Space-based gravitational wave detector spacecraft formation dynamics simulation system

Abstract

The application relates to the field of aerospace technology, and particularly discloses a space gravitational wave detection spacecraft formation dynamics simulation system, which comprises a model input module used for inputting a spacecraft shell and a test mass; a perturbation force calculation module used for calculating multiple perturbation forces respectively acting on the spacecraft shell and the test mass; and a parallel coupling numerical integration module used for carrying out orbit-spin coupling dynamics parallel numerical integration on the spacecraft shell and the test mass based on the perturbation forces, so as to synchronize the orbit motion and the attitude motion of the spacecraft shell and the test mass; wherein the perturbation forces comprise coupling perturbations between the spacecraft shell and the test mass; the coupling perturbations at least comprise electromagnetic coupling perturbations. The application integrates multiple complex perturbation forces and a brand-new numerical integration format, and guarantees high-precision long-time simulation calculation on the spacecraft and the test mass.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to a space gravitational wave detection spacecraft formation dynamics simulation system. Background Technology

[0002] The basic principle of space-based gravitational wave detection is to form an equilateral triangle formation of three spacecraft and measure the distance changes between them caused by gravitational waves using Michelson laser interferometry. However, due to the multi-source perturbations affecting spacecraft during their operation in space, the stability of the space gravitational wave formation configuration is highly susceptible to disruption. Current research is insufficient on issues such as assessing the impact of multi-source perturbations on spacecraft in the space environment, analyzing the instability mechanisms of the formation configuration, developing techniques for reconstructing instability in the formation configuration, and designing the initial formation configuration.

[0003] GMAT is NASA's open-source space mission analysis software, primarily used for orbit design, navigation, and control system simulation. GMAT employs a modular, object-oriented C++ architecture, supporting visual modeling and execution. It includes models for several perturbations, such as solar and planetary gravitational models (with built-in ephemeris), non-spherical gravitational fields, Earth's atmospheric drag, solar radiation pressure, spacecraft finite thrust, and relativistic effect corrections. For numerical integration methods, it provides various fixed-step / variable-step high-order Runge-Kutta integration methods.

[0004] However, the GMAT software cannot fully meet the numerical simulation requirements for spacecraft formations used in space gravitational wave detection. The platform only provides numerical integration methods for orbits and does not offer integration methods for orbit-rotation coupling dynamics under external torque. In space gravitational wave detection missions, the relative / absolute attitude information of the spacecraft and the test mass is extremely important for the success and accuracy of the detection, and the multi-source perturbation environment in which the spacecraft operates can potentially cause rotation of both the spacecraft and the test mass.

[0005] Various problems exist in the orbit integration schemes proposed by various institutions for detectors, mainly including the failure to consider orbit-self-selection coupling, or the oversimplification of the physical model and the incomplete consideration of perturbation forces. Summary of the Invention

[0006] To address the aforementioned problems, the purpose of this invention is to provide a space gravitational wave detection spacecraft formation dynamics simulation system. This system aims to offer a numerical simulation platform capable of parallel calculation of spacecraft and verification mass orbit-spin coupling dynamics integrals. It allows for the selection of different perturbation models for different mission scenarios, employing more precise and efficient numerical methods to achieve orbit-spin extrapolation numerical calculations for space gravitational wave detection spacecraft formations on a 10-year timescale.

[0007] This invention provides a spacecraft formation dynamics simulation system for space gravitational wave detection, comprising: The model input module is used to input the spacecraft shell and inspection quality; The perturbation force calculation module is used to calculate various perturbation forces acting on the spacecraft shell and the test mass, respectively. A parallel coupled numerical integration module is used to perform parallel numerical integration of orbit-spin coupled dynamics on the spacecraft shell and the test mass based on the perturbation force, so as to synchronize the orbital motion and attitude motion of the spacecraft shell and the test mass; wherein, the perturbation force includes the coupled perturbation between the spacecraft shell and the test mass; the coupled perturbation includes at least electromagnetic coupling perturbation.

[0008] In one possible implementation, the perturbation force also includes two-body gravity; The perturbation calculation module uses the polyhedral method to calculate the two-body gravitational force and gravitational torque between the spacecraft shell and the test mass.

[0009] In one possible implementation, the perturbation force also includes solar radiation pressure; The perturbation force calculation module calculates solar pressure using the surface element method based on the spacecraft shell and inspection mass, in order to obtain the solar pressure perturbation force and perturbation torque acting on the spacecraft shell.

[0010] In one possible implementation, the perturbation force further includes perturbation force from a non-spherical gravitational field and / or perturbation force from a spatial electromagnetic field; The space electromagnetic field includes the solar magnetic field and planetary magnetic fields.

[0011] In one possible implementation, the space gravitational wave detection spacecraft formation dynamics simulation system is configured with different perturbation dynamic calculation models for different space gravitational wave detection mission scenarios; The scenarios described include spacecraft formations operating in heliocentric orbits, geocentric orbits, Sun-Earth Lagrange point orbits, or Earth-Moon Lagrange point orbits.

[0012] In one possible implementation, the calculation of the electromagnetic coupling perturbation between the spacecraft shell and the test mass includes at least one of the following models: classical stiffness and driving force model, patch effect and stray potential model, and accumulated charge and Lorentz force model.

[0013] In one possible implementation, the parallel coupled numerical integration module employs a symplectic integration algorithm; the symplectic integration algorithm can incorporate non-conservative perturbation forces.

[0014] In one possible implementation, the dynamic equations upon which the parallel numerical integration of the orbit-spin coupled dynamics is based include 13-dimensional state variables; the state variables include: 3-dimensional position, 3-dimensional velocity, 4-dimensional attitude quaternion, and 3-dimensional angular velocity.

[0015] In one possible implementation, the parallel coupled numerical integration module further includes coupled dynamic equations of orbital motion and attitude motion variables to perform synchronous numerical integration of the state of the spacecraft shell and the test mass.

[0016] In one possible implementation, the input module supports input of geometric model files in STL format.

[0017] This invention provides a spacecraft formation dynamics simulation system for space gravitational wave detection. Developed for mission scenarios involving space gravitational wave detector formations, the system supports decadal-scale numerical simulations of orbit-rotation coupling dynamics. It incorporates various complex perturbations and a novel numerical integration scheme to ensure high-precision, long-term simulation calculations for both spacecraft and testing quality. Attached Figure Description

[0018] Figure 1 A schematic diagram of a spacecraft formation dynamics simulation system for space gravitational wave detection provided for embodiments of the present invention; Figure 2 A schematic diagram of a simplified model of a spacecraft outer shell provided in an embodiment of the present invention; Figure 3 A schematic diagram of a simplified inspection quality model provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the optical physical model of a spacecraft surface element provided in an embodiment of the present invention. Detailed Implementation

[0019] The embodiments of the present invention will be further described in detail below with reference to the accompanying drawings and examples. The following detailed description of the embodiments and the accompanying drawings are used to illustrate the principles of the present invention by way of example, but should not be used to limit the scope of the present invention. That is, the present invention is not limited to the described preferred embodiments, and the scope of the present invention is defined by the claims.

[0020] In the description of this invention, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance; those skilled in the art can understand the specific meaning of the above terms in this invention as appropriate.

[0021] Space-based gravitational wave detection missions rely on ultra-stable formations of three spacecraft spanning millions of kilometers, using laser interferometry to measure minute distance changes (on the order of picometers) caused by gravitational waves. This places near-extreme numerical simulation demands on the stability of the formation configuration over a decade-long mission cycle. Existing general-purpose space mission analysis tools, such as NASA's open-source platform GMAT (General Mission Analysis Tool), are primarily designed for traditional orbital dynamics problems. When applied to the high-precision scenario of space-based gravitational wave detection, they suffer from three fundamental limitations: First, they lack the ability to model and integrate the dynamics of orbital and attitude coupling. In gravitational wave detection, the attitude changes of the spacecraft's outer shell and its internally suspended test mass are strongly coupled with orbital motion, directly affecting the accuracy of drag-free control and interferometric measurement results. GMAT only provides integration of the six-dimensional orbital state variables. Second, its perturbation model library fails to cover the complex close-range coupling perturbations between the spacecraft and its internal test mass. The test mass's free-fall state within the spacecraft cavity is fundamental to the detection. However, in addition to gravity, complex electromagnetic interactions (such as electrostatic forces and stray magnetic forces) exist between the two. These minute forces are not negligible in the gravitational wave frequency band, and GMAT does not provide such models. Third, its architecture is not designed for multi-rigid-body parallel co-simulation. The spacecraft shell and the test mass are two independent yet interacting dynamic objects, requiring synchronous and coupled solutions to their motion states, which GMAT's single-object integration framework cannot directly support.

[0022] The core concept of this invention lies in addressing the aforementioned shortcomings by conducting in-depth secondary development based on the modular architecture of GMAT to construct a dedicated, high-fidelity dynamics simulation system. The innovative integration of this system is reflected in: 1) the introduction of an orbit-spin coupled dynamics model describing 13-dimensional full-state variables (position, velocity, attitude, angular velocity), unifying the description of translation and rotation; 2) the establishment of a refined multiphysics perturbation model library, particularly enhancing spacecraft-test mass coupled perturbation models (such as two-body gravity and electromagnetic coupling) and high-precision external environment models (such as analytical surface element photopressure); 3) the design of a solver supporting parallel coupled numerical integration, capable of simultaneously and efficiently solving the coupled motion equations of multiple interacting rigid bodies, and employing a symplectic integral algorithm suitable for long-term simulations. This system aims to achieve high-precision numerical simulations of space gravitational wave detection formations from orbit to attitude, and from the spacecraft shell to the internal test mass, over a timescale of up to ten years, providing an indispensable tool for mission design, stability analysis, error assessment, and control law verification.

[0023] Combination Figure 1 This invention provides a spacecraft formation dynamics simulation system for space gravitational wave detection, comprising: The model input module is used to input the spacecraft shell and inspection quality; In one possible implementation, the detector system consists of a spacecraft shell and a test mass. Since detector system designs vary across agencies, the input module supports STL format geometric model files to accommodate different missions and detector configurations. This input geometric model will be used in calculations to perform full two-body gravitational and solar radiation pressure perturbations.

[0024] In one example, the system can provide, for example, Figure 2 and Figure 3 The simplified default model shown is for quick start-up. The output of this module forms the geometric basis for all subsequent accurate calculations of perturbations.

[0025] Furthermore, this module also allows users to specify physical property parameters for different parts of the model, such as the optical properties (absorption rate, reflectivity), mass characteristics, electromagnetic parameters, etc. of the surface material, which will serve as inputs for perturbation calculations.

[0026] Spacecraft Formation Configurations for Gravitational Wave Detection: Currently, most missions employ a formation of three spacecraft in an equilateral triangle, though the specific positions within the formation vary. The US LISA mission and China's Taiji mission use a heliocentric orbit centered on the Sun, while China's Tianqin project uses a geocentric orbit. Other formation configurations include those at the Sun-Earth Lagrange point and the Earth-Moon Lagrange point. This invention will consider these mission scenarios uniformly, employing different perturbation dynamic calculation models for different scenarios.

[0027] The gravitational wave detector formation consists of three spacecraft, each containing two small metallic blocks called test masses. This design aims to create a completely weightless detection environment, isolated from the effects of multiple perturbations in outer space. The spacecraft's outer shell protects the test masses from external perturbations (solar wind, solar radiation pressure, etc.), while the test masses are responsible for detecting gravitational waves through interferometry.

[0028] The perturbation force calculation module is used to calculate various perturbation forces acting on the spacecraft shell and the test mass, respectively. In one possible implementation, the perturbation includes the coupled perturbation between the spacecraft shell and the test mass and the perturbation of the external environment; Among them, coupling perturbation includes at least electromagnetic coupling perturbation and two-body gravity; The calculation of electromagnetic coupling perturbation between the spacecraft shell and the test mass includes at least one of the following models: classical stiffness and driving force model, patch effect and stray potential model, and accumulated charge and Lorentz force model.

[0029] The perturbation calculation module uses the polyhedral method to calculate the two-body gravitational force and gravitational moment between the spacecraft shell and the test mass. The two-body gravitational force and gravitational moment will be used for orbital-rotational coupling dynamics calculations between the spacecraft and the test mass.

[0030] Among them, external environmental perturbations include at least solar radiation pressure, non-spherical gravitational field perturbation force, and / or space electromagnetic field perturbation force; the space electromagnetic field includes the solar magnetic field and planetary magnetic fields.

[0031] The perturbation force calculation module uses the surface element method to calculate solar pressure based on the spacecraft shell and inspection mass, in order to obtain the solar pressure perturbation force and perturbation torque acting on the spacecraft shell.

[0032] Specifically, the perturbation dynamics calculation module first divides the discrete surface of the spacecraft into countless tiny surface elements, and then independently calculates the light pressure effect on each surface element.

[0033] When sunlight strikes a surface element of the spacecraft, the angle of incidence is... The unit vector of the incident light direction is The unit normal vector of the surface element is n. According to the optical physical properties of the surface, the incident light energy will be decomposed into three parts according to the law of conservation of energy: absorption, specular reflection, and diffuse reflection.

[0034] Let the first The area of ​​each facet is Absorption rate The specular reflectance is The diffuse reflectance is The following relation is satisfied: .

[0035] Absorption component: The thrust generated by the complete absorption of incident light by the surface element is P is the light pressure intensity coefficient. Specular reflection component: The thrust generated by a surface element reflecting light like a mirror is .

[0036] Diffuse reflection component: The thrust generated by a surface element uniformly scattering light in all directions (following Lambert's cosine law) is... .

[0037] By superimposing these three vector components, the total photopressure on the surface element can be obtained. Integrating and summing over all surface elements yields the total photopressure vector and total torque acting on the spacecraft's outer shell. This refined calculation method based on physical optics properties can significantly improve the calculation accuracy of solar photopressure perturbations under complex lighting conditions (such as entering and exiting Earth's shadow, and during solar eclipses), providing a more accurate external excitation source for subsequent orbit-rotation coupled dynamic integration.

[0038] For the gravity of certain celestial bodies, point mass cannot be used for calculations at close range; instead, spherical and non-spherical gravitational fields must be considered. The choice of gravity model here depends on the mission scenario.

[0039] Space electromagnetic fields take into account the magnetic fields of the sun and planets, that is, the effects of solar wind and charged particles in space on the outer shell of spacecraft.

[0040] In one possible implementation, the space gravitational wave detection spacecraft formation dynamics simulation system is configured with different perturbation dynamics calculation models for different space gravitational wave detection mission scenarios; wherein, the scenarios include spacecraft formations operating in heliocentric orbit, geocentric orbit, Sun-Earth Lagrange point orbit, or Earth-Moon Lagrange point orbit.

[0041] In a preferred embodiment, the perturbation calculation module is managed in a plug-in manner. Users can enable or disable specific perturbation models and set their parameter priorities according to specific task scenarios (such as heliocentric orbit, geocentric orbit), thereby achieving a flexible trade-off between simulation accuracy and computational efficiency.

[0042] The parallel coupled numerical integration module is used to perform parallel numerical integration of orbit-spin coupled dynamics on the spacecraft shell and the test mass based on perturbation forces, so as to synchronize the orbital motion and attitude motion of the spacecraft shell and the test mass. The parallel coupled numerical integration module receives force / torque data from the perturbation calculation module and performs numerical integration in parallel on the equations of motion of the two independent dynamic objects, the spacecraft shell and the test mass.

[0043] In one possible implementation, the dynamic equations upon which the parallel numerical integration of orbit-spin coupled dynamics is based include 13-dimensional state variables: 3-dimensional position, 3-dimensional velocity, 4-dimensional attitude quaternion, and 3-dimensional angular velocity. Its motion follows the orbit-spin coupled dynamic equations, which simultaneously encompass orbital translation and attitude rotation, and these two influence each other through perturbations (especially coupled perturbations).

[0044] In one possible implementation, the parallel coupled numerical integration module also includes coupled dynamic equations for orbital motion and attitude motion variables to simultaneously numerically integrate the state of the spacecraft shell and the test mass.

[0045] In one possible implementation, the Runge-Kutta (RK) method is a commonly used integration approach. However, due to the complexity of the perturbations of the spacecraft and test mass in this invention, the Runge-Kutta method may not necessarily offer advantages in computational efficiency and accuracy, and may also suffer from numerical divergence. Symplectic integral algorithms have significant advantages in long-step, long-duration numerical simulations and can be incorporated into this numerical simulation platform as a method to improve computational efficiency.

[0046] In this invention, the parallel coupled numerical integration module employs a symplectic integral algorithm, which can incorporate non-conservative perturbations. Combined with parallel accelerated computation, this improves the efficiency of numerical integration, achieving numerical simulation capabilities at the 10-year level. This invention uses a symplectic integral algorithm or its variants that can incorporate non-conservative forces (such as light pressure and damping), ensuring the stability and energy characteristics of long-term numerical calculations, and further enhancing efficiency through parallel computing technology.

[0047] Among them, parallel coupling has two aspects: First, the simulation tasks of multiple spacecraft (usually 3) and their internal inspection quality can be computed in parallel; second, within a single spacecraft unit, the solution of the dynamic equations of the outer shell and the inspection quality is synchronously advanced and mutually coupled in the data flow, that is, in each integration step, the states of each other and the coupling perturbations they are subjected to will interact in real time.

[0048] This invention is adaptable to various mission scenarios. By configuring the model activation set and parameters in the perturbation dynamics calculation module, it can support simulations for different space gravitational wave detection missions, such as: Heliocentric orbit schemes (such as LISA and the Taiji Program) mainly consider solar gravity, interplanetary space environment, and coupling perturbations between and within spacecraft.

[0049] Geocentric orbit schemes (such as the Tianqin Project): It is necessary to focus on the near-Earth environmental effects such as the Earth's non-spherical gravity, the Earth's magnetic field, and the Earth's shadow.

[0050] Lagrange point orbit scheme (Sun-Earth L-point, Earth-Moon L-point): requires complex multibody gravitational field modeling and dynamic characteristics of the corresponding points.

[0051] In one example, using this invention, the calculation error of spacecraft orbital perturbation acceleration within the space gravitational wave detection frequency range is ≤10. 15 m / s²; the single-step calculation error of the orbit under multi-source perturbation conditions is no greater than the picometer level, and the extrapolation calculation error of the orbit over a 10-year ultra-long time period is no greater than 500 meters.

[0052] The space gravitational wave detection spacecraft formation dynamics simulation system provided by this invention can reduce the calculation error of spacecraft orbital perturbation acceleration within the space gravitational wave detection frequency range, the single-step calculation error of orbit under multi-source perturbation conditions, and the calculation error of orbit extrapolation over a 10-year ultra-long time period.

[0053] This invention can also reveal the stability conditions and error propagation mechanisms of equilateral triangular formations under conditions of multiple perturbation sources and uncertainties, laying a simulation foundation for subsequent research on configuration optimization and formation control methods. Currently, domestic theoretical research and data accumulation on space perturbation factors mainly focus on near-Earth orbit environments, while research on the multi-body gravitational field, space thermal radiation, and cosmic electromagnetic coupling environment faced by deep space orbits is still in its early stages. This project aims to study the generation mechanism of multi-source perturbations and coupling effects in space, and establish a high-fidelity multiphysics model to provide reference support for subsequent deep space orbit design and deep space environment research.

[0054] The above are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

[0055] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. The embodiments of the present invention are described with reference to flowchart illustrations and / or block diagrams of methods, terminal devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing terminal device to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing terminal device, generate instructions for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 The computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing terminal device to operate in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1The functions specified in one or more boxes. These computer program instructions may also be loaded onto a computer or other programmable data processing terminal equipment to cause a series of operational steps to be performed on the computer or other programmable terminal equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable terminal equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the functions specified in one or more boxes. Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of the embodiments of the invention. Finally, it should be noted that in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or terminal device that includes said element.

[0056] The methods and apparatus provided by the present invention have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of the present invention. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

[0057] In the description of this specification, references to terms such as "an embodiment," "some embodiments," "example," "specific example," or "a specific embodiment" or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0058] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions 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 this application.

Claims

1. A space gravitational wave explorer spacecraft formation dynamics simulation system, characterized by, include: The model input module is used to input the spacecraft shell and inspection quality; The perturbation force calculation module is used to calculate various perturbation forces acting on the spacecraft shell and the test mass, respectively. A parallel coupled numerical integration module is used to perform parallel numerical integration of orbit-spin coupled dynamics on the spacecraft shell and the test mass based on the perturbation force, so as to synchronize the orbital motion and attitude motion of the spacecraft shell and the test mass; wherein, the perturbation force includes the coupled perturbation between the spacecraft shell and the test mass; the coupled perturbation includes at least electromagnetic coupling perturbation.

2. The system for simulating the dynamics of a formation of space-based gravitational wave detectors of claim 1, wherein, The perturbation force also includes two-body gravity; The perturbation calculation module uses the polyhedral method to calculate the two-body gravitational force and gravitational torque between the spacecraft shell and the test mass.

3. The space gravitational wave detection spacecraft formation dynamics simulation system according to claim 1, characterized in that, The perturbation force also includes solar radiation pressure; The perturbation force calculation module calculates solar pressure using the surface element method based on the spacecraft shell and inspection mass, in order to obtain the solar pressure perturbation force and perturbation torque acting on the spacecraft shell.

4. The space gravitational wave detector spacecraft formation dynamics simulation system of claim 1, wherein, The perturbation force also includes the perturbation force of non-spherical gravitational field and / or the perturbation force of spatial electromagnetic field; The space electromagnetic field includes the solar magnetic field and planetary magnetic fields.

5. The space gravitational wave detector spacecraft formation dynamics simulation system of claim 1, wherein, The space gravitational wave detection spacecraft formation dynamics simulation system is configured with different perturbation dynamic calculation models for different space gravitational wave detection mission scenarios; The scenarios described include spacecraft formations operating in heliocentric orbits, geocentric orbits, Sun-Earth Lagrange point orbits, or Earth-Moon Lagrange point orbits.

6. The space gravitational wave detector spacecraft formation dynamics simulation system of claim 1, wherein, The calculation of the electromagnetic coupling perturbation between the spacecraft shell and the test mass includes at least one of the following models: classical stiffness and driving force model, patch effect and stray potential model, and accumulated charge and Lorentz force model.

7. The system of claim 1, wherein, The parallel coupled numerical integration module uses a symplectic integration algorithm; the symplectic integration algorithm can incorporate non-conservative perturbation forces.

8. The space gravitational wave detector spacecraft formation dynamics simulation system of claim 1, wherein, The dynamic equations upon which the parallel numerical integration of the orbit-spin coupled dynamics is based include 13-dimensional state variables; these state variables include: 3-dimensional position, 3-dimensional velocity, 4-dimensional attitude quaternion, and 3-dimensional angular velocity.

9. The space gravitational wave detector spacecraft formation dynamics simulation system of claim 1, wherein, The parallel coupled numerical integration module also includes coupled dynamic equations for orbital motion and attitude motion variables to perform synchronous numerical integration of the state of the spacecraft shell and the test mass.

10. The space gravitational wave detector spacecraft formation dynamics simulation system of claim 1, wherein, The input module supports input of STL format geometric model files.

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