Spacecraft attitude control single-machine type selection method and system and computer equipment

Abstract

The invention discloses a spacecraft attitude control single-machine model selection method and system and computer equipment. The spacecraft attitude control single-machine model selection method comprises the steps that disturbance torque is calculated based on a disturbance torque model; torque data of the disturbance torque and the suppression capability of the attitude control single machine on the disturbance torque are obtained, wherein the torque data comprise the torque distribution condition, the torque size and the torque direction; selecting a corresponding attitude control single machine combination and single machine control parameters by utilizing an optimization algorithm on the basis of spacecraft attitude control requirements, torque data and the suppression capability of attitude control single machines on disturbance torque; and based on the attitude control single-machine combination, the corresponding single-machine control parameters and numerical simulation, simulating the operation attitude of the spacecraft in different orbits and space environments, and selecting the attitude control single-machine combination according to a simulation result. According to the method, the precision and the stability of the satellite attitude control system can be remarkably improved, and the possible uncertainty in a traditional model selection method is reduced.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft technology, and in particular to a single-machine selection method, system and computer equipment for spacecraft attitude control. Background Art

[0002] In the attitude control system of spacecraft, the interference torque in the space environment (such as gravity gradient torque, sunlight pressure torque, atmospheric drag torque, residual magnetic torque, etc.) is an important factor affecting the accuracy of spacecraft attitude control.

[0003] Existing attitude control system selection methods usually rely on experience or simple simulation models, which usually cannot fully consider the complex impact of various interference 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] Based on this, a new technical solution is needed. Summary of the invention

[0005] In view of this, an embodiment of the present invention provides a single-machine selection method, system and computer device for spacecraft attitude control, so as to at least solve the problem that existing optimization methods are mostly empirical algorithms that lack system optimization under the combined action of different interference torques.

[0006] The embodiment of the present invention provides the following technical solutions:

[0007] An embodiment of the present invention provides a single-machine selection method for spacecraft attitude control, comprising:

[0008] Establishing an interference torque model based on the orbital parameters, physical characteristics and space environment of the spacecraft, and calculating the interference torque based on the interference torque model, wherein the interference torque includes gravity gradient torque, atmospheric drag torque, sunlight pressure torque and residual magnetic torque;

[0009] Obtaining torque data of the interference torque and the ability of the attitude control unit to suppress the interference torque, wherein the torque data includes 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 interference torque, the corresponding attitude control unit combination and the unit control parameters are selected by using an optimization algorithm;

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

[0012] Furthermore, the calculation method of the interference torque includes:

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

[0014] Calculating the solar pressure moment based on the spacecraft surface reflection coefficient, solar radiation intensity and spacecraft attitude angle;

[0015] Calculating the atmospheric drag moment based on the spacecraft orbit, atmospheric density data, drag coefficient, and the frontal area of ​​the spacecraft;

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

[0017] Furthermore, based on the control accuracy of a single machine, the response speed of a single machine, the energy consumption of a single machine, and the stability of a single machine, the ability of the single machine to suppress the interference torque of the attitude control machine is evaluated and obtained.

[0018] Furthermore, using the optimization algorithm to select the corresponding attitude control unit combination and the unit control parameters also includes:

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

[0020] Further, the selecting the attitude control stand-alone combination according to the simulation result comprises:

[0021] In the case where the simulation result matches the spacecraft attitude control requirement, the attitude control stand-alone combination is selected.

[0022] Furthermore, the simulation of the operating attitude of the spacecraft in different orbits and space environments based on the attitude control stand-alone combination and numerical simulation includes:

[0023] Constructing a virtual simulation environment, and inputting a disturbance torque model and the attitude control unit combination;

[0024] The operating states of the spacecraft in different orbits and different space environments are simulated based on the virtual simulation environment to verify the effect of the attitude control unit combination in suppressing the interference torque under different mission conditions.

[0025] A single-machine selection system for spacecraft attitude control of the present invention comprises:

[0026] A data input module, wherein the data input module is used to obtain orbital parameters, physical characteristics of the spacecraft and space environment parameters of the space environment in which the spacecraft is located;

[0027] An interference torque calculation module, the interference torque calculation module is used to establish an interference torque model and calculate the interference torque based on the interference torque model, the interference torque includes gravity gradient torque, atmospheric drag torque, sunlight pressure torque and residual magnetic torque;

[0028] A stand-alone selection module, the stand-alone selection module is used to obtain the torque data of the interference torque and the suppression capability of the attitude control stand-alone to the interference torque, the torque data including the torque distribution, the torque magnitude and the torque direction, and based on the spacecraft attitude control requirements, the torque data and the suppression capability of the attitude control stand-alone to the interference torque, select the corresponding attitude control stand-alone combination and stand-alone control parameters by using an optimization algorithm;

[0029] A simulation verification module, wherein the simulation verification module is used to simulate the operating attitude of the spacecraft in different orbits and space environments based on the attitude control single-machine combination, the corresponding single-machine control parameters and numerical simulation, and select the attitude control single-machine combination according to the simulation results.

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

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

[0032] A computer device of the present invention comprises a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor implements the single-machine selection method for spacecraft attitude control as described in any one of the above items when executing the computer program.

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

[0034] The present invention provides a method for selecting a single machine for spacecraft attitude control. By accurately modeling various types of space environment interference torques, the torque affecting the attitude control system is calculated, including factors such as orbital parameters, satellite physical properties, and space environment changes. Then, based on the interference torque model and attitude control requirements, the selection of the single machine for attitude control is optimized to minimize the goals of attitude error, energy consumption, etc. The present invention can significantly improve the accuracy and stability of the satellite attitude control system and reduce the uncertainty that may exist in the traditional selection method. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0036] Figure 1 A flowchart of a single-machine selection method for spacecraft attitude control according to an embodiment of this specification;

[0037] Figure 2 It is a schematic diagram of atmospheric drag moment calculation provided by the implementation of this specification;

[0038] Figure 3 It is a schematic diagram of gravity gradient moment calculation provided by the implementation of this specification;

[0039] Figure 4 It is a schematic diagram of the calculation of the solar pressure moment provided by the implementation of this specification;

[0040] Figure 5 It is a schematic diagram of residual magnetic torque calculation provided by the implementation of this specification;

[0041] Figure 6 It is a schematic diagram of a single machine selection method based on calculation of space environment interference torque provided in the implementation of this specification. DETAILED DESCRIPTION

[0042] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0043] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0044] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present application, it should be understood by those skilled in the art that an 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 aspect described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0045] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The drawings only show components related to the present application rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0046] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the examples can be practiced without these specific details.

[0047] In the prior art, although some studies have modeled the space environment interference torque, these methods usually have the following shortcomings:

[0048] 1. Insufficient model accuracy and comprehensiveness: The current disturbance torque modeling and simulation process is relatively simple, lacking sufficient accuracy and comprehensiveness, and it is 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 to select attitude control units, and fail 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 changing spatial environments.

[0051] Therefore, an innovative method is urgently needed that can comprehensively consider the influence of the space environment interference torque and optimize the selection of attitude control units, thereby significantly improving the accuracy and stability of satellite attitude control, especially under complex and changeable environmental conditions.

[0052] Based on this, this specification embodiment proposes a processing solution: Figure 1As shown, a method for selecting a single spacecraft attitude control unit of the present invention comprehensively considers the influence of various interference torques in the space environment (such as gravity gradient torque, atmospheric drag torque, solar pressure torque, residual magnetic torque, etc.) on the satellite attitude control system, adopts precise mathematical modeling and optimization algorithms, and optimizes 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 various embodiments of the present application are described below in conjunction with the accompanying drawings.

[0054] like Figures 1 to 6 As shown, a single-machine selection method for spacecraft attitude control of the present invention comprises:

[0055] Step S102: establishing an interference torque model based on the orbital parameters, physical characteristics and space environment of the spacecraft, and calculating the interference torque based on the interference torque model. The interference torque includes gravity gradient torque, atmospheric drag torque, solar pressure torque and residual magnetic torque.

[0056] Among them, the calculation methods of the interference torque include: calculating the gravity gradient torque based on the spacecraft position and the earth's gravitational field model; calculating the solar pressure torque based on the spacecraft surface reflection coefficient, solar radiation intensity and spacecraft attitude angle; calculating the atmospheric drag torque based on the spacecraft orbit and atmospheric density data; calculating the residual magnetic torque based on the spacecraft material, magnetic properties and changes in the magnetic field.

[0057] Among them, considering that the spacecraft is affected by the earth's gravitational field, the interference torque model calculates the torque caused by the gravity gradient, and based on the changes in orbital position and satellite attitude, the expression of the three-axis gravity gradient torque is derived by combining the inertia matrix and the attitude matrix. The conditions of orbital angular velocity and small attitude angle are specially considered to make the calculation more accurate.

[0058] Specifically, the calculation method of the gravity gradient torque is as follows:

[0059] Calculate the unit vector, r is the position vector of the spacecraft, and γ is the distance from the satellite to the center of the earth;

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

[0061] According to the orbit and attitude conditions, the three-axis gravity gradient torque is calculated using the above formula to obtain the three-axis torque (Tgx, Tgy, Tgz) in the spacecraft coordinate system.

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

[0063] Among them, based on the light pressure effect of solar radiation on the spacecraft, the interference torque model calculates the light pressure of the spacecraft on different illuminated surfaces, and further derives the calculation formula of the total light pressure moment by combining the spacecraft shape, reflection coefficient and solar radiation intensity.

[0064] Among them, the light pressure generated by solar radiation acts on the surface of the spacecraft, especially on the solar sail panels, which generates torque on the spacecraft. The calculation method of the solar light pressure torque is as follows:

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

[0066] According to the direction of solar radiation, calculate the angle θ between the normal unit vector n of the spacecraft's illuminated surface and the unit vector L of the light source direction;

[0067] The total area S of the force-bearing surface is calculated based on the shape of the spacecraft, and the light pressure is calculated based on the reflection coefficient η;

[0068] The light pressure moment generated on each surface is obtained by multiplying the force arm of each force-bearing surface by the light pressure, and the light pressure moment on all surfaces is summed up to obtain the total sunlight pressure moment. The calculation formula is as follows:

[0069] F=-ρ sun cosθ[(1-η)L+2ηcosθn].

[0070] Among them, the atmospheric drag torque is calculated by the atmospheric density and the relative speed of the spacecraft. The atmospheric drag torque usually has a greater impact on low-orbit satellites. The interference torque model calculates the aerodynamic torque generated by the impact of air molecules based on the atmospheric density, drag coefficient and the frontal area of ​​the spacecraft.

[0071] Specifically, the calculation method of the atmospheric drag moment is as follows:

[0072] Calculate the atmospheric density ρ a , which 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 according to the aerodynamic drag coefficient C D Calculate the torque generated by atmospheric drag using the following formula:

[0075] T a =ρ a C D A P ·l×(u×u) / 2.

[0076] Among them, this application is based on the interaction between the effective magnetic moment of the spacecraft and the local geomagnetic field. The interference torque model calculates the torque generated by the magnetic moment and uses the vector cross product form to describe the magnitude and direction of the residual magnetic torque.

[0077] Specifically, the calculation method of the residual magnetic torque is as follows:

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

[0079] The residual magnetic moment is calculated based on the geomagnetic field strength B at the satellite's location. The calculation formula for the residual magnetic moment is as follows:

[0080] Tm=M×B.

[0081] Step S104, obtaining torque data of the interference torque and the suppression capability of the attitude control unit to the interference torque, wherein the torque data includes torque distribution, torque magnitude and torque direction.

[0082] Step S104 is used to provide the necessary data basis for the selection of attitude control points, which establishes an optimized selection process for specific satellite missions by obtaining the interference torque and the attitude control unit's ability to suppress the interference torque.

[0083] Among them, the torque distribution is the distribution of the interference torque on each axis of the spacecraft in three-dimensional space.

[0084] Specifically, different types of disturbance torques (such as gravity gradient torque, sunlight pressure torque, etc.) may have different strengths and directions in different directions. For example, the main component of the gravity gradient torque may be on a specific axis, while the sunlight pressure torque may be related to the direction of the satellite surface normal.

[0085] Among them, the torque size reflects the strength of the interference torque and is an important reference indicator in the selection process of attitude control stand-alone machines.

[0086] Among them, torques in different directions will have different effects on the spacecraft's attitude, which requires a comprehensive evaluation in combination with the spacecraft's attitude dynamics.

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

[0088] Among them, the characteristics of the suppression capability include: Maximum output torque: the maximum reaction torque that each unit can provide to counteract the interference torque. If the unit cannot provide enough torque, the interference cannot be completely suppressed. Response time: the delay time from the unit receiving the control command to the actual output torque. The faster the response, the better the suppression capability of short-term high-frequency interference. Energy efficiency: the power consumption required to suppress interference, which directly affects the satellite energy budget. Cumulative error: the deviation 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, the single-machine control accuracy is the contribution of the attitude control unit to the attitude control accuracy; the single-machine stability is the ability of the control system to maintain stability when subjected to different interference torques; the 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 interference torque and the suppression performance of different units on these torques, thereby providing a basis for the subsequent selection of attitude control units.

[0091] Step S106: Based on the spacecraft attitude control requirements, torque data and the attitude control unit's ability to suppress interference torque, the corresponding attitude control unit combination and unit control parameters are selected using an optimization algorithm.

[0092] Among them, the selection basis of the attitude control unit is to select the most suitable attitude control unit combination by comparing the performance of different attitude control units in suppressing interference torque.

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

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

[0095] Among them, the spacecraft attitude control requirement is the attitude control accuracy that the spacecraft needs to achieve.

[0096] Among them, the attitude control unit includes a flywheel, a magnetic torquer, a micro-thruster, a gyroscope or a reaction wheel.

[0097] Among them, this step can select different types of stand-alone selection strategies according to optimization requirements, and the optimization requirements include maximizing attitude control accuracy, minimizing system energy consumption, improving attitude stability, or reducing total cost and load, etc. This application can use optimization algorithms to select different attitude control stand-alone combinations and corresponding stand-alone control parameters according to different requirements.

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

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

[0100] Furthermore, using the optimization algorithm to select the corresponding attitude control unit combination and unit control parameters also includes: evaluating the ability of the attitude control unit to suppress interference torque in different mission environments, and selecting the corresponding attitude control unit combination and unit control parameters based on the suppression ability, so as to comprehensively evaluate the comprehensive performance of the attitude control unit in the ability to suppress interference torque.

[0101] Among them, the comprehensive performance of the selected control unit combination in different mission environments is evaluated, and it is ensured that the selected structure can provide efficient attitude control under all predetermined orbital and environmental conditions.

[0102] Step S106 is used to find the optimal attitude control unit combination and its control parameters according to the influence of the interference 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 the spacecraft attitude control requirements, disturbance torque data and single-machine performance data, and uses an optimization algorithm to automatically select the optimal attitude control single-machine combination and its parameters. This method not only improves the scientific nature of the selection, but also effectively improves the accuracy, stability and adaptability of the satellite attitude control system, while reducing energy consumption and costs, and achieving comprehensive system optimization. This process has a wide range of applicability, especially in complex space mission environments, and can significantly enhance the performance of spacecraft.

[0104] Step S108, based on the attitude control unit combination, the corresponding unit control parameters and numerical simulation, simulate the operating attitude of the spacecraft in different orbits and space environments, and select the attitude control unit combination according to the simulation results, so as to verify and select the optimal attitude control unit combination and its control parameters through numerical simulation, so as to ensure that the spacecraft can effectively maintain the required attitude in different orbits and space environments.

[0105] Specifically, based on the attitude control stand-alone combination and numerical simulation, the simulation of the spacecraft's operating attitude in different orbits and space environments includes:

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

[0107] Based on the virtual simulation environment, the operating status of the spacecraft in different orbits and different space environments is simulated to verify the effect of the attitude control single-machine combination in suppressing interference torque under different mission conditions.

[0108] Furthermore, when the simulation results match the spacecraft attitude control requirements, the attitude control stand-alone combination is selected.

[0109] In step S108, a software simulation platform may be used for simulation, such as MATLAB / Simulink, STK and other software platforms.

[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 performs multi-scenario simulation by using numerical simulation tools (such as MATLAB, Simulink, etc.). The simulation test simulates the operation of satellites under different orbits and environmental conditions to evaluate the performance of the selection results in actual applications.

[0112] The method for selecting a spacecraft attitude control unit of the present invention improves the reliability and adaptability of the system design and reduces the risks and costs caused by unforeseen problems in practical applications by ensuring that the selected attitude control unit combination is not only optimal in theory but also can effectively operate in a real space environment through time verification through simulation.

[0113] The present invention also provides a single-machine selection system for spacecraft attitude control, including a data input module, an interference torque calculation module, a single-machine selection module and a simulation verification module. Among them, the data input module is used to obtain the orbital parameters, physical characteristics and space environment parameters of the spacecraft; the interference torque calculation module is used to establish an interference torque model, and calculate the interference torque based on the interference torque model, and the interference torque includes gravity gradient torque, atmospheric drag torque, solar pressure torque and residual magnetic torque; the single-machine selection module is used to obtain the torque data of the interference torque and the attitude control single machine's suppression ability for the interference torque, the torque data includes torque distribution, torque size and torque direction, and based on the spacecraft attitude control requirements, torque data and the attitude control single machine's suppression ability for the interference torque, the corresponding attitude control single machine combination and single machine control parameters are selected using an optimization algorithm; the simulation verification module is used to simulate the operating attitude of the spacecraft in different orbits and space environments based on the attitude control single machine combination, the corresponding single machine control parameters and numerical simulation, and select the attitude control single machine combination according to the simulation results.

[0114] Among them, the interference torque calculation module is also used to calculate different types of interference torques according to the input data, including gravity gradient torque, solar pressure torque, atmospheric drag torque and residual magnetic torque.

[0115] Among them, the unit selection module selects the most suitable attitude control unit according to the calculation results of the interference torque. This module evaluates the suppression ability of different control units to the interference torque, and selects the control unit with the best performance according to the performance parameters of each unit.

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

[0117] The simulation verification module constructs a virtual simulation environment to simulate the satellite's operating status in different orbits (such as low orbit, medium orbit, and high orbit) and different space environments (such as solar radiation, earth's magnetic field, etc.). During the simulation, the disturbance torque model and the selected attitude control unit parameters are input to simulate the satellite's attitude response and stability, and verify the effect 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 interference torque based on the 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 interference torque model and the attitude control unit combination, and simulate the operating status of the spacecraft in different orbits and different space environments based on the virtual simulation environment to verify the effect of the attitude control unit combination in suppressing the interference torque under different mission conditions.

[0120] The present invention also provides a computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the single-machine selection method for spacecraft attitude control as described in any one of Example 1 when executing the computer program.

[0121] In this specification, the same or similar parts between the various embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the product embodiment described later, since it corresponds to the method, the description is relatively simple, and the relevant parts can be referred to the partial description of the system embodiment.

[0122] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A single-machine selection method for spacecraft attitude control, characterized in that: include: Establishing an interference torque model based on the orbital parameters, physical characteristics and space environment of the spacecraft, and calculating the interference torque based on the interference torque model, wherein the interference torque includes gravity gradient torque, atmospheric drag torque, sunlight pressure torque and residual magnetic torque; Obtaining torque data of the interference torque and the ability of the attitude control unit to suppress the interference torque, wherein the torque data includes torque distribution, torque magnitude and torque direction; Based on the spacecraft attitude control requirements, the torque data and the ability of the attitude control unit to suppress the interference torque, the corresponding attitude control unit combination and the unit control parameters are selected by using an optimization algorithm; Based on the attitude control unit combination, the corresponding unit control parameters and numerical simulation, the operating attitude of the spacecraft in different orbits and space environments is simulated, and the attitude control unit combination is selected according to the simulation results.

2. The single-machine selection method for spacecraft attitude control according to claim 1 is characterized in that: The calculation method of the interference torque includes: Calculating the gravity gradient torque based on the spacecraft position and the Earth's gravitational field model; Calculating the solar pressure moment based on the spacecraft surface reflection coefficient, solar radiation intensity and spacecraft attitude angle; Calculating the atmospheric drag moment based on the spacecraft orbit, atmospheric density data, drag coefficient, and the frontal area of ​​the spacecraft; The residual magnetic torque is calculated based on the spacecraft material, magnetic properties and changes in the magnetic field.

3. The single-machine selection method for spacecraft attitude control according to claim 1, characterized in that: The ability of the attitude control unit to suppress the interference torque is evaluated and obtained based on the control accuracy of the unit, the response speed of the unit, the energy consumption of the unit and the stability of the unit.

4. The single-machine selection method for spacecraft attitude control according to claim 1 or 3, characterized in that: The optimization algorithm is used to select the corresponding attitude control unit combination and the unit control parameters, which also include: The ability of the attitude control unit to suppress the disturbance torque in different mission environments is evaluated, and a corresponding attitude control unit combination and the unit control parameters are selected based on the suppression ability.

5. The single-machine selection method for spacecraft attitude control according to claim 1, characterized in that: The selecting the attitude control stand-alone combination according to the simulation result comprises: In the case where the simulation result matches the spacecraft attitude control requirement, the attitude control stand-alone combination is selected.

6. The single-machine selection method for spacecraft attitude control according to claim 1, characterized in that: The simulation of the operating attitude of the spacecraft in different orbits and space environments based on the attitude control stand-alone combination and numerical simulation includes: Constructing a virtual simulation environment, and inputting a disturbance torque model and the attitude control unit combination; The operating states of the spacecraft in different orbits and different space environments are simulated based on the virtual simulation environment to verify the effect of the attitude control unit combination in suppressing the interference torque under different mission conditions.

7. A single-machine selection system for spacecraft attitude control, characterized in that: include: A data input module, wherein the data input module is used to obtain orbital parameters, physical characteristics of the spacecraft and space environment parameters of the space environment in which the spacecraft is located; An interference torque calculation module, the interference torque calculation module is used to establish an interference torque model and calculate the interference torque based on the interference torque model, the interference torque includes gravity gradient torque, atmospheric drag torque, sunlight pressure torque and residual magnetic torque; A stand-alone selection module, the stand-alone selection module is used to obtain the torque data of the interference torque and the suppression capability of the attitude control stand-alone to the interference torque, the torque data including the torque distribution, the torque magnitude and the torque direction, and based on the spacecraft attitude control requirements, the torque data and the suppression capability of the attitude control stand-alone to the interference torque, select the corresponding attitude control stand-alone combination and stand-alone control parameters by using an optimization algorithm; A simulation verification module, wherein the simulation verification module is used to simulate the operating attitude of the spacecraft in different orbits and space environments based on the attitude control single-machine combination, the corresponding single-machine control parameters and numerical simulation, and select the attitude control single-machine combination according to the simulation results.

8. The spacecraft attitude control stand-alone selection system according to claim 7, characterized in that: The stand-alone machine selection module is also used to evaluate and obtain the ability of the attitude control stand-alone machine to suppress the interference torque based on the stand-alone machine control accuracy, the stand-alone machine response speed, the stand-alone machine energy consumption, and the stand-alone machine stability.

9. The spacecraft attitude control stand-alone selection system according to claim 7, characterized in that: The simulation verification module is also used to construct a virtual simulation environment, input the interference torque model and the attitude control unit combination, and simulate the operating status of the spacecraft in different orbits and different space environments based on the virtual simulation environment to verify the effect of the attitude control unit combination in suppressing interference torque under different mission conditions.

10. 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, the single-machine selection method for spacecraft attitude control according to any one of claims 1 to 6 is implemented.

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