Numerical simulation integrated demonstration system and method for space array telescope system

Abstract

The present invention relates to a numerical simulation integrated demonstration system and method for a space array telescope system, the system comprising a basic support unit (1), a physical engine unit (2), a system function unit (3) and a user interaction unit (4), wherein the physical engine unit (2), the system function unit (3) and the user interaction unit (4) can communicate and exchange data with the basic support unit (1). The present invention has the characteristics of good compatibility, strong expansibility, high flexibility and the like.

Description

Technical Field

[0001] The invention relates to a numerical simulation integrated demonstration scheme for a space vehicle system, in particular to a numerical simulation integrated demonstration system and method for a space array telescope system. Background Art

[0002] The search and research of stars and planets other than the sun has always been a hot topic in astronomy. As a new generation of telescope configuration, array telescopes can achieve high-resolution astronomical observations while meeting the needs of searching for habitable planets outside our solar system, providing a revolutionary new way to detect solar system objects, stars, galaxies, and black holes, and realizing the cross-generation of telescope systems.

[0003] Array telescopes are complex space systems that integrate multiple disciplines, requiring mutual coupling and integration between disciplines. In addition to being directly related to the performance of scientific payload equipment, their observation performance indicators are also closely related to the control accuracy of the spacecraft platform, payload control accuracy, structural micro-vibration, actuator interference, sensor error, and environmental interference. Due to the precision of measurement, the space array telescope system places extremely high demands on the design, manufacturing, and control accuracy of the platform and payload. Therefore, it is particularly important to have the ability to accurately evaluate the overall performance of the system during the design phase.

[0004] The existing numerical simulation integrated demonstration system for space telescopes for single satellites cannot meet the requirements of typical mission scenarios of array telescopes (multi-target, extended target, etc.), nor can it be used for the demonstration, verification and evaluation of array telescope mission plans. Therefore, it is of great significance to establish an array telescope simulation integrated demonstration system for space array telescopes that takes into account both the real-time performance and calculation accuracy requirements of the system and is suitable for a variety of observation targets and observation modes. Summary of the invention

[0005] The object of the present invention is to provide a numerical simulation integrated demonstration system and method for a space array telescope system.

[0006] To achieve the above-mentioned objectives, the present invention provides a numerical simulation integrated demonstration system and method for a space array telescope system. The system includes a basic support unit, a physical engine unit, a system function unit and a user interaction unit. The physical engine unit, the system function unit and the user interaction unit can all communicate and exchange data with the basic support unit.

[0007] According to one aspect of the present invention, the basic support unit comprises:

[0008] A script generation module for associating a text-based system description module to a system modeling module based on a system modeling language;

[0009] Task scheduling module, including bus simulation program;

[0010] The parallel computing resource scheduling module is used to receive and execute instructions from the task scheduling module;

[0011] The data storage module includes a database, a data file import and export module, and a format conversion module.

[0012] According to one aspect of the present invention, the system modeling module is used for task requirement analysis, structural analysis and behavior description, and serves as a benchmark for system operation;

[0013] The bus simulation program is used as a common controller, responsible for processing the state synchronization of each aircraft, and uses the socket as the main interface to make corresponding application programming interfaces for the server and client, and respectively establish server and client programs for the time synchronization and posture synchronization of each aircraft;

[0014] The parallel computing resource scheduling module is used to allocate parallel computing resources and execute, archive, restore, and terminate the computing process according to the instructions of the task scheduling module;

[0015] The data storage module stores, obtains and queries the calculated data based on the database.

[0016] According to one aspect of the present invention, the physical engine unit is used for modeling and simulation of a space array telescope, including:

[0017] Observation simulators, including target source simulators and observation configuration simulators;

[0018] Space environment simulators, including dynamic simulators, thermal environment simulators, optical environment simulators and space radiation environment simulators;

[0019] Array telescope system simulator, including platform control simulator, thermal-mechanical coupling finite element simulator, active optical control simulator, interference process optical simulator and fringe tracking control simulator.

[0020] According to one aspect of the present invention, the target source simulator is used to provide characteristics of the observed target;

[0021] The observation configuration simulator is used as the input of the current observation task, which is directly input by the user or obtained by real-time optimization of the control algorithm according to the target source characteristics and the current state of the system, and is used as the state input of the array telescope system simulator;

[0022] The dynamics simulator is used to perform dynamics simulation on celestial bodies, provide the dynamic conditions of the aircraft at a specific time, and provide dynamics environment input for the array telescope system simulator;

[0023] The thermal environment simulator is used to simulate the thermal environment impact of the aircraft during the mission and provide thermodynamic environment input for the array telescope system simulator;

[0024] The optical environment simulator is used as an input for evaluating the stray light effect and the effective observation time during the observation process;

[0025] The space radiation environment simulator is used to evaluate the impact of the space radiation environment on the spacecraft;

[0026] The platform control simulator includes a whole-device attitude sensor, an inter-device relative distance sensor and a control actuator;

[0027] The mechanical-thermal coupling finite element simulator is used to perform mechanical-thermal coupling finite element modeling simulation using the dynamics simulator and the thermal environment simulator under different orbital and formation configuration conditions and control actuator actuation information as input;

[0028] The active optical control simulator is used to simulate the control of the active optical part of the load based on the surface input of each component of the mechanical and thermal coupling finite element simulator and the overall posture of the platform control simulator, and output the active optical control result and state;

[0029] The interference process optical simulator is used to simulate the interference process according to different formation configurations and optical system status information, and output interference measurement results;

[0030] The fringe tracking control simulator is used to calculate the phase delay and group delay for each set of interference baselines, and the optical path difference controller is used to calculate the correction signal required by the actuator and to stabilize the fringes.

[0031] According to one aspect of the present invention, the system functional unit comprises:

[0032] Light-collecting detector simulators, including light-collecting detector platform simulators and light-collecting detector payload simulators;

[0033] A beam-combining detector simulator, including a beam-combining detector platform simulator and a beam-combining detector payload simulator.

[0034] According to one aspect of the present invention, the light collecting detector platform simulator is used for simulation of structure and mechanism, thermal control, control, on-board energy and information management;

[0035] The light collecting detector payload simulator is used for simulating the light collecting optical system, beam adaption system and focal plane, simulating the collection of target light for direct focusing imaging, and forwarding it to the beam combiner through beam adaptation;

[0036] The beam combining detector payload simulator is used for simulating the beam combining optical system and the focal plane detector assembly, simulating the beam combiner to receive the light beam forwarded by the light collector, and performing sampling and quantitative detection using a photoelectric detector on the pupil plane or the focal plane.

[0037] According to one aspect of the present invention, the user interaction unit is used to implement task scene rendering and animation output as well as user interaction based on virtual reality technology, and includes a real-time visualization module and a high-precision rendering module.

[0038] According to one aspect of the present invention, the real-time visualization module is used to perform simulation at the task level, including simulation of the operating status of each device at each stage of the task profile, and is used to send control instructions to each device for simulated observation and attitude adjustment during the system simulation stage;

[0039] The high-precision rendering module is used to use rendering software to render the task with high precision based on the aircraft and space scene model, and output images and videos.

[0040] A numerical simulation integrated demonstration method for a space array telescope system comprises the following steps:

[0041] a. Analyze the input model established based on the system modeling language using the basic support unit, generate a domain-specific language, and provide it as input to the physical engine unit;

[0042] b. Using the analytical model as input, the physical engine unit is used to perform observation simulation of the space array telescope, space environment simulation, and system simulation;

[0043] c. Use a distributed architecture that is the same as the array telescope system to simulate and demonstrate the system's functional units and reflect the interaction between the subsystems;

[0044] d. Based on the user interaction unit, task scene rendering and animation output as well as user interaction based on VR technology are realized.

[0045] According to the concept of the present invention, a numerical simulation integrated demonstration system of a space array telescope system is proposed, which is composed of numerical simulation software and hardware. The concept of the numerical simulation system is formed based on the system of the model, and the system architecture and core component design are designed around the numerical simulation system. Through the construction and mutual cooperation of the basic support unit, the physical engine unit, the system function unit and the user interaction unit, the integrated demonstration of the numerical simulation of the array telescope system suitable for a variety of observation targets and compatible with a variety of observation modes can be realized according to different task requirements, and it has many advantages such as good compatibility, strong scalability and high flexibility. In addition, facing the needs of task scenarios, it can allow users to participate in the design and optimization of observation plans in an interactive manner in advance while significantly improving the degree of integration of the plan, and significantly improve the task planning ability and operation efficiency in the task operation stage, taking into account the needs of the system real-time and calculation accuracy, so that the real-time performance is high and the scalability is strong. It can also be used as a numerical simulation integrated demonstration system with strong versatility to drive task scenario demonstrations, as well as to carry out solution verification and evaluation. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 is a diagram schematically showing a structure of a numerical simulation integrated demonstration system for a space array telescope system according to an embodiment of the present invention;

[0047] Figure 2 is a flowchart schematically showing a simulation task workflow according to an embodiment of the present invention;

[0048] Figure 3 is a diagram schematically showing the relationship between modules in an array telescope system simulator according to an embodiment of the present invention;

[0049] Figure 4 It is a schematic diagram showing the working process of the collector and combiner of the simulation platform according to one embodiment of the present invention. DETAILED DESCRIPTION

[0050] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0051] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

[0052] See also Figure 1 and Figure 2The numerical simulation integrated demonstration system of the space array telescope system of the present invention is implemented according to the model-view-controller (MVC) framework and can be used for the research on the design of the space array telescope system for exoplanet detection. The system includes a basic support unit 1, a physical engine unit 2, a system function unit 3 and a user interaction unit 4. The physical engine unit 2, the system function unit 3 and the user interaction unit 4 can communicate and exchange data with the basic support unit 1.

[0053] In the present invention, the basic support unit 1 includes a script generation module 11, a task scheduling module 12, a parallel computing resource scheduling module 13 and a data storage module 14. The script generation module 11 is used to associate the text-based system description module 111 with the system modeling module 112 based on the System Modeling Language (SysML), wherein the system modeling module 112 is used for task requirement analysis, structure analysis and behavior description, and serves as a benchmark for the operation of this (modeling and simulation) system.

[0054] The task scheduling module 12 is responsible for scheduling the entire system, including a bus simulation program 121, which is used as a common controller and is responsible for processing the state synchronization of each aircraft. It uses the socket as the main interface, and makes corresponding application programming interfaces (APIs) for the server (device) end 122 and the client 123, and respectively establishes the server 122 and client 123 programs for the time synchronization and posture synchronization of each device. Among them, time synchronization provides simulation of time services, including methods such as obtaining time and resetting time; formation posture provides registration and query services for parameters such as spacecraft attitude quaternions and angular velocity, including position coordinates, center of mass velocity and other information; platform posture provides registration and query services for attitude quaternions and angular velocity of the platform that affect the direction of the main optical axis, including position coordinates, center of mass velocity and center of mass acceleration and other information.

[0055] The parallel computing resource scheduling module 13 is used to receive instructions from the task scheduling module 12 and is responsible for the allocation of specific parallel computing resources (such as Figure 1 No. 131) and the execution, archiving, recovery, and termination of the calculation process (such as Figure 1 The data storage module 14 includes a database 141, a data file import and export module 142, and a format conversion module 143. The data storage module 14 relies on the database 141 to perform operations such as storage, acquisition, and query of high-throughput computing data.

[0056] In the present invention, the physical engine unit 2 is used for modeling and simulation of space array telescopes, including an observation simulator 21, a space environment simulator 22, an array telescope system simulator 23, etc. The observation simulator 21 includes a target source simulator 211 and an observation configuration simulator 212. Among them, the target source simulator 211 is used to provide the characteristics of the observation target, including the time and space distribution characteristics of the target point source, extended source, and multiple sources, spectrum, polarization and other multi-dimensional information; the observation configuration simulator 212 is used as the input of the current observation task (such as observation parameters such as baseline configuration), which can be directly input by the user, or it can be obtained by real-time optimization by the control algorithm according to the target source characteristics and the current state of the system, and used as the state input of the subsequent array telescope system simulator 23. The observation target can be various celestial bodies such as exohabitable planets, solar system bodies, protoplanetary disks, and active galactic nuclei. Taking the simulation of an extrasolar planet as an observation object as an example, the star-planet system part includes its distance from the earth, system composition, planetary orbit parameters, etc., the star simulation parameters include its equivalent temperature, star metallicity, star surface gravity, etc., and the planet simulation parameters include planetary mass, radius, temperature profile, atmospheric composition, etc., and a forward radiation transfer model is established to simulate the image, spectrum and other information observed by observers in the solar system. Based on the extrasolar planet system information simulated by the target source simulator 211, the observation configuration simulator 212 simulates its observation efficiency by changing the observation baseline arrangement configuration (relative distance and angle of each instrument), continuous or discrete observation sampling methods, etc., and determines the optimal observation configuration and sampling method.

[0057] The space environment simulator 22 includes a dynamics simulator 221, a thermal environment simulator 222, an optical environment simulator 223, and a space radiation environment simulator 224. The dynamics simulator 221 is used to perform dynamics simulation on celestial bodies (sun, earth, moon, giant planets, etc.) in the solar system, provide the perturbation force of the spacecraft at a specific time, and provide dynamics environment input for the array telescope system simulator 23. The solar system planetary ephemeris can be generated by calling an existing toolkit (such as As tropy package in Python), and the geocentric equatorial inertial coordinate system of the generated position needs to be converted to the daily equatorial inertial coordinate system. Some calculation results can also be cached in advance to perform interpolation as needed and avoid the influence of boundary values. At the same time, this part also includes a module for realizing the dynamics calculation of the object, that is, analyzing the field force on the object when it moves along a given orbit, and calculating the external force required to be applied along the orbit, as well as analyzing the field force on the object and the given external force (as the output of the control algorithm), and calculating its dynamic state evolution and orbit. Taking the astronomical observation mission near the sun-earth collinear libration point orbit as an example, it is necessary to construct a high-precision mechanical model of the interplanetary orbit near the operating orbit in the solar system's center of mass coordinate system, and on this basis, give the relative motion equation of the probe to evaluate the influence of various perturbations on the relative motion, providing a basis for the selection of force models for probe orbit simulation in subsequent work.

[0058] The thermal environment simulator 222 is used to simulate the main thermal environment influences on the aircraft during the mission, including flux distribution models of solar radiation, earth infrared radiation, and earth reflection, etc., to provide thermodynamic environment input for the array telescope system simulator 23.

[0059] The optical environment simulator 223 includes models of the brightness and spectrum of celestial bodies inside and outside the solar system and the skylight background, which are used as inputs for evaluating the stray light effect and effective observation time during the observation process. Since the distance between stars and the earth is generally on the order of light years, the stellar radiation source can be simplified to a point source when modeling. Based on star catalogs such as Hipparcos and Gaia, and using spectral template technology, a point source radiation model of the optical band (ultraviolet, visible light to infrared) is established to simulate the stellar point source background seen by detectors in any direction and field of view, and to determine whether the star enters the observation field of view according to the collective position relationship between the celestial body and the telescope.

[0060] The space radiation environment simulator 224 includes environmental parameters of space radiation sources such as solar cosmic rays and galactic cosmic rays, as well as radiation effect models such as total dose and single particle of the spacecraft, which are used to evaluate the impact of the space radiation environment on the spacecraft.

[0061] The array telescope system simulator 23 includes a platform control simulator 231, a force-heat coupling finite element simulator 232, an active optical control simulator 233, an interference process optical simulator 234, and a fringe tracking control simulator 235. In order to be compatible with a variety of system design schemes, the interface design of the optical simulation system modeling is based on the specific implementation method of decoupling the functional units of each subsystem. Its structure and interface relationship are as follows: Figure 3 As shown, it is compatible with various forms such as geometric optics simulation based on ray tracing software and physical optics simulation written in programming languages ​​such as Python and C++.

[0062] Among them, the platform control simulator 231 includes measurement modules such as whole-device attitude sensors (such as star sensors, inertial sensors, position and angle sensors, etc.), inter-device relative distance sensors (such as inter-device radio communication, navigation cameras, laser ranging, etc.), and control actuators (such as control moment gyroscopes, thrusters, momentum wheels, etc.), which are used to complete the simulation of these modules. In order to achieve the purpose of distributed interferometry, it is necessary to realize the functions of inter-device capture, autonomous adjustment, and beam combination through precise control of the optical path difference between each device. Therefore, in terms of orbit and formation configuration, it is necessary to use simulation programs to perform the following analysis: examine the dynamic environment of each device and simulate its orbit to put forward requirements for the control algorithm, such as control frequency, control strategy, etc.; simulate the motion status of each device after applying control to determine whether the control algorithm can meet the design requirements and evaluate the advantages and disadvantages of the control algorithm; frame the cost of the flight mission to provide quantitative tools for demonstrating the feasibility of the mission and constrain the design of orbital maneuvers.

[0063] The force-heat coupling finite element simulator 232 is used to use the dynamics simulator 221 and the thermal environment simulator 222 in different orbits and formation configuration conditions and the control actuator actuation information as input to perform force-heat coupling finite element modeling and simulation, including modeling and simulation of parameters such as the non-uniformity of the external environment immersion temperature and the temperature gradient, and output the surface state of each device. Compared with the single exposure integration time, the time scale of the change of spatial force and thermal environment is longer, so this part is independent of the single, time-containing light interference observation simulation and only serves as the input of its optical system.

[0064] The active optical control simulator 233 is used to simulate the control of the active optical part of the payload based on the surface input of each device of the mechanical and thermal coupling finite element simulator 232 and the overall posture information of the platform control simulator 231, and output the active optical control results and other states. Different from the single-aperture optical telescope, the distributed optical interference system in space is affected by pointing errors and platform vibrations, and there are various movable components such as delay lines, swing mirrors, deformable mirrors, and fiber stretchers. Its interference imaging process is dynamic.

[0065] The interference process optical simulator 234 is used to simulate the interference process according to different formation configurations and optical system status information, and output interference measurement results.

[0066] The fringe tracking control simulator 235 is used to calculate the phase delay and group delay for each set of interference baselines, calculate the correction signal required by the actuator using the optical path difference controller, and host the state machine to switch between the following operations: fringe search, center fringe group delay tracking, phase tracking, etc., for stabilizing the fringe. The fringe tracking control simulator 235 also analyzes the actual optical path difference residual and the instructions of the actuator and performs high-frequency parameter updates.

[0067] In the present invention, each device function is divided into two parts: a front display screen and a backend model. Specifically, the system function unit 3 is divided into a light-collecting detector simulator 31 and a beam-combining detector simulator 32 according to the type of aircraft. The light-collecting detector simulator 31 includes a light-collecting detector platform simulator 311 and a light-collecting detector payload simulator 312. Among them, the light-collecting detector platform simulator 311 is used for the simulation of the structure and mechanism, thermal control, control, on-board energy and information management, etc.; the light-collecting detector payload simulator 312 is used for the simulation of components such as the light-collecting optical system, beam adaptation system and focal plane, which can simulate the collection of target light for direct focusing imaging, and forwarding to the beam combiner through beam adaptation. The beam-combining detector simulator 32 includes a beam-combining detector platform simulator 321 and a beam-combining detector payload simulator 322. Among them, the beam combining detector platform simulator 321 is similar to the light collecting detector platform simulator 311, so it will not be repeated; the beam combining detector payload simulator 322 is used for the simulation of the beam combining optical system and the focal (or pupil) plane detector assembly, which can simulate the process of the beam combiner receiving the light beam forwarded by the light collector and using the photodetector to perform sampling and quantitative detection on the pupil plane or focal plane. The external command and data input information of the two devices simulated by the light collecting detector simulator 31 and the beam combining detector simulator 32 include temperature and temperature control targets, fringe tracking status, optical path difference detection results and control targets, high-precision pointing results of the main optical axis, active optical status, photodetector data, refrigerator working status, command execution status and results; external command and data output information includes commands (power on and off, working mode), attitude data packets, inter-satellite relative position, inertial system position determination and other positioning, navigation, timing data packets, payload installation platform status data (position sensor and angle sensor data), etc.

[0068] In the present invention, the user interaction unit 4 is used to realize the functions of mission scene rendering and animation output and user interaction based on virtual reality technology (VR), including a real-time visualization module 41 for simulation using real data and a high-precision rendering module 42 for highlighting the overall mission process from the mission process. Among them, the real-time visualization module 41 is used to perform simulation at the mission level, including the simulation of the operating status of each device at each stage of the mission profile, and is used to send control instructions to each device in the system simulation stage to simulate observation, attitude adjustment and other scheduling operations; the high-precision rendering module 42 is used to use rendering software to render the mission with high precision based on the aircraft and space scene model, and output images and videos and other results.

[0069] like Figure 4As shown, the simulation platform light collector panel can request its own position, posture and other parameters through instructions, and the background server sends the corresponding information, and calculates the relevant physical quantities according to the information sent back and updates the display; similarly, the simulation platform beam combiner panel calculates optical parameters according to the information sent back by the requested background server, and then requests the background server to calculate the optical imaging process. The background server schedules the corresponding imaging calculation simulation or calls the relevant database and sends the imaging calculation results, which are transmitted to the beam combiner panel for updating the display. In the demonstration scenario with high requirements for system real-time performance, the background server can pre-store the simulation data obtained by running the physical engine and store it in the data storage module 14, and directly read and display it when running system functions and user interaction processes.

[0070] The numerical simulation integrated demonstration method of the space array telescope system of the present invention first uses the basic support unit 1 to parse the input model established based on the system modeling language, generates a domain-specific language (DSL), and provides it as input to the physical engine unit 2. In addition, the basic support unit 1 also provides various supports for the operation of the demonstration system. Then, using the above-mentioned parsed model as input, the physical engine unit 2 is used to perform observation simulation, space environment simulation and system simulation of the space array telescope. Then, a distributed architecture that is isomorphic to the array telescope system is adopted to perform simulation demonstration of the system functional units, and reflect the interactive relationship between the subsystems. Finally, based on the user interaction unit 4, task scene rendering and animation output (including real-time rendering quality, movie-level rendering quality) and user interaction based on VR technology are realized.

[0071] In summary, the various units of the present invention cooperate with each other, take into account the requirements of system real-time performance and calculation accuracy for different task requirements, and have high real-time performance and strong scalability. The end-to-end modeling and simulation method of the array telescope adopted by the present invention is applicable to various observation targets, can describe dynamic systems, and has strong scalability. The system simulation platform built based on this modeling and simulation method is compatible with the simulation of multiple observation modes, and is applicable to scenes at all stages of the mission. It can be used as a highly versatile and scalable array telescope modeling and simulation system, which can be used for formation control and collaborative observation of multiple aircraft.

[0072] The above description is only an embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A numerical simulation integrated demonstration system for a space array telescope system, characterized in that: It comprises a basic support unit (1), a physical engine unit (2), a system function unit (3) and a user interaction unit (4), wherein the physical engine unit (2), the system function unit (3) and the user interaction unit (4) can communicate and exchange data with the basic support unit (1); The basic support unit (1) comprises: A script generation module (11) for associating a text-based system description module (111) with a system modeling module (112) based on a system modeling language; A task scheduling module (12), including a bus simulation program (121); A parallel computing resource scheduling module (13), used for receiving and executing instructions from the task scheduling module (12); A data storage module (14), comprising a database (141), a data file import and export module (142) and a format conversion module (143); The system modeling module (112) is used for task requirement analysis, structural analysis and behavior description, and serves as a benchmark for system operation; The bus simulation program (121) is used as a common controller, responsible for processing the state synchronization of each aircraft, and uses the socket as the main interface to make corresponding application programming interfaces for the server (122) and the client (123), and respectively establish the server (122) and client (123) programs for the time synchronization and posture synchronization of each aircraft; The parallel computing resource scheduling module (13) is used to allocate parallel computing resources and execute, archive, restore and terminate the computing process according to the instructions of the task scheduling module (12); The data storage module (14) stores, obtains and queries the calculated data based on the database (141); The physical engine unit (2) is used for modeling and simulating a space array telescope, and comprises: An observation simulator (21), comprising a target source simulator (211) and an observation configuration simulator (212); A space environment simulator (22), including a dynamics simulator (221), a thermal environment simulator (222), an optical environment simulator (223) and a space radiation environment simulator (224); An array telescope system simulator (23), including a platform control simulator (231), a force-thermal coupling finite element simulator (232), an active optical control simulator (233), an interference process optical simulator (234) and a fringe tracking control simulator (235); The target source simulator (211) is used to provide characteristics of the observed target; The observation configuration simulator (212) is used as an input of the current observation task, which is directly input by a user or obtained by real-time optimization of a control algorithm according to target source characteristics and a current state of the system, and is used as a state input of the array telescope system simulator (23); The dynamics simulator (221) is used to perform dynamics simulation on a celestial body, provide the dynamic conditions of the aircraft at a specific time, and provide dynamics environment input for the array telescope system simulator (23); The thermal environment simulator (222) is used to simulate the thermal environment impact of the aircraft during the mission and provide thermodynamic environment input for the array telescope system simulator (23); The optical environment simulator (223) is used as an input for evaluating the stray light effect and effective observation time during the observation process; The space radiation environment simulator (224) is used to evaluate the impact of the space radiation environment on the space vehicle; The platform control simulator (231) comprises a whole-device attitude sensor, an inter-device relative distance sensor and a control actuator; The mechanical-thermal coupling finite element simulator (232) is used to use the dynamics simulator (221) and the thermal environment simulator (222) as inputs to perform mechanical-thermal coupling finite element modeling simulation under different orbital and formation configuration conditions and control actuator actuation information; The active optical control simulator (233) is used to simulate the control of the active optical part of the load based on the surface input of each component of the mechanical and thermal coupling finite element simulator (232) and the overall position and posture of the platform control simulator (231), and output the active optical control result and state; The interference process optical simulator (234) is used to simulate the interference process according to different formation configurations and optical system state information, and output interference measurement results; The fringe tracking control simulator (235) is used to calculate the phase delay and group delay for each set of interference baselines, and to calculate the correction signal required by the actuator using the optical path difference controller and to stabilize the fringe.

2. The system according to claim 1, characterized in that The system functional unit (3) includes: A light collecting detector simulator (31), comprising a light collecting detector platform simulator (311) and a light collecting detector payload simulator (312); A beam-combining detector simulator (32) comprises a beam-combining detector platform simulator (321) and a beam-combining detector payload simulator (322).

3. The system according to claim 1, characterized in that The user interaction unit (4) is used to realize task scene rendering and animation output as well as user interaction based on virtual reality technology, and comprises a real-time visualization module (41) and a high-precision rendering module (42).

4. The system according to claim 3, characterized in that The real-time visualization module (41) is used to perform simulation at the task level, including simulation of the operating status of each device at each stage of the task profile, and is used to send control instructions to each device to perform simulated observation and attitude adjustment during the system simulation stage; The high-precision rendering module (42) is used to render the task with high precision using rendering software based on the aircraft and space scene model, and output images and videos.

5. A demonstration method using the numerical simulation integrated demonstration system of the space array telescope system according to any one of claims 1 to 4, comprising the following steps: a. Utilizing the basic support unit (1) to parse the input model established based on the system modeling language, generate a domain-specific language, and provide it as input to the physical engine unit (2); b. Using the analytical model as input, the physical engine unit (2) performs observation simulation of the space array telescope, space environment simulation, and system simulation; c. Using a distributed architecture that is the same as the array telescope system to simulate and demonstrate the system functional unit (3), and reflect the interaction between the subsystems; d. Based on the user interaction unit (4), task scene rendering and animation output as well as user interaction based on VR technology are realized.

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