements, and further convert it into the attitude quaternion in the inertial coordinate system. When the thrusters are ignited, ensure that the satellite's attitude is consistent with the thrust direction; when the thrusters are turned off, maintain the stability of the satellite's attitude. Through this model, the thruster ignition and attitude adjustment form a closed-loop control to ensure the dynamic balance of the satellite during the orbit change process.

[0076] Step 5: Output and visualization of simulation results

[0077] Connect the simulation results to the visualization module to realize dynamic display and storage of data.

[0078] Detailed description: Based on the output results of the orbital dynamics model and attitude control model, simulation data is generated, including changes in the six orbital parameters, thruster status, thrust direction, and satellite attitude information. Through the visualization display module, users can dynamically observe the real-time changes in orbital parameters and satellite status during the orbit change process, and compare and verify with the actual telemetry data. The simulation data is stored in a specified format to support subsequent mission planning and data analysis.

[0079] Step 6: Full process verification and optimization

[0080] The entire process is verified based on simulation data, and the track change strategy is adjusted to optimize the results.

[0081] Detailed description: Analyze the changes in the six orbital numbers of the simulation results, compare the errors with the real telemetry data, and focus on evaluating the accuracy of thrust vector calculation and the stability of attitude control. For the stage with large errors, adjust the mission instruction generation logic and thrust direction control strategy in the interpretation model to optimize the orbit change efficiency and simulation accuracy. Verify that the optimized solution can be repeated until the expected effect is achieved.

[0082] Embodiment 7: This embodiment provides a simulation verification device for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, including:

[0083] A module that outputs the simulation results of the simulation method provided in the first implementation mode and verifies the simulation accuracy through multi-perturbation factor modeling.

[0084] Embodiment 8: This embodiment provides a computer storage medium for storing a computer program. When the computer program is read by a computer, the computer executes the method provided in embodiment 1.

[0085] Embodiment 9: This embodiment provides a computer, including a processor and a storage medium. When the processor reads a computer program stored in the storage medium, the computer executes the method provided in embodiment 1.

[0086] Embodiment 10: This embodiment provides a computer program product, which is a computer program. When the computer program is executed, the method provided in embodiment 1 is implemented.

[0087] Implementation Method XI: Combination Figure 1-6 This embodiment is described in detail by using specific examples to further describe the technical solution provided above. Specifically:

[0088] This implementation method includes a low-thrust orbit change input model for an all-electric propulsion satellite platform, a strategy interpretation model, an orbit dynamics model, and an attitude control model. The main implementation process is as follows:

[0089] 1. The low-thrust orbit change input model of the all-electric propulsion satellite platform is responsible for the platform parameters and strategy input, including:

[0090] 1) Input the six orbit numbers of the all-electric propulsion satellite platform, the total mass of the platform, and the platform dynamics model parameters;

[0091] 2) Input the thruster parameters of the all-electric propulsion satellite platform, including the number of thrusters, thrust and specific impulse of each thruster;

[0092] 3) Input the low-thrust orbit change strategy of the all-electric propulsion satellite platform, including the judgment conditions of the propulsion phase and the participating thrusters.

[0093] 2. The low-thrust orbit change strategy interpretation model of the all-electric propulsion satellite platform is responsible for strategy interpretation and command push, including:

[0094] 1) According to the six orbit numbers of the all-electric propulsion satellite platform and the judgment conditions of the propulsion stage, the orbit change stage of the all-electric propulsion satellite at the current moment is judged, which is divided into three stages: the first stage is propulsion within the orbital plane to raise the perigee; the second stage is the inference at a certain angle to the orbital plane, raising the orbital altitude and reducing the orbital inclination; the third stage is that the thrust is perpendicular to the eccentricity vector in the orbital plane and at a certain angle to the orbital plane, reducing the eccentricity and reducing the orbital inclination.

[0095] 2) According to different mission stages, build mission execution instructions and push them to the orbital dynamics model and attitude control model.

[0096] 3) Determine the exposure of the satellite platform to sunlight and whether the satellite platform is in the earth’s shadow.

[0097] 4) Based on the historical on / off status of the platform thrusters and the current exposure to sunlight, the on / off status of the thrusters at the current moment is determined, and the on / off status of the thrusters is pushed to the orbital dynamics model.

[0098] 5) During the second and third stages of orbit change, determine whether the thrust needs to change direction, provided that the amplitude angle is 90° or 270°, and push the judgment result to the orbital dynamics model.

[0099] 3. The orbital dynamics model of low-thrust orbit change of all-electric propulsion satellite platform is responsible for thrust calculation and orbit recursion, including:

[0100] 1) Receive the mission execution instructions, thruster on / off status and thrust direction conversion results from the interpreted model.

[0101] 2) According to the input parameters and strategies, the thrust vector in the J2000 inertial system (referred to as the inertial system) is solved. There are different solving processes according to different stages, which are specifically divided into:

[0102] A. Phase 1: The thrust vector is along the velocity direction.

[0103] The velocity vector of the satellite inertial system is solved according to the six elements of the satellite platform orbit, and the thrust direction is obtained after normalization. The thrust vector is obtained according to the thrust size of the thruster.

[0104] B. Second stage: The thrust vector makes a certain angle α with the orbital plane and moves along the velocity direction within the orbital plane.

[0105] The velocity vector in the satellite inertial system is solved according to the six elements of the satellite platform orbit and converted into the VVLH orbit coordinate system (orbital system for short), and the flight path angle β is solved. The thrust vector in the orbital system can be solved according to the flight path angle and the thrust vector angle:

[0106]

[0107] Where F is the thrust of the thruster. After converting to the inertial system, the thrust vector in the inertial system can be obtained.

[0108] C. The third stage: The thrust vector makes a certain angle α with the orbital plane and is perpendicular to the eccentricity vector in the orbital plane.

[0109] Solve the eccentricity unit vector of the satellite inertial system according to the six elements of the satellite platform orbit And convert it to the orbital coordinate system, thus obtaining the unit thrust component in the orbital plane

[0110]

[0111] In the formula, is the y-axis unit vector in the orbital system.

[0112] Thus, the thrust vector in the orbital system can be obtained:

[0113]

[0114] Where F is the thrust of the thruster, is the thrust component in the orbital plane under the orbital system, and should satisfy F orbit_y = 0. After converting to the inertial system, the thrust vector in the inertial system can be obtained.

[0115] 3) Solve the mass consumption Δm according to the thrust:

[0116]

[0117] 4) Based on the thrust vector in the inertial system, the current position, velocity and mass consumption of the satellite platform, the HPOP high-precision orbit recursion model is used to update the position, velocity and mass of the satellite platform.

[0118] 4. The low-thrust orbit change attitude control model of the all-electric propulsion satellite platform is responsible for attitude control during the orbit change process and solves the stable attitude quaternion of the satellite platform in the ignition or shutdown state. It mainly includes:

[0119] 1) Receive satellite attitude control instructions from the interpretation model.

[0120] 2) According to different attitude control instructions, calculate the attitude quaternion of the satellite platform in the orbital coordinate system.

[0121] 3) Based on the satellite platform attitude quaternion in the orbital system, solve the satellite platform attitude quaternion in the inertial system.

[0122] Based on the above process, the simulation process of the low-thrust orbit change strategy of the all-electric propulsion satellite platform is as follows: Figure 1 shown.

[0123] In the specific implementation work, this embodiment can achieve high-precision simulation of the small-thrust orbit change process of the all-electric propulsion platform with long period, multiple perturbations and complex strategies by inputting the specified orbit change strategy. Figure 2 It is the result of comparing the six orbital numbers of the simulation data of this implementation method with the telemetry data of the real satellite platform during the low-thrust orbit change process of the all-electric propulsion satellite platform under the same orbit change strategy.

[0124] As can be seen from the figure, the low-thrust orbit change process of the all-electric propulsion satellite platform achieved by this implementation method has extremely high accuracy. Compared with the actual telemetry data, during the one-day orbit change process, the simulation results are better than the actual telemetry results, and the simulation accuracy is better than 1‰, which can realize the low-thrust orbit change process of the all-electric propulsion satellite platform with high accuracy.

[0125] according to Figure 3-8 In the software simulation work, SpaceSim, a spacecraft system simulation software independently developed by Harbin Institute of Technology, is used for implementation. The implementation method is as follows:

[0126] Step 1: Based on the visual human-computer interaction interface of SpaceSim software, realize the satellite platform low-thrust orbit change input model, and set the satellite platform orbit parameters, thruster parameters and orbit change strategy through the visual human-computer interaction interface, such as Figure 3-5 shown.

[0127] Step 2: According to Figure 1As shown in the process, the strategy interpretation model, orbital dynamics model and attitude control model of the low-thrust orbit change strategy simulation method of the all-electric propulsion satellite platform are embedded in the SpaceSim software, as shown in Figure 6 shown.

[0128] Step 3: Connect the simulation results to the visualization display module and data storage module of the software to realize the visualization display and output of the simulation results, such as Figure 7 and 8 shown.

[0129] The technical solution provided by the present invention is further described in detail above through several specific implementation modes in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the several specific implementation modes described above are not intended to be used as limitations on the present invention. Any reasonable modification and improvement of the present invention, combination of implementation modes and equivalent substitution within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A simulation method for a low-thrust orbit change strategy for an all-electric propulsion satellite platform, characterized in that: include: The steps of collecting the preset input model and inputting the six orbital numbers, thruster parameters and orbit change strategy of the satellite; Based on the preset input model, a step of determining the track change stage and generating a track change strategy; The steps of collecting a preset orbital dynamics model, calculating a thrust vector according to the orbit change strategy, and updating the orbital parameters and mass consumption of the satellite; The steps of collecting a preset attitude control model, solving the attitude quaternion of the current satellite, and judging whether the satellite attitude is stable according to the solution result.

2. The simulation method of the low-thrust orbit change strategy of the all-electric propulsion satellite platform according to claim 1 is characterized in that: The orbital dynamics model updates the orbital parameters of the satellite by combining the thrust vector, the current position and the speed of the satellite through an orbital recursive model.

3. The simulation method of the low-thrust orbit change strategy of the all-electric propulsion satellite platform according to claim 1 is characterized in that: The orbital dynamics model calculates the propellant mass consumption according to the thrust magnitude and specific impulse of the satellite.

4. The simulation method of the low-thrust orbit change strategy of the all-electric propulsion satellite platform according to claim 1 is characterized in that: The attitude control model calculates the attitude quaternion in the orbital coordinate system and converts it into an attitude quaternion in the inertial coordinate system.

5. A simulation verification device for the low-thrust orbit change strategy of an all-electric propulsion satellite platform, characterized in that: include: A module that collects preset input models and inputs the satellite's six orbital numbers, thruster parameters, and orbit change strategies; A module for determining the track change stage and generating a track change strategy based on the preset input model; A module for collecting a preset orbital dynamics model, calculating a thrust vector according to the orbit change strategy, and updating the orbital parameters and mass consumption of the satellite; A module that collects the preset attitude control model, solves the attitude quaternion of the current satellite, and determines whether the satellite attitude is stable based on the solution result.

6. A simulation verification method for a low-thrust orbit change strategy of an all-electric propulsion satellite platform, characterized in that: include: The step of outputting the simulation results of the simulation method described in claim 1 and verifying the simulation accuracy through multi-perturbation factor modeling.

7. A simulation verification device for the low-thrust orbit change strategy of an all-electric propulsion satellite platform, characterized in that: include: A module for outputting the simulation results of the simulation method described in claim 1 and verifying the simulation accuracy through multi-perturbation factor modeling.

8. A computer storage medium for storing a computing program, characterized in that: When the computer program is read by a computer, the computer executes the method of claim 1 .

9. A computer, comprising a processor and a storage medium, characterized in that: When the processor reads the computer program stored in the storage medium, the computer executes the method of claim 1 .

10. A computer program product, being a computer program, characterized in that When the computer program is executed, the method of claim 1 is implemented.

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