A method, system, and computer device for selecting a single unit for spacecraft attitude control.

Abstract

This invention discloses a method, system, and computer equipment for selecting individual attitude control units for spacecraft. The method includes: calculating disturbance torque based on a disturbance torque model; acquiring torque data of the disturbance torque and the suppression capability of the attitude control unit against the disturbance torque, with the torque data including torque distribution, magnitude, and direction; selecting the corresponding attitude control unit combination and unit control parameters using an optimization algorithm based on the spacecraft's attitude control requirements, torque data, and the suppression capability of the attitude control unit against the disturbance torque; simulating the spacecraft's operating attitude under different orbits and space environments based on the attitude control unit combination, corresponding unit control parameters, and numerical simulation, and selecting the attitude control unit combination based on the simulation results. This invention can significantly improve the accuracy and stability of satellite attitude control systems and reduce the uncertainties that may exist in traditional selection methods.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, and more specifically to a method, system, and computer equipment for selecting a single unit for spacecraft attitude control. Background Technology

[0002] In the attitude control system of spacecraft, disturbance torques in the space environment (such as gravity gradient torque, solar pressure torque, atmospheric drag torque, and residual magnetic torque) are important factors affecting the attitude control accuracy of spacecraft.

[0003] Existing attitude control system selection methods typically rely on experience or simple simulation models, which usually cannot fully consider the complex effects of various disturbance torques on the spacecraft attitude control system. Therefore, existing attitude control system selection methods are difficult to meet the requirements of high-precision and high-stability attitude control.

[0004] Therefore, a new technological solution is needed. Summary of the Invention

[0005] In view of this, embodiments of the present invention provide a method, system and computer device for selecting a single unit for spacecraft attitude control, in order to at least solve the problem that existing optimization methods are mostly empirical algorithms and lack system optimization under the combined action of different disturbance torques.

[0006] The embodiments of the present invention provide the following technical solutions:

[0007] This invention provides a method for selecting a single attitude control unit for a spacecraft, comprising:

[0008] An interference torque model is established based on the spacecraft's orbital parameters, physical characteristics, and the space environment. The interference torque is then calculated based on the interference torque model. The interference torque includes gravity gradient torque, atmospheric drag torque, solar pressure torque, and remanent magnetization torque.

[0009] The torque data of the disturbance torque and the ability of the attitude control unit to suppress the disturbance torque are obtained. The torque data includes the torque distribution, torque magnitude, and torque direction.

[0010] Based on the spacecraft attitude control requirements, the torque data, and the ability of the attitude control unit to suppress the disturbance torque, an optimization algorithm is used to select the corresponding attitude control unit combination and unit control parameters.

[0011] Based on the attitude control unit combination, the corresponding unit control parameters, and numerical simulation, the spacecraft's operating attitude under different orbits and space environments is simulated, and the attitude control unit combination is selected according to the simulation results.

[0012] Furthermore, the method for calculating the disturbance torque includes:

[0013] The gravity gradient torque is calculated based on the spacecraft's position and the Earth's gravitational field model;

[0014] The solar pressure torque is calculated based on the spacecraft surface reflectance, solar radiation intensity, and spacecraft attitude angle.

[0015] The atmospheric drag moment is calculated based on spacecraft orbit, atmospheric density data, drag coefficient, and spacecraft frontal area;

[0016] The remanent torque is calculated based on the spacecraft's material, magnetic properties, and changes in the magnetic field.

[0017] Furthermore, based on the single-machine control accuracy, single-machine response speed, single-machine energy consumption, and single-machine stability assessment, the ability of the attitude control unit to suppress the disturbance torque is obtained.

[0018] Furthermore, the selection of the corresponding attitude control unit combination and unit control parameters using optimization algorithms also includes:

[0019] The ability of the attitude control unit to suppress the disturbance torque under different task environments is evaluated, and the corresponding combination of attitude control units and the control parameters of the unit are selected based on the suppression capability.

[0020] Furthermore, the step of selecting the attitude control unit combination based on simulation results includes:

[0021] If the simulation results match the spacecraft attitude control requirements, then the attitude control unit combination is selected.

[0022] Furthermore, the simulation of the spacecraft's operational attitude under different orbital and space environments, based on the attitude control unit assembly and numerical simulation, includes:

[0023] Construct a virtual simulation environment and input the disturbance torque model and the attitude control unit combination;

[0024] The virtual simulation environment is used to simulate the operation of spacecraft in different orbits and space environments to verify the effect of the attitude control unit combination in suppressing disturbance torque under different mission conditions.

[0025] The present invention provides a single-unit selection system for spacecraft attitude control, comprising:

[0026] The data input module is used to acquire the spacecraft's orbital parameters, physical characteristics, and space environment parameters of the space environment in which it is located.

[0027] The disturbance torque calculation module is used to establish a disturbance torque model and calculate the disturbance torque based on the disturbance torque model. The disturbance torque includes the gravitational gradient torque, atmospheric drag torque, solar pressure torque, and remanent magnetization torque.

[0028] A single-unit selection module is used to acquire the torque data of the disturbance torque and the suppression capability of the attitude control unit for the disturbance torque. The torque data includes torque distribution, torque magnitude and torque direction. Based on the spacecraft attitude control requirements, the torque data and the suppression capability of the attitude control unit for the disturbance torque, the module uses an optimization algorithm to select the corresponding attitude control unit combination and single-unit control parameters.

[0029] The simulation verification module is used to simulate the spacecraft's operating attitude under different orbits and space environments based on the attitude control unit combination, the corresponding unit control parameters, and numerical simulation, and to select the attitude control unit combination based on the simulation results.

[0030] Furthermore, the single-machine selection module is also used to evaluate and obtain the ability of the attitude control single machine to suppress the disturbance torque based on the single-machine control accuracy, single-machine response speed, single-machine energy consumption, and single-machine stability.

[0031] Furthermore, the simulation verification module is also used to construct a virtual simulation environment, input the disturbance torque model and the attitude control unit combination, and simulate the spacecraft's operating state under different orbits and different space environments based on the virtual simulation environment, so as to verify the effect of the attitude control unit combination in suppressing disturbance torque under different mission conditions.

[0032] A computer device according to the present invention includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the single-unit selection method for spacecraft attitude control as described in any of the preceding claims.

[0033] Compared with the prior art, the beneficial effects that the at least one technical solution adopted in the embodiments of the present invention can achieve include at least:

[0034] This invention discloses a method for selecting a single attitude control unit for a spacecraft. By accurately modeling various disturbance moments in the space environment, it calculates the moments affecting the attitude control system, taking into account factors such as orbital parameters, satellite physical properties, and changes in the space environment. Then, based on the disturbance moment model and attitude control requirements, it optimizes the selection of the single attitude control unit to minimize attitude error, energy consumption, and other objectives. This invention can significantly improve the accuracy and stability of the satellite attitude control system and reduce the uncertainties that may exist in traditional selection methods. Attached Figure Description

[0035] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0036] Figure 1 This is a flowchart illustrating a method for selecting a single unit for spacecraft attitude control, as described in an embodiment of this specification.

[0037] Figure 2 This is a schematic diagram illustrating the calculation of atmospheric drag torque provided in this instruction manual;

[0038] Figure 3 This is a schematic diagram illustrating the calculation of gravity gradient torque provided in this instruction manual;

[0039] Figure 4 This is a schematic diagram illustrating the calculation of solar pressure torque provided in this instruction manual;

[0040] Figure 5 This is a schematic diagram for calculating the residual magnetic torque provided in this instruction manual;

[0041] Figure 6 This is a schematic diagram of the single-machine selection method based on the calculation of space environment disturbance torque provided in this manual. Detailed Implementation

[0042] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0043] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0044] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number and aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0045] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0046] Additionally, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that practice can be carried out without these specific details.

[0047] In existing technologies, although some studies have modeled the disturbance torque of the space environment, these methods generally have the following shortcomings:

[0048] 1. Insufficient model accuracy and comprehensiveness: The current modeling and simulation process for disturbance torque is relatively simple and lacks sufficient accuracy and comprehensiveness, making it difficult to fully reflect the complex dynamics in the actual environment.

[0049] 2. Limitations of attitude control unit selection: Most methods rely mainly on empirical methods for selecting attitude control units, failing to fully consider the optimization of system behavior under the combined action of different disturbance torques.

[0050] 3. Poor adaptability of optimization methods: Existing optimization strategies are mostly based on empirical algorithms, which often fail to provide sufficient adaptability and robustness when dealing with variable spatial environments.

[0051] Therefore, there is an urgent need for an innovative method that can comprehensively consider the influence of space environment disturbance torques and optimize the selection of attitude control units, thereby significantly improving the accuracy and stability of satellite attitude control, especially under complex and variable environmental conditions.

[0052] Based on this, the embodiments of this specification propose a processing solution: such as Figure 1As shown, the present invention provides a method for selecting a single attitude control unit for a spacecraft. By comprehensively considering the influence of various disturbance torques in the space environment (such as gravity gradient torque, atmospheric drag torque, solar pressure torque, remanent magnetization torque, etc.) on the satellite attitude control system, it adopts precise mathematical modeling and optimization algorithms to optimize the selection of the single attitude control unit, thereby improving the attitude control accuracy and stability of the satellite in the space environment.

[0053] The technical solutions provided by the various embodiments of this application are described below with reference to the accompanying drawings.

[0054] like Figures 1-6 As shown, the present invention provides a method for selecting a single unit for spacecraft attitude control, comprising:

[0055] Step S102: Establish a disturbance torque model based on the spacecraft's orbital parameters, physical characteristics, and the space environment, and calculate the disturbance torque based on the disturbance torque model. The disturbance torque includes gravity gradient torque, atmospheric drag torque, solar pressure torque, and remanent magnetization torque.

[0056] The methods for calculating the disturbance torque include: calculating the gravity gradient torque based on the spacecraft's position and the Earth's gravitational field model; calculating the solar radiation pressure torque based on the spacecraft's surface reflection coefficient, solar radiation intensity, and spacecraft attitude angle; calculating the atmospheric drag torque based on the spacecraft's orbit and atmospheric density data; and calculating the remanent magnetic torque based on the spacecraft's material, magnetic properties, and changes in the magnetic field.

[0057] In this study, considering the influence of Earth's gravitational field on the spacecraft, the disturbance moment model calculates the moment caused by the gravitational gradient. Based on changes in orbital position and satellite attitude, the expression for the three-axis gravity gradient moment is derived by combining the inertial matrix and attitude matrix. The conditions of orbital angular velocity and small attitude angles are specifically considered, making the calculation more accurate.

[0058] Specifically, the calculation method for the gravitational gradient torque is as follows:

[0059] Calculate the unit vector. r is the spacecraft's position vector, and γ is the distance from the satellite to the Earth's center;

[0060] Calculate the inertia matrix I of the spacecraft, which reflects the physical characteristics of the spacecraft;

[0061] Based on the orbit and attitude conditions, the three-axis gravity gradient torque is calculated using the above formula, and the three-axis torques (Tgx, Tgy, Tgz) in the spacecraft coordinate system are obtained.

[0062] Among them, the solar pressure torque varies with the attitude of the spacecraft and is easily affected by the intensity of solar radiation and the surface characteristics of the spacecraft.

[0063] Among them, based on the light pressure effect of solar radiation on spacecraft, the disturbance torque model calculates the light pressure of spacecraft on different illuminated surfaces. Combining the spacecraft shape, reflection coefficient and solar radiation intensity, the calculation formula for the total light pressure torque is further derived.

[0064] Among them, the solar radiation-induced light pressure acts on the surface of the spacecraft, especially on the solar panels, generating a torque on the spacecraft. The calculation method for the solar radiation pressure torque is as follows:

[0065] Calculate solar radiation intensity ρ sun This value is usually determined by physical constants such as the solar constant and the speed of light;

[0066] Calculate the angle θ between the unit normal vector n of the spacecraft's illuminated surface and the unit vector L of the light source direction, based on the direction of solar radiation.

[0067] Calculate the total area S of the stressed surface based on the shape of the spacecraft, and calculate the light pressure based on the reflection coefficient η;

[0068] By multiplying the lever arm of each surface by the solar pressure, the solar pressure torque generated on each surface is obtained. The total solar pressure torque is then summed up, and the calculation formula is as follows:

[0069] F = -ρ sun cosθ[(1-η)L+2ηcosθn].

[0070] Among them, atmospheric drag torque is calculated by atmospheric density and the relative velocity of the spacecraft. Atmospheric drag torque usually has a significant impact on low-orbit satellites. The interference torque model is based on atmospheric density, drag coefficient and the airflow area of ​​the spacecraft to calculate the aerodynamic torque generated by air molecule collisions.

[0071] Specifically, the calculation method for atmospheric drag torque is as follows:

[0072] Calculate atmospheric density ρ a This value depends on the satellite's orbital altitude and atmospheric conditions;

[0073] Calculate the relative velocity V of the spacecraft, including the relative velocity between the satellite and the atmosphere;

[0074] Calculate the frontal area A of the spacecraft P And based on the aerodynamic drag coefficient C D The formula for calculating the torque generated by atmospheric drag is as follows:

[0075] T a =ρ a C D A P ·l×(u×u) / 2.

[0076] In this application, based on the interaction between the effective magnetic moment of the spacecraft and the local geomagnetic field, the disturbance torque model calculates the torque generated by the magnetic moment and uses a vector cross product to describe the magnitude and direction of the residual magnetic torque.

[0077] Specifically, the calculation method for remanent torque is as follows:

[0078] Calculate the effective magnetic moment M of the spacecraft, which originates from the residual magnetic field of various electronic devices on the spacecraft or the magnetic moment coils used for attitude control;

[0079] The remanent magnetization torque is calculated based on the geomagnetic field strength B at the satellite's location. The formula for calculating the remanent magnetization torque is as follows:

[0080] Tm = M × B.

[0081] Step S104: Obtain the torque data of the disturbance torque and the ability of the attitude control unit to suppress the disturbance torque. The torque data includes the torque distribution, torque magnitude and torque direction.

[0082] Step S104 is used to provide the necessary data foundation for the selection of attitude control clicks. It establishes an optimized selection process for specific satellite missions by acquiring the interference torque and the ability of the attitude control unit to suppress the interference torque.

[0083] The torque distribution refers to the distribution of the disturbance torque along each axis of the spacecraft in three-dimensional space.

[0084] Specifically, different types of disturbance moments (such as gravitational gradient moments and solar pressure moments) may exhibit different strengths and directions in different directions. For example, the main component of the gravitational gradient moment may be on a specific axis, while the solar pressure moment may be related to the direction of the normal to the satellite surface.

[0085] Among them, the magnitude of the torque reflects the intensity of the disturbance torque and is an important reference indicator in the selection process of attitude control unit.

[0086] Among them, torques in different directions will have different effects on the attitude of the spacecraft, which need to be comprehensively evaluated in conjunction with the attitude dynamics of the spacecraft.

[0087] Among them, the suppression capability of the attitude control unit refers to its ability to resist and eliminate the influence of disturbance torque on the satellite's attitude, which directly affects the degree to which the satellite can maintain attitude stability and precise control.

[0088] The characteristics of suppression capability include: Maximum output torque: The maximum reaction torque that each unit can provide to counteract interference torque. If a unit cannot provide sufficient torque, interference cannot be completely suppressed. Response time: The delay time from receiving a control command to the actual output torque of the unit. The faster the response, the better the suppression capability against short-term high-frequency interference. Energy efficiency: The power consumption required to suppress interference, directly affecting the satellite's energy budget. Cumulative error: Deviations that may occur in the control unit during long-term operation, such as the angular momentum saturation problem of the flywheel or the external magnetic field adaptability of the magnetic torquer.

[0089] Among them, single-machine control accuracy is the contribution of a single attitude control unit to the attitude control accuracy; single-machine stability is the ability of the control system to maintain stability when subjected to different disturbance torques; single-machine energy consumption is the energy consumption of the control system to ensure the feasibility of long-term operation.

[0090] Step S104 can accurately obtain the basic characteristics of the disturbance torque and the suppression performance of different single units on these torques, thus providing a basis for the subsequent selection of attitude control single units.

[0091] Step S106: Based on the spacecraft attitude control requirements, torque data, and the ability of the attitude control unit to suppress disturbance torque, use an optimization algorithm to select the corresponding attitude control unit combination and unit control parameters.

[0092] The selection of attitude control units is based on comparing the performance of different attitude control units in suppressing disturbance torque, and selecting the most suitable combination of attitude control units.

[0093] For example, the performance of each control unit (such as flywheel, reaction wheel) can be evaluated based on the calculation results of the disturbance torque (such as the magnitude, direction and distribution of each disturbance torque), especially their effect on reducing each disturbance torque. The selection process can be optimized using optimization algorithms to automatically select the most suitable combination of units.

[0094] Specifically, the ability of a single attitude control unit to suppress disturbance torque can be evaluated and obtained based on its single-unit control accuracy, single-unit response speed, single-unit energy consumption, and single-unit stability.

[0095] Among them, the spacecraft attitude control requirement is the required attitude control accuracy of the spacecraft.

[0096] The attitude control unit includes a flywheel, magnetic torque generator, micro-thruster, gyroscope, or reaction wheel, etc.

[0097] This step allows for the selection of different single-machine selection strategies based on optimization requirements. These requirements include maximizing attitude control accuracy, minimizing system energy consumption, improving attitude stability, or reducing overall cost and load. This application utilizes optimization algorithms to select different attitude control single-machine combinations and corresponding single-machine control parameters according to varying needs.

[0098] The optimization algorithms include genetic algorithms, particle swarm optimization algorithms, simulated annealing, deep learning, and other algorithms.

[0099] Among them, the attitude control unit combination is a combination of different units, such as three flywheels and one magnetic torquer. The unit control parameters are the specific control parameters of the unit, such as the speed range of the flywheels and the current setting of the magnetic torquer.

[0100] Furthermore, the selection of the corresponding attitude control unit combination and unit control parameters using optimization algorithms also includes: evaluating the ability of the attitude control unit to suppress disturbance torques under different task environments, and selecting the corresponding attitude control unit combination and unit control parameters based on the suppression capability, so as to comprehensively evaluate the overall performance of the attitude control unit in suppressing disturbance torques.

[0101] This includes evaluating the overall performance of the selected control unit combination under different mission environments and ensuring that the selected structure can provide efficient attitude control under all predetermined orbit and environmental conditions.

[0102] Step S106 is used to find the optimal combination of attitude control units and their control parameters based on the impact of the disturbance torque on the spacecraft attitude and the performance of various attitude control units, so as to improve the accuracy and stability of the system and reduce resource consumption.

[0103] Step S106 combines spacecraft attitude control requirements, disturbance torque data, and individual unit performance data, using an optimization algorithm to automatically select the optimal combination of attitude control units and their parameters. This method not only improves the scientific rigor of the selection process but also effectively enhances the accuracy, stability, and adaptability of the satellite attitude control system, while reducing energy consumption and cost, achieving comprehensive system optimization. This process has broad applicability, especially in complex space mission environments, where it can significantly enhance spacecraft performance.

[0104] Step S108: Based on the attitude control unit combination, the corresponding unit control parameters, and numerical simulation, simulate the spacecraft's operating attitude in different orbits and space environments, and select the attitude control unit combination according to the simulation results. Verify and select the optimal attitude control unit combination and its control parameters through numerical simulation to ensure that the spacecraft can effectively maintain the required attitude in different orbits and space environments.

[0105] Specifically, based on attitude control unit assembly and numerical simulation, the operational attitude of the spacecraft under different orbits and space environments is simulated, including:

[0106] Construct a virtual simulation environment and input the disturbance torque model and attitude control unit combination;

[0107] The virtual simulation environment is used to simulate the operation of spacecraft in different orbits and space environments to verify the effect of attitude control unit combination on suppressing disturbance torque under different mission conditions.

[0108] Furthermore, if the simulation results match the spacecraft's attitude control requirements, then a combination of individual attitude control units is selected.

[0109] In step S108, simulation can be performed using a software simulation platform, such as MATLAB / Simulink, STK, etc.

[0110] Among them, by simulating different orbits and space environments, it is possible to cope with simulation and attitude adjustment under different conditions.

[0111] Step S108 involves using numerical simulation tools (such as MATLAB, Simulink, etc.) to perform multi-scenario simulations. The simulation test evaluates the performance of the selection results in practical applications by simulating satellite operation under different orbital and environmental conditions.

[0112] The present invention provides a method for selecting single attitude control units for spacecraft. By ensuring that the selected combination of attitude control units is not only theoretically optimal, but also can operate effectively in a real space environment through simulation time verification, the reliability and adaptability of the system design are improved, and the risks and costs caused by unforeseen problems in practical applications are reduced.

[0113] This invention also provides a spacecraft attitude control unit selection system, including a data input module, a disturbance torque calculation module, a unit selection module, and a simulation verification module. The data input module acquires the spacecraft's orbital parameters, physical characteristics, and space environment parameters. The disturbance torque calculation module establishes a disturbance torque model and calculates the disturbance torque based on this model. The disturbance torque includes gravity gradient torque, atmospheric drag torque, solar pressure torque, and remanent magnetization torque. The unit selection module acquires the torque data of the disturbance torque and the attitude control unit's ability to suppress the disturbance torque. The torque data includes torque distribution, magnitude, and direction. Based on the spacecraft's attitude control requirements, the torque data, and the attitude control unit's ability to suppress the disturbance torque, an optimization algorithm is used to select the corresponding attitude control unit combination and unit control parameters. The simulation verification module simulates the spacecraft's operating attitude under different orbital and space environments based on the attitude control unit combination, corresponding unit control parameters, and numerical simulations. The module then selects the attitude control unit combination based on the simulation results.

[0114] The disturbance torque calculation module is also used to calculate different types of disturbance torques based on the input data, including gravity gradient torque, solar pressure torque, atmospheric drag torque, and remanent magnetic torque.

[0115] The single-unit selection module selects the most suitable attitude control unit based on the calculation results of the disturbance torque. This module evaluates the ability of different control units to suppress disturbance torque and selects the control unit with the best performance based on the performance parameters of each unit.

[0116] The single-unit selection module not only selects units based on the calculated disturbance torque, but also comprehensively evaluates the energy consumption, system stability, and attitude control accuracy of each control unit under specific tasks. Through these comprehensive evaluations, the most suitable attitude control unit is selected.

[0117] The simulation verification module constructs a virtual simulation environment to simulate the satellite's operational status under different orbits (such as low Earth orbit, medium Earth orbit, and high Earth orbit) and different space environments (such as solar radiation and Earth's magnetic field). During the simulation, the disturbance torque model and selected attitude control unit parameters are input to simulate the satellite's attitude response and stability, verifying the effectiveness of the selected unit under different mission conditions.

[0118] Furthermore, the single-machine selection module is also used to evaluate and obtain the attitude control single machine's ability to suppress disturbance torque based on single-machine control accuracy, single-machine response speed, single-machine energy consumption, and single-machine stability.

[0119] Furthermore, the simulation verification module is also used to construct a virtual simulation environment, input the disturbance torque model and attitude control unit combination, and simulate the spacecraft's operating state in different orbits and different space environments based on the virtual simulation environment, so as to verify the effect of the attitude control unit combination in suppressing disturbance torque under different mission conditions.

[0120] The present invention also provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the spacecraft attitude control single-machine selection method as described in any one of Embodiment 1.

[0121] In this specification, the same or similar parts between the various embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, for the product embodiments described later, since they correspond to the methods, the descriptions are relatively simple, and the relevant parts can be referred to the descriptions in the system embodiments.

[0122] The above description is merely a specific embodiment of this application, but the scope of protection of this application 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 this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for selecting a single unit for spacecraft attitude control, characterized in that, include: An interference torque model is established based on the spacecraft's orbital parameters, physical characteristics, and the space environment. The interference torque is then calculated based on the interference torque model. The interference torque includes gravity gradient torque, atmospheric drag torque, solar pressure torque, and remanent magnetization torque. The torque data of the disturbance torque and the suppression capability of the attitude control unit against the disturbance torque are obtained. The torque data includes torque distribution, torque magnitude and torque direction. The suppression capability of the attitude control unit against the disturbance torque is obtained based on the unit's control accuracy, unit response speed, unit energy consumption and unit stability. Based on the spacecraft attitude control requirements, the torque data, and the ability of the attitude control unit to suppress the disturbance torque, an optimization algorithm is used to select the corresponding attitude control unit combination and unit control parameters. Based on the attitude control unit combination, the corresponding unit control parameters, and numerical simulation, the spacecraft's operating attitude under different orbits and space environments is simulated, and the attitude control unit combination is selected according to the simulation results. The method for calculating the disturbance torque includes: The gravity gradient torque is calculated based on the spacecraft's position and the Earth's gravitational field model; The solar pressure torque is calculated based on the spacecraft surface reflectance, solar radiation intensity, and spacecraft attitude angle. The atmospheric drag moment is calculated based on spacecraft orbit, atmospheric density data, drag coefficient, and spacecraft frontal area; The remanent torque is calculated based on the spacecraft's material, magnetic properties, and changes in the magnetic field. The selection of the appropriate attitude control unit combination and unit control parameters using optimization algorithms also includes: The ability of the attitude control unit to suppress the disturbance torque under different task environments is evaluated, and the corresponding combination of attitude control units and the control parameters of the unit are selected based on the suppression capability. The step of selecting the attitude control unit combination based on simulation results includes: If the simulation results match the spacecraft attitude control requirements, then the attitude control unit combination is selected. The simulation of the spacecraft's operational attitude under different orbital and space environments, based on the attitude control unit assembly and numerical simulation, includes: Construct a virtual simulation environment and input the disturbance torque model and the attitude control unit combination; The virtual simulation environment is used to simulate the operation of spacecraft in different orbits and space environments to verify the effect of the attitude control unit combination in suppressing disturbance torque under different mission conditions.

2. A single-unit selection system for spacecraft attitude control, characterized in that, include: The data input module is used to acquire the spacecraft's orbital parameters, physical characteristics, and space environment parameters of the space environment in which it is located. The disturbance torque calculation module is used to establish a disturbance torque model and calculate the disturbance torque based on the disturbance torque model. The disturbance torque includes gravity gradient torque, atmospheric drag torque, solar pressure torque and remanent magnetization torque, and is used to calculate the gravity gradient torque based on the spacecraft position and the Earth's gravitational field model. The solar pressure torque is calculated based on the spacecraft surface reflectance, solar radiation intensity, and spacecraft attitude angle. The atmospheric drag moment is calculated based on spacecraft orbit, atmospheric density data, drag coefficient, and spacecraft frontal area; The remanent torque is calculated based on the spacecraft's material, magnetic properties, and changes in the magnetic field. A single-unit selection module is used to acquire the torque data of the disturbance torque and the suppression capability of the attitude control unit against the disturbance torque. The torque data includes torque distribution, torque magnitude, and torque direction. Based on the spacecraft attitude control requirements, the torque data, and the suppression capability of the attitude control unit against the disturbance torque, the module uses an optimization algorithm to select the corresponding attitude control unit combination and single-unit control parameters. The module also evaluates the suppression capability of the attitude control unit against the disturbance torque in different mission environments and selects the corresponding attitude control unit combination and single-unit control parameters based on the suppression capability. The simulation verification module is used to simulate the spacecraft's operating attitude under different orbits and space environments based on the attitude control unit combination, the corresponding unit control parameters, and numerical simulation. The module selects the attitude control unit combination based on the simulation results, and selects the attitude control unit combination if the simulation results match the spacecraft's attitude control requirements. The single-machine selection module is also used to evaluate and obtain the ability of the attitude control single machine to suppress the disturbance torque based on the single-machine control accuracy, single-machine response speed, single-machine energy consumption, and single-machine stability. The simulation verification module is also used to construct a virtual simulation environment, input the disturbance torque model and the attitude control unit combination, and simulate the spacecraft's operating state in different orbits and different space environments based on the virtual simulation environment, so as to verify the effect of the attitude control unit combination in suppressing disturbance torque under different mission conditions.

3. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the spacecraft attitude control single-machine selection method as described in claim 1.

Images