Ground full-physical simulation test system for spacecraft attitude stability control under strong impact interference

Abstract

The invention discloses a ground full-physical simulation test system for spacecraft attitude stability control under strong impact interference, which uses a'heaven-earth equivalent analysis method 'to convert strong impact interference borne by a spacecraft space into an impulse moment form, and realizes equivalent simulation through the ground full-physical simulation test system. The ground full-physical simulation test system is high in strong impact interference ground equivalence, good in regulation and control performance, high in spacecraft space mechanical environment condition simulation degree, high in applicability, high in spacecraft attitude control precision and stability and easy to implement. The system can equivalently simulate the spatial strong impact interference, fully verify the effectiveness and correctness of the attitude control scheme under the strong impact interference, provide technical reference for the stable control of the spacecraft spatial attitude, reduce the spatial test cost, and improve the success rate of the spatial test.

Description

Technical Field

[0001] The present invention relates to a ground-based full-physics simulation test system for spacecraft attitude stabilization control under strong impact interference. The system targets the field of spacecraft attitude control and ground-based simulation tests, and particularly adopts a "ground-ground equivalent simulation method" to perform equivalent simulation of strong impact interference in spacecraft space. A ground-based full-physics simulation test system is designed for simulation testing and verification evaluation of spacecraft attitude stabilization control schemes. Background Art

[0002] Current theoretical research on space disturbances affecting spacecraft attitude stability can be categorized into technical areas such as disturbance source analysis, disturbance suppression, and attitude stabilization control algorithm design. Verification and analysis methods for theoretical research can be categorized into pure digital simulation, semi-physical simulation, and full-physical simulation testing. For disturbances with ideal and well-defined mathematical models, both theoretical analysis of spacecraft attitude stabilization control and verification through spacecraft space / ground simulation testing can yield relevant research results or achieve the desired simulation effects. However, strong impact disturbances experienced by spacecraft in space often exhibit complex characteristics such as unknown sources, brief impacts, and intense effects. These have a significant impact on the spacecraft's attitude, potentially leading to serious consequences such as center of mass shift, attitude instability, and even structural damage.

[0003] At present, theoretical analysis of strong impact disturbances is difficult, time-consuming and hard to verify effectively; the mathematical model for simulation verification of spacecraft attitude stability control under strong impact interference is unclear, the simulation test results are not ideal, and the correctness and rationality of the control scheme are difficult to verify and evaluate. Summary of the Invention

[0004] To address the issue of spacecraft attitude stabilization control under strong impact disturbances, this paper designs a ground-based, fully physical simulation test system for spacecraft attitude stabilization control under strong impact disturbances. This system features high ground equivalence and controllability for strong impact disturbances, a high degree of simulation of spacecraft aerodynamic conditions, strong applicability, and high precision and stability in spacecraft attitude control, all easily implemented. This system can effectively simulate strong impact disturbances in space, fully verifying the effectiveness and correctness of attitude control schemes under strong impact disturbances, providing a technical reference for spacecraft attitude stabilization control, reducing the cost of space experiments and increasing their success rate.

[0005] The technical solution of the present invention is: a ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact interference, including a single-axis air floating platform, an ejection simulator, a sensor, a calculation simulation module, a power supply and distribution module, and a data communication module;

[0006] The uniaxial air-floating platform includes an air-floating platform and an air-floating platform support column arranged at the center of the bottom of the air-floating platform. The air-floating platform is used to fix and install various experimental hardware and single units. The air-floating platform and the test hardware and single units with determined positions can be accurately leveled again using a center of mass tester with counterweights of different specifications, so that the center of mass of the air-floating platform is perpendicular to the rotation center of the uniaxial air-floating platform. The air-floating platform, counterweights, test hardware and single units are fixed to form an integrated test platform. The test platform floats due to pressurized gas, forming a microgravity and low-friction mechanical environment in the horizontal plane.

[0007] The ejection simulator adopts a modular design and is fixed to the side of the test platform through an adapter. The mass block of the ejection simulator has no secondary contact with the test platform after ejection, and the ejection direction does not pass through the rotation center of the test platform.

[0008] The sensor uses a combination of an optical encoder angle measuring device and a fiber optic gyroscope. The rotation angle of the test platform is measured by the optical encoder angle measuring device and then transmitted to the ground front-end computer. The fiber optic gyroscope on the test platform can measure the angular velocity of the current air-floating platform in real time, remove the angular velocity of the earth's rotation, and transmit it to the ground front-end computer.

[0009] The test platform uses a propulsion simulator and a flywheel actuator to control torque distribution output. The propulsion simulator consists of a nozzle, a solenoid valve, and a compressed gas cylinder, and uses pulse modulation technology to output torque. The flywheel adopts a speed control mode, removes friction interference torque through an internal closed loop, and outputs accurate and stable reaction torque.

[0010] The computing simulation module is composed of an industrial computer, a PXI system and a ground front-end computer.

[0011] Furthermore, the ejection simulator includes a mechanical device and a control system;

[0012] The mechanical device includes a slide rail, a launch tube, and an ejection mass block. The ejection mass block is placed in the launch tube. One end of the launch tube is engraved with a thread. By rotating a handle connected to the thread, an elastic force is applied to the spring in the launch tube, which further acts on the ejection mass block. An electromagnetic lock is installed at the other end of the launch tube, which is controlled by a relay of the control system to open and close the cover at the other end of the launch tube.

[0013] When simulating an ejection process, the cover must first be opened, and after placing the ejection mass inside the launch tube, the electromagnetic lock must be controlled to close the cover. Secondly, the handle must be rotated to compress the spring until sufficient elastic potential energy is generated. Finally, the electromagnetic lock must be controlled to open the cover, and the ejection mass must gain sufficient kinetic energy to be ejected from the launch tube.

[0014] The lower base of the launch tube is installed on a movable slide rail. By adjusting the position of the launch tube on the slide rail, the center of mass offset is changed to form impulse moments of different sizes and directions, thereby realizing adjustable strong impact simulation levels.

[0015] Furthermore, the optical code disc is installed on the bottom surface of the test platform, and the angle measuring device corresponding to the optical code disc is installed on the support column of the air-floating platform, so that the optical code disc and the corresponding angle measuring device are physically isolated.

[0016] Furthermore, the industrial computer loads and runs the xPC Target real-time system, and the system writes the Matlab / Simulink spacecraft attitude control program.

[0017] Furthermore, the PXI system includes a chassis, a controller and a board module, and is a measurement and testing system that integrates software and hardware.

[0018] Furthermore, the front-end computer runs Matlab / Simulink, LabView and SQL server database software, and provides a graphical human-computer interaction interface.

[0019] Furthermore, the power supply and distribution module uses a combination of a mobile power supply and a voltage regulator. The mobile power supply not only guarantees the rated capacity and output power, but also has simple and fast charging and discharging, making it suitable for use on a table. The voltage regulator provides multiple voltage outputs, and the output voltage is adjustable, stable and reliable.

[0020] Furthermore, the data communication module adopts a combination of cables, optical fibers, network cables and wireless routers; wherein, the PXI system realizes data transmission and reception between the fiber optic gyroscope, flywheel and propulsion simulator solenoid valve through the board card and the matching cable; the industrial computer realizes high-speed, low-latency data communication with the PXI system through the optical fiber direct connection to the optical fiber reflective memory board card; the industrial computer and the PXI system are directly connected to the wireless router through the network cable, and are wirelessly connected to the front-end computer under the table to realize data forwarding and storage within the same network.

[0021] The beneficial effects of the present invention are:

[0022] (1) Using the "ground-space equivalent analysis method", the strong impact interference to the spacecraft in space is specifically expressed as an impulse rectangle, and an equivalent simulation is achieved through a ground-based full-physics simulation test system. The sources of strong impact interference in space include but are not limited to spacecraft mechanism separation, space-based launch, foreign object collision, rendezvous and docking, and many other forms. The ground-based full-physics simulation test system assumes the strong impact interference input as the reaction torque of the platform ejection, and does not care about the specific magnitude of the interference torque and the duration of the action. It only analyzes the impulse torque generated by the test platform due to the strong impact. This method has a wide coverage of strong impact interference in space, strong practicality, simple and clear test principles, strong equivalence of test conditions, low test costs, and greater ground feasibility.

[0023] (2) A "launch simulator" was used to complete the input of strong impact interference. By adjusting the ejection speed and eccentricity of the ejection mass block, the impulse moment was kept constant, and the strong impact interference was controllable. Impulse moment = ejection speed × eccentricity. When the impulse moment is constant, increasing the eccentricity will reduce the ejection speed requirement accordingly. During ground testing, the position of the ejection simulator on the slide rail can be adjusted to increase or decrease the eccentricity, thereby reducing the ejection speed. Compared with the actual strong impact effect, the intensity is reduced and the danger is reduced. The ejection simulator adopts a modular design with a simple mechanical structure, convenient control and adjustment, clear ejection principle, reduced ejection danger, and strong compatibility with the air flotation test platform.

[0024] (3) Using the "microgravity, low friction" characteristics of a single-axis air flotation platform to simulate the spacecraft's space mechanics environment, the full physical ground test system hardware and unit components, test equipment, and methods are provided. The test air flotation platform has rich interfaces, strong load-bearing capacity, and strong scalability. Later, components such as sails, antennas, or tanks can be added to further analyze and verify the effects of interference such as flexibility and liquid sloshing on the stability control of the spacecraft's attitude.

[0025] (4) Use "propulsion simulator + flywheel" as actuators for joint distribution control. The propulsion simulator uses pulse modulation technology, which has a high thrust limit, fast response speed, and controllable thrust duration; the flywheel adopts speed control mode, which has high torque response accuracy, good stability, and easy control. The two are jointly controlled and a suitable torque distribution plan is formulated, which not only improves control accuracy and stability, but also shortens the stable convergence time.

[0026] (5) A hardware and software integrated test and measurement system based on the xPC Target real-time system is used, and a light reflection memory is used to store and forward test data. The test platform and the computer under the platform use a wireless network for information exchange, which is convenient and fast and does not introduce additional interference, ensuring the low latency, high bandwidth and strong stability of the test system data communication.

[0027] (6) A complete process of ground-based full-physics simulation test for rapid and stable control of spacecraft attitude under strong impact disturbances is provided. The simulation test process is streamlined, visualized, and easy to evaluate. It verifies the correctness of the spacecraft attitude stabilization control scheme and examines the function and performance of the actual control system. It fills the gaps in related research, reduces the cost of conducting space-based experiments, and provides a reference for similar simulation experiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the ground full-physics simulation test system;

[0029] Figure 2 This is a bottom view of the air bearing stage optical code disk and angle measuring device;

[0030] Figure 3 This is the flowchart of the full physical simulation test;

[0031] Figure 4 is the angular velocity change curve of the test platform;

[0032] Figure 5 is the test platform angle change curve;

[0033] Figure 6 is the flywheel speed change curve;

[0034] Figure 7 is the thruster operating time.

[0035] In the figure: 1-air floating platform, 2-ejection simulator, 3-nozzle, 4-solenoid valve, 5-compressed gas cylinder, 6-voltage source, 7-mobile power supply, 8-wireless router, 9-industrial computer, 10-PXI system, 11-fiber optic gyroscope, 12-flywheel, 13-front-end computer, 14-angle measuring device, 15-optical encoder. DETAILED DESCRIPTION

[0036] The present invention will be further described below with reference to the accompanying drawings.

[0037] The present invention adopts the "ground-space equivalent analysis method" to locate the unknown form of strong impact interference suffered by the spacecraft in space at the impulse moment, and performs equivalent simulation through a ground test device.

[0038] Spacecraft in space are subject to strong impact disturbances from unknown sources, the form and duration of which are difficult to determine. According to the law of conservation of energy, the energy of impacts on a spacecraft is converted into its own kinetic energy. When the impact does not pass through the spacecraft's center of mass, part of the impact energy is converted into the spacecraft platform's rotational kinetic energy, manifesting as an increase in the spacecraft's rotational angular velocity.

[0039] Angular momentum, also known as angular momentum, represents the product of a spacecraft's moment of inertia and angular velocity. For a point mass on a spacecraft, its angular momentum is defined as the product of momentum and eccentricity. According to the law of conservation of angular momentum, a spacecraft subjected to a strong impact is separated into two parts: the separation body and the spacecraft body, which satisfy the following conditions:

[0040]

[0041] Where, is the moment of inertia of the spacecraft body; is the change in the angular velocity of the spacecraft body; is the mass of the separated body; is the change in the velocity of the separated body; is the separation eccentricity.

[0042] Impulse moment, also known as angular impulse, is expressed as the product of the external torque and the duration of action. It is also equal to the product of the impulse acting on the object and the eccentricity. For a strong impact disturbance to a spacecraft, the disturbance torque and duration are unknown and difficult to measure. The strong impact disturbance can be expressed as:

[0043]

[0044] Where, is the impulse moment of the spacecraft subjected to strong impact disturbance; is the disturbance torque of the strong impact on the spacecraft; is the duration of the interference torque of the strong impact on the spacecraft.

[0045] From the above, we can see that the impulse moment generated by the spacecraft under strong impact interference can be expressed as:

[0046]

[0047] The ground test system uses a catapult simulator to perform strong impact interference input. The interference torque and action time are also unknown. The impulse rectangle formula is expressed as:

[0048]

[0049] Where, is the impulse moment of the ground test platform subjected to strong impact disturbance; is the interference torque of the ground ejection mass block on the test platform; is the duration of the interference torque of the ground ejection mass block on the test platform; is the mass of the ejection mass; is the change in angular velocity of the ejection mass; is the eccentricity of the ejection mass; is the moment of inertia of the ground test platform; is the change in the angular velocity of the ground test platform.

[0050] In order to realize the equivalent analysis of heaven and earth, it is advisable to assume , the electromagnetic catapult simulator can be set as a full physical simulation test system to carry out strong impact interference input of the same magnitude.

[0051] The present invention Figure 1In the full-physical simulation test system shown, the strong impact interference input is provided by the ejection simulator. The ejection simulator 2 adopts a modular design and is installed and fixed on the test platform through an adapter. During actual installation, the ejection simulator 2 is generally installed on the side of the test platform. After the mass block is ejected, there is no secondary contact with the test platform, and the ejection direction does not pass through the rotation center of the test platform. The ejection simulator is mainly composed of a mechanical device and a control system. The mechanical device is mainly divided into three parts: a slide rail, a launch tube, and a mass block; the control system completes the locking and release of the mass block through a relay. Specifically, the ejection simulator places the ejection mass block in the launch tube. One end of the launch tube is engraved with a thread. By rotating the bottom handle, the spring in the launch tube is applied with elastic force, which further acts on the ejection mass block. An electromagnetic lock is installed at the other end of the launch tube to control the opening and closing of the cover. To simulate an ejection, the cover is first opened, and after placing the ejection mass inside the launch tube, the electromagnetic lock is controlled to close the cover. Next, the handle is rotated to compress the spring until sufficient elastic potential energy is generated. Finally, the electromagnetic lock is controlled to open the cover, allowing the ejection mass to gain sufficient kinetic energy and be ejected from the launch tube. The lower base of the launch tube is mounted on a movable slide. By adjusting the position of the launch tube on the slide, the center of mass offset is changed, generating impulse moments of varying magnitudes and directions, thus achieving adjustable, step-by-step simulation of strong impacts.

[0052] The core device of the fully physical simulation test system described in this invention is a uniaxial air-floating platform equipped with an optical encoder angle measurement device. The air-floating platform 1 serves as the primary support surface at the bottom, upon which all other test hardware and individual units are placed. After proper placement, electrical connections, and center-of-mass leveling, the specific positions of the test hardware and individual units on the air-floating platform can be roughly determined. The air-floating platform is pre-fabricated with a variety of screw holes of varying sizes evenly distributed throughout. Some individual units or structural components have precise mechanical interfaces and can be directly mounted to the air-floating platform using prefabricated screw holes or indirectly secured to the platform using custom adapter plates. Other hardware can be secured to the platform using adhesive or lashing. The air-floating platform, along with the positioned test hardware and individual units, can be precisely leveled again using a center-of-mass tester and counterweights of varying sizes, ensuring that the platform's center of mass is perpendicular to the uniaxial air-floating platform's center of rotation. The air-floating platform, counterweights, test hardware, and individual units are secured together to form a single unit, hereinafter referred to as the test platform. The pressurized gas buoys the test platform, creating a microgravity, low-friction mechanical environment within the horizontal plane.

[0053] The sensor of the simulation test system adopts the combination of optical code disk angle measuring device and fiber optic gyroscope. Figure 2As shown, the optical code disk 15 is installed on the bottom surface of the test platform, and the corresponding angle measuring device 14 of the optical code disk 15 is installed on the support column of the air bearing platform. The two are physically isolated. The rotation angle of the test platform is measured by the optical code disk angle measuring device and then transmitted to the ground front-end computer 13; the fiber optic gyroscope on the test platform can measure the current angular velocity of the air bearing platform in real time, remove the angular velocity of the Earth's rotation, and then transmit it to the ground front-end computer; the "propulsion simulator + flywheel" combined actuator on the test platform controls the torque distribution output, wherein the propulsion simulator consists of a nozzle 3, a solenoid valve 4 and a compressed gas cylinder 5, and adopts pulse modulation technology for torque output; the flywheel adopts a speed control mode, removes friction interference torque through an internal closed loop, and outputs a precise and stable reaction torque.

[0054] The simulation test system's computational simulation module utilizes an industrial computer 9, a PXI system 10, and a ground-based front-end computer 13. The industrial computer runs the xPC Target real-time system, which contains Matlab / Simulink spacecraft attitude control programs. The PXI system, comprising a chassis, controller, and board modules, is a comprehensive hardware and software measurement and testing system. The front-end computer runs software such as Matlab / Simulink, LabView, and a SQL Server database, and provides a graphical human-computer interface.

[0055] The power supply and distribution module of the simulation test system uses a combination of a mobile power supply 7 and a voltage regulator 6. The mobile power supply not only guarantees the rated capacity and output power, but also features simple and fast charging and discharging, making it suitable for benchtop use. The voltage regulator provides multiple voltage outputs, with adjustable, stable, and reliable output voltages.

[0056] The simulation test system's data communication module utilizes a combination of electrical cables, optical fibers, network cables, and a wireless router 8. The PXI system uses boards and supporting cables to transmit and receive data between the fiber-optic gyroscope 11, flywheel 12, and propulsion simulator solenoid valves. The industrial computer directly connects to the fiber-optic reflective memory board via optical fiber, enabling high-speed, low-latency data communication with the PXI system. The industrial computer and the PXI system are directly connected to the wireless router via network cables, and wirelessly connect to the front-end computer off-stage, enabling data forwarding and storage within the same network.

[0057] The following is a specific example of a ground-based full-physics simulation test system for spacecraft attitude stabilization control under strong impact interference:

[0058] Assume that a spacecraft is undergoing a space ejection test, and the strong impact disturbance generated during the ejection process affects the stability of the spacecraft's attitude. , ejection speed , ejection eccentricity , the spacecraft's moment of inertia after ejection The ground test platform uses a ejection simulator for strong impact interference equivalent input. It is known that the ejection simulator can eject standard mass blocks. , if the ejection simulation body momentum moment is to be satisfied , then the velocity of the ejection mass block needs to be changed , and the ejection eccentricity of the ground simulation device .

[0059] like Figure 3 As shown, the following test steps are carried out according to the test process:

[0060] 1. Conduct electrical commissioning of the hardware unit. Test that the power supply and distribution module is working properly, the test platform is floating normally, and data communication is transmitting and receiving normally.

[0061] 2. Balancing the center of mass of the test platform and measuring the moment of inertia. , the center of mass deviation is less than 0.0003m.

[0062] 3. Measure the friction torque of the air-floating platform. After the test platform is air-floated, apply a rotational angular velocity and record the test platform angle and angular velocity information in real time. By analyzing the test platform data, calculate the rotational angular acceleration of the air-floating platform. , and then calculate the friction interference torque of the platform .

[0063] 4. Determine the strong impact disturbance impulse moment. Set up the ejection simulator and eject the mass block at a speed of At the same time, adjust the position of the mass block on the slide rail so that the ejection eccentricity of the test platform is , satisfying formula (4). After the test platform is air-floated, the computer front-end program controls the ejection simulator to close the electromagnetic lock, open the cover, eject the projectile, and record the test platform angle and angular velocity information in real time.

[0064] 5. Test simulation and record test data. The test platform angular velocity and angle change curves are as follows: Figure 4 、 Figure 5 As shown, the flywheel speed curve of the test platform is as follows Figure 6 As shown, the test platform propulsion simulator action time is as follows Figure 7 shown.

[0065] 6. Test data analysis and evaluation. It can be seen from the simulation test data that the ground-based full-physics simulation test system and method for spacecraft attitude stability control under strong impact interference designed by the present invention has an angular momentum of about , and the expected effect was achieved for the equivalent simulation of strong impact interference; under the strong impact interference simulated by ground ejection, the control pointing accuracy of the test platform was better than 0.03°, and the control stability was better than 0.01° / s, which can effectively verify the effectiveness of the attitude control system scheme and provide a reference for the spacecraft space attitude stabilization control scheme under strong impact interference.

[0066] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact disturbances, characterized by: It includes a single-axis air-floating platform, a launch simulator, a sensor, a computing simulation module, a power supply and distribution module, and a data communication module; The uniaxial air-floating platform includes an air-floating platform and an air-floating platform support column arranged at the center of the bottom of the air-floating platform. The air-floating platform is used to fix and install various experimental hardware and single units. The air-floating platform and the test hardware and single units with determined positions can be accurately leveled again using a center of mass tester with counterweights of different specifications, so that the center of mass of the air-floating platform is perpendicular to the rotation center of the uniaxial air-floating platform. The air-floating platform, counterweights, test hardware and single units are fixed to form an integrated test platform. The test platform floats due to pressurized gas, forming a microgravity and low-friction mechanical environment in the horizontal plane. The ejection simulator adopts a modular design and is fixed to the side of the test platform through an adapter. The mass block of the ejection simulator has no secondary contact with the test platform after ejection, and the ejection direction does not pass through the rotation center of the test platform. The sensor uses a combination of an optical encoder angle measuring device and a fiber optic gyroscope. The rotation angle of the test platform is measured by the optical encoder angle measuring device and then transmitted to the ground front-end computer. The fiber optic gyroscope on the test platform can measure the angular velocity of the current air-floating platform in real time, remove the angular velocity of the earth's rotation, and transmit it to the ground front-end computer. The test platform uses a propulsion simulator and a flywheel actuator to control torque distribution output. The propulsion simulator consists of a nozzle, a solenoid valve, and a compressed gas cylinder, and uses pulse modulation technology to output torque. The flywheel adopts a speed control mode, removes friction interference torque through an internal closed loop, and outputs accurate and stable reaction torque. The computing simulation module is composed of an industrial computer, a PXI system and a ground front-end computer.

2. The ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact disturbance according to claim 1 is characterized by: The ejection simulator includes a mechanical device and a control system; The mechanical device includes a slide rail, a launch tube, and an ejection mass block. The ejection mass block is placed in the launch tube. One end of the launch tube is engraved with a thread. By rotating a handle connected to the thread, an elastic force is applied to the spring in the launch tube, which further acts on the ejection mass block. An electromagnetic lock is installed at the other end of the launch tube, which is controlled by a relay of the control system to open and close the cover at the other end of the launch tube. When simulating an ejection process, the cover must first be opened, and after placing the ejection mass inside the launch tube, the electromagnetic lock must be controlled to close the cover. Secondly, the handle must be rotated to compress the spring until sufficient elastic potential energy is generated. Finally, the electromagnetic lock must be controlled to open the cover, and the ejection mass must gain sufficient kinetic energy to be ejected from the launch tube. The lower base of the launch tube is installed on a movable slide rail. By adjusting the position of the launch tube on the slide rail, the center of mass offset is changed to form impulse moments of different sizes and directions, thereby realizing adjustable strong impact simulation levels.

3. The ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact disturbance according to claim 1 is characterized by: The optical code disk is installed on the bottom surface of the test platform, and the angle measuring device corresponding to the optical code disk is installed on the support column of the air-floating platform, so that the optical code disk and the corresponding angle measuring device are physically isolated.

4. The ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact disturbance according to claim 1 is characterized by: The industrial computer loads and runs the xPC Target real-time system, and the system writes the Matlab / Simulink spacecraft attitude control program.

5. The ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact disturbance according to claim 1 is characterized by: The PXI system includes a chassis, a controller and a board module, and is a measurement and testing system integrating software and hardware.

6. The ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact disturbance according to claim 1 is characterized by: The front-end computer runs Matlab / Simulink, LabView and SQL server database software, and provides a graphical human-computer interaction interface.

7. The ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact disturbance according to claim 1 is characterized by: The power supply and distribution module adopts a combination of a mobile power source and a voltage stabilizing source.

8. The ground-based full-physics simulation test system for spacecraft attitude stability control under strong impact disturbance according to claim 1 is characterized by: The data communication module uses a combination of cables, optical fibers, network cables and wireless routers; the PXI system uses boards and supporting cables to realize data transmission and reception between the fiber optic gyroscope, flywheel and propulsion simulator solenoid valve; the industrial computer is directly connected to the fiber optic reflective memory board through optical fiber to achieve high-speed, low-latency data communication with the PXI system; the industrial computer and the PXI system are directly connected to the wireless router through the network cable, and are wirelessly connected to the front-end computer under the table to realize data forwarding and storage within the same network.

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