Coplanar arrangement method, system and computer readable medium for satellite thrusters

Abstract

The application relates to a coplanar layout method, system and computer readable medium of a satellite thruster, the satellite thruster comprising a plurality of attitude control thrusters and a plurality of orbit control thrusters, the method comprising: simulating control of a satellite according to satellite parameters and preset thruster layout parameters to obtain a simulation control result of the satellite; generating thruster coplanar layout parameters according to the simulation control result; and mounting the plurality of attitude control thrusters and the plurality of orbit control thrusters coplanarly on a same satellite cabin plate according to the thruster coplanar layout parameters. The application can reduce the complexity of a satellite pipeline layout space and meet the requirements of deep space satellites for high reliability, low complexity and easy integration.

Description

Technical Field

[0001] This application mainly relates to the field of aircraft overall design technology, and specifically to a coplanar layout method, system and computer-readable medium for a satellite thruster. Background Technology

[0002] In deep space exploration missions, satellites need to meet complex orbit control requirements, which typically require propulsion systems with high reliability and multi-stage thrust output capabilities to achieve precise orbital maneuvers and attitude adjustments.

[0003] Currently, most satellite propulsion systems adopt a non-coplanar mounting method, such as attitude control thrusters and orbit control thrusters being distributed and mounted on different satellite panels. This layout increases the complexity of pipeline layout, the difficulty of overall satellite integration, and the difficulty of redundancy backup, which is not conducive to the high reliability and simplicity design of deep space satellites.

[0004] The non-coplanar mounting layout of satellite thrusters in existing propulsion systems leads to high spatial complexity in satellite piping layout, making it difficult to meet the requirements of deep space satellites for high reliability, low complexity, and easy integration. Therefore, a more optimized thruster layout scheme is urgently needed. Summary of the Invention

[0005] The technical problem to be solved by this application is to provide a coplanar layout method, system and computer-readable medium for satellite thrusters, which can reduce the complexity of satellite pipeline layout space and meet the requirements of deep space satellites for high reliability, low complexity and easy integration.

[0006] The technical solution adopted in this application to solve the above-mentioned technical problems is a coplanar layout method for satellite thrusters. The satellite thrusters include multiple attitude control thrusters and multiple orbit control thrusters. The method includes: simulating the control of the satellite based on satellite parameters and preset thruster layout parameters to obtain the simulated control results of the satellite; generating thruster coplanar layout parameters based on the simulated control results; and coplanarly mounting the multiple attitude control thrusters and the multiple orbit control thrusters on the same satellite module according to the thruster coplanar layout parameters.

[0007] In one embodiment of this application, the satellite is simulated and controlled based on satellite parameters and preset thruster layout parameters to obtain the simulated control results of the satellite. This includes: generating initial thruster coplanar layout parameters based on the satellite parameters and the preset thruster layout parameters; simulating the satellite performing orbit control and / or attitude control tasks based on the Monte Carlo method and the initial thruster coplanar layout parameters to obtain the simulated control results, wherein the simulated control results include closed-loop attitude angular velocity and / or closed-loop attitude angle.

[0008] In one embodiment of this application, generating thruster coplanar layout parameters based on the simulation control results includes: in response to the simulation control results being within a preset threshold range, using the initial thruster coplanar layout parameters corresponding to the simulation control results as the thruster coplanar layout parameters; or in response to the simulation control results being outside the preset threshold range, regenerating the initial thruster coplanar layout parameters, and resimulating the satellite performing orbit control and / or attitude control tasks.

[0009] In one embodiment of this application, the satellite parameters include one or any combination of the following: overall satellite size, overall satellite inertia, center of mass deviation, and thrust value; the preset thruster layout parameters include one or any combination of the following: tilt angle of the attitude control thruster, layout position of the attitude control thruster, and layout position of the orbit control thruster.

[0010] In one embodiment of this application, the coplanar layout parameters of the thrusters include: A attitude control thrusters, where A is an even number greater than or equal to eight, each pair of attitude control thrusters forms an attitude control thruster group, one of the attitude control thrusters in each attitude control thruster group serves as the main attitude control thruster and the other serves as the backup attitude control thruster, all attitude control thruster groups are evenly distributed on the edge of the satellite module, and each attitude control thruster is tilted at a preset angle.

[0011] In one embodiment of this application, the coplanar layout parameters of the thrusters include: B orbital control thrusters, where B is an even number greater than or equal to four, with each pair of orbital control thrusters forming an orbital control thruster group, one of which serves as the main orbital control thruster and the other as a backup orbital control thruster in each orbital control thruster group, and all orbital control thruster groups are evenly distributed on a ring constructed with the centroid of the satellite module as a reference and according to a preset radius.

[0012] In one embodiment of this application, the satellite module is rectangular, and the preset radius is less than or equal to half the length of the shorter side of the satellite module.

[0013] In one embodiment of this application, the satellite thruster satisfies one or any combination of the following conditions: the thrust value is the same in the same attitude control thruster group; the thrust value is the same in the same orbit control thruster group; the thrust values ​​are the same or different between different attitude control thruster groups; and the thrust values ​​are the same or different between different orbit control thruster groups.

[0014] To address the aforementioned technical problems, this application also proposes a coplanar layout system for a satellite thruster, comprising: a memory for storing instructions executable by a processor; and a processor for executing the instructions to implement the coplanar layout method for the satellite thruster as described above.

[0015] To address the aforementioned technical problems, this application also proposes a computer-readable medium storing computer program code, which, when executed by a processor, implements the coplanar layout method of the satellite thrusters described above.

[0016] The technical solution of this application simulates satellite control using preset parameters and generates and optimizes the coplanar layout parameters of the thrusters, achieving coplanar installation of the attitude control thrusters and orbit control thrusters on the satellite module, thus reducing the complexity of the satellite piping layout space. Simulation verification ensures that the thruster layout meets control requirements, improves the redundancy of the thruster system, and facilitates thruster installation and maintenance. With a simple and reliable thrust system layout, it can achieve multi-stage thrust output in multiple batches, providing stable attitude control and orbit control thrust output under different orbit control directions and times. This application, while significantly simplifying the layout, meets the attitude and orbit control requirements of deep-space satellites and lays the foundation for the subsequent construction of modular satellite propulsion modules. Attached Figure Description

[0017] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, the specific embodiments of this application will be described in detail below with reference to the accompanying drawings, wherein:

[0018] Figure 1 This is an exemplary flowchart of a coplanar layout method for a satellite thruster according to an embodiment of this application;

[0019] Figure 2 This is a schematic diagram of satellite thrusters coplanarly mounted on the same satellite module in one embodiment of this application;

[0020] Figure 3 This is an exemplary flowchart of a coplanar layout method for a satellite thruster according to another embodiment of this application;

[0021] Figure 4 This is a flowchart of attitude control and multi-stage orbit control for a deep space satellite with coplanar installation of satellite thrusters in one embodiment of this application;

[0022] Figure 5 This is a schematic diagram of the closed-loop attitude angle calculated during the simulated control of a satellite in one embodiment of this application;

[0023] Figure 6 This is a schematic diagram of the closed-loop attitude angular velocity calculated during the simulated control of a satellite in one embodiment of this application;

[0024] Figure 7 This is a system block diagram of a coplanar layout system of a satellite thruster according to an embodiment of this application.

[0025] Explanation of reference numerals in the accompanying drawings for specific embodiments:

[0026] 210. Attitude control thruster;

[0027] 220. Rail-controlled thruster;

[0028] 230. Satellite panel;

[0029] 240. Circular ring. Detailed Implementation

[0030] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, the specific embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0031] Many specific details are set forth in the following description in order to provide a full understanding of this application. However, this application may also be implemented in other ways different from those described herein, and therefore this application is not limited to the specific embodiments disclosed below.

[0032] As illustrated in this application, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" do not specifically refer to the singular and may also include the plural. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0033] Flowcharts are used in this application to illustrate the operations performed by the system according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, various steps can be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more steps may be removed from these processes.

[0034] This application proposes a coplanar layout method for satellite thrusters, which includes multiple attitude control thrusters and multiple orbit control thrusters. This application is equivalent to a coplanar installation method for deep space satellite attitude control thrusters and orbit control thrusters. Applicable application scenarios include: complex multi-batch, multi-parameter orbit control missions of deep space satellites that require multi-stage thrust output support with system reliability; satellites that require modular assembly and miniaturization design; and satellites that require optimized propulsion pipeline layout design, etc.

[0035] The coplanar layout method for satellite thrusters described in this application can operate at a ground station, such as within the controller of a ground station computer, or on a cloud platform. When the coplanar layout method for satellite thrusters operates on a cloud platform, data from the ground station computer and the cloud platform interact via a wireless network. Exemplarily, the cloud platform may include a private cloud, public cloud, hybrid cloud, community cloud, distributed cloud, interconnected cloud, and multiple clouds, or any combination thereof. This application does not limit the operating environment of the coplanar layout method for satellite thrusters.

[0036] Figure 1 This is an exemplary flowchart of a coplanar layout method for a satellite thruster according to an embodiment of this application, with reference to... Figure 1 As shown, the coplanar layout method of the satellite thruster in this embodiment includes the following steps:

[0037] Step S110: Simulate and control the satellite based on the satellite parameters and preset thruster layout parameters to obtain the simulated control results of the satellite.

[0038] Step S120: Generate thruster coplanar layout parameters based on simulation control results.

[0039] Step S130: Based on the thruster coplanar layout parameters, multiple attitude control thrusters and multiple orbit control thrusters are coplanarly installed on the same satellite module.

[0040] The following details steps S110 to S130:

[0041] In step S110, the satellite is simulated and controlled based on satellite parameters and preset thruster layout parameters to obtain the simulated control results. For example, simulating satellite control based on preset parameters allows for early verification of the thruster layout's rationality, enabling optimization of the thruster's installation location and configuration. This reduces design risks in actual engineering projects and improves the control accuracy and reliability of the propulsion system.

[0042] In some embodiments, satellite parameters include one or any combination of the following: overall satellite dimensions (i.e., overall satellite structural dimensions), overall satellite inertia, center of mass deviation, and thrust value (i.e., thrust magnitude). Preset thruster layout parameters include one or any combination of the following: tilt angle of the attitude control thruster, layout position of the attitude control thruster, and layout position of the orbit control thruster.

[0043] For example, by pre-designing satellite parameters and thruster layout parameters, the matching accuracy between the thruster layout and the satellite's physical characteristics can be improved, effectively enhancing the adaptability and reliability of the control system and providing a foundation for subsequent optimization of the thruster coplanar layout.

[0044] In some embodiments, the satellite is simulated and controlled based on satellite parameters and preset thruster layout parameters to obtain the simulated control results of the satellite, including:

[0045] Initial thruster coplanar layout parameters are generated based on satellite parameters and preset thruster layout parameters;

[0046] The satellite's orbit control and / or attitude control tasks are simulated using the Monte Carlo method and initial thruster coplanar layout parameters to obtain simulation control results, including closed-loop attitude angular velocity and / or closed-loop attitude angle.

[0047] For example, the Monte Carlo method combines target parameters (such as initial thruster coplanar layout parameters) within a possible range, then selects the optimal parameter combination by evaluating the effect of each set of parameters. The parameter combination includes the thruster's tilt angle and layout position. In practical applications, the Monte Carlo method can be incorporated into the mathematical model of a satellite control system, allowing the design of installation parameters under different satellite parameters to be implemented through the satellite control system.

[0048] This application generates an initial coplanar layout scheme by combining satellite parameters and preset thruster layout parameters, and uses the Monte Carlo method to simulate the satellite performing the mission. This allows for a comprehensive and reliable evaluation of the control performance of the thruster layout. Parameters such as closed-loop attitude angular velocity and closed-loop attitude angle are used to quantitatively evaluate control accuracy and control stability, which facilitates layout optimization.

[0049] In step S120, thruster coplanar layout parameters are generated based on simulation control results. In some embodiments, this includes:

[0050] If the simulation control results are within a preset threshold range, the initial thruster coplanar layout parameters corresponding to the simulation control results are used as the thruster coplanar layout parameters; or, if the simulation control results are outside the preset threshold range, the initial thruster coplanar layout parameters are regenerated, and the satellite is resimulated to perform orbit control and / or attitude control tasks.

[0051] For example, this application automatically judges and optimizes the simulation control results by setting a preset threshold range, which can efficiently determine the thruster coplanar layout parameters that meet the accuracy requirements. When the simulation control results are within the preset threshold range, the optimal parameters are directly output; when the simulation control results exceed the preset threshold range, an iterative process of regeneration and simulation verification is automatically executed. Through a closed-loop feedback mechanism, the layout parameters are automatically optimized, and a highly reliable and adaptable thruster coplanar layout scheme can be obtained.

[0052] The following example illustrates the process by which this application obtains the optimal coplanar layout parameters of the thruster.

[0053] Figure 3 This is an exemplary flowchart of a coplanar layout method for a satellite thruster according to another embodiment of this application. (See reference...) Figure 3As shown, in step S310, satellite parameters are obtained, including the overall satellite size, overall satellite inertia, center of mass deviation, and thrust value. In step S320, preset thruster layout parameters are obtained, including the tilt angle of the attitude control thruster, the layout position of the attitude control thruster, and the layout position of the orbit control thruster. In step S330, the satellite parameters are used as characteristic parameters of the controlled object, and the preset thruster layout parameters are used as installation parameters. The data is traversed using the mathematical model of the satellite control system. In step S340, the data is traversed using the Monte Carlo method. In step S350, the optimal coplanar layout parameters of the thrusters are obtained through an optimization algorithm.

[0054] The remaining steps of this application will now be described.

[0055] In step S130, multiple attitude control thrusters and multiple orbit control thrusters are coplanarly mounted on the same satellite module according to the thruster coplanar layout parameters. For example, a robotic arm can be used to install the attitude control thrusters and orbit control thrusters. This application achieves optimized satellite and pipeline layout through the coplanar mounting of attitude control thrusters and orbit control thrusters, which is beneficial for modular satellite assembly and suitable for satellite miniaturization design.

[0056] Figure 2 This is a schematic diagram of satellite thrusters coplanarly mounted on the same satellite module in one embodiment of this application. (Reference) Figure 2 As shown, in some embodiments, the coplanar layout parameters of the thrusters include: A attitude control thrusters 210, where A is an even number greater than or equal to eight (e.g., ...). Figure 2 The diagram shows eight attitude control thrusters (F1, F2, F3, F4, F5, F6, F7, and F8), each set to 5 N, where N represents Newtons. Every two attitude control thrusters form a group (e.g., ...). Figure 2 F1 and F5 in the series are a group of attitude control thrusters. In each attitude control thruster group, one of them serves as the main attitude control thruster and the other serves as the backup attitude control thruster. All attitude control thruster groups are evenly distributed on the edge of the satellite deck, and each attitude control thruster is tilted at a preset angle of 210°.

[0057] For example, this application can improve the reliability of the satellite control system by configuring the attitude control thruster group as a primary and backup unit. By grouping multiple attitude control thrusters 210, each group containing a primary and backup dual-redundant thruster, and by tilting these attitude control thrusters 210 at a preset angle and uniformly installing them on the edge of the same satellite panel 230, this configuration can achieve high-reliability operation of the thruster system and ensure balanced control torque in all directions.

[0058] Continue to refer to Figure 2 As shown, in some embodiments, the coplanar layout parameters of the thrusters include: B orbital control thrusters 220, where B is an even number greater than or equal to four (e.g., ...). Figure 2 The diagram shows four orbit control thrusters, corresponding to F9, F10, F11, and F12 respectively. Each pair of orbit control thrusters forms an orbit control thruster group (e.g., Figure 2 F9 and F11 in the group are a group of orbit control thrusters. In each orbit control thruster group, one of them serves as the main orbit control thruster and the other serves as the backup orbit control thruster. All orbit control thruster groups are evenly distributed on a ring 240 constructed with the centroid of the satellite panel 230 as the reference and according to a preset radius.

[0059] For example, this application can improve the reliability of the satellite control system by configuring the orbital control thruster group as a primary and backup. Figure 2 The four orbital control thrusters shown (corresponding to F9-F12) are all set to 20N, where N represents Newton. Figure 2 The four orbit control thrusters are located on a ring 240 constructed with the centroid of the satellite module 230 as the reference and according to a preset radius (i.e., around the satellite's centroid). This arrangement allows for three combinations of orbit control thrusters: the first combination is F9 and F11; the second combination is F10 and F12; and the third combination is F9, F10, F11, and F12. The arrangement of the orbit control thrusters 220 in this application does not generate significant offset torque interference.

[0060] This application ensures that a single-point failure of the track control thruster 220 does not affect the track control function through a primary and backup redundancy design. The uniform circular layout ensures the symmetry of the thrust direction and control accuracy, forming an optimal layout scheme for control accuracy and propulsion efficiency.

[0061] In some embodiments, the satellite module 230 is rectangular, comprising a short side and a long side, and a preset radius is less than or equal to half the length of the short side of the satellite module 230. For example, Figure 2 The satellite module 230 shown is roughly rectangular, and the preset radius of the annulus 240 is 350 mm, where mm represents millimeters. In practical applications, the sides of the rectangular satellite module 230 are all equal, so the preset radius can be set to be less than or equal to half the side length.

[0062] This application ensures that the installation position of the orbit control thruster 220 is always within the effective structural range of the satellite panel 230 by limiting the radius of the annulus on the satellite panel 230 to less than half the length of the short side of the satellite panel 230. The thruster layout on the satellite panel 230 is compact, which improves the space utilization of the satellite panel 230.

[0063] In some embodiments, the satellite thruster satisfies one or any combination of the following conditions:

[0064] The thrust values ​​are the same in the same attitude control thruster group;

[0065] The thrust values ​​are the same in the same track control thruster group;

[0066] The thrust values ​​may be the same or different between different attitude control thruster groups;

[0067] The thrust values ​​of different track control thruster groups may be the same or different.

[0068] For example, by configuring the thrust values ​​of the attitude control thruster 210 and the orbit control thruster 220, a multi-stage thrust output scheme can be generated during orbit control, which improves the reliability of orbit control missions, meets the complex multi-batch and multi-parameter orbit control requirements of deep space satellites, and achieves a balance between control accuracy, mission adaptability and energy efficiency in the satellite propulsion system.

[0069] This combination Figure 2 This application describes an embodiment in which multiple attitude control thrusters 210 and multiple orbit control thrusters 220 are coplanarly mounted on the same satellite module 230.

[0070] refer to Figure 2 As shown, the deep space satellite's satellite module 230 is equipped with eight 5N attitude control thrusters 210 for attitude control. The eight attitude control thrusters correspond to F1, F2, F3, F4, F5, F6, F7, and F8, respectively. Each attitude control thruster is tilted at a certain angle (e.g., 25°) to generate sufficient attitude control torque. Every two attitude control thrusters form a group and serve as primary and backup thrusters to each other. It is also equipped with four 20N orbit control thrusters 220 for orbit control. The four orbit control thrusters correspond to F9, F10, F11, and F12, respectively. The orbit control thrusters are installed without tilting to generate maximum orbit control efficiency. Every two orbit control thrusters form a group and serve as primary and backup thrusters to each other. These thrusters are coplanarly mounted on the satellite panel 230 at the bottom of the satellite. Among them, eight 5N attitude control thrusters 210 are mounted on the edge of the satellite panel 230, and four 20N orbit control thrusters 220 are mounted on a ring 240 with the centroid of the bottom plate φ=350mm. The line connecting two opposite thrusters is parallel to the two sides of the bottom plate.

[0071] In practical applications, the following can be adopted: Figure 2 The satellite employs a configuration where eight 5N attitude control thrusters 210 (four primary or backup 5N attitude control thrusters are used during normal operation) and four 20N orbit control thrusters 220, or two 20N orbit control thrusters 220, or four 5N orbit control thrusters 220, are installed on the same satellite module 230. During orbit control thrust output, the deep-space satellite can generate multiple rated thrust levels through different thruster combinations, such as 80N, 40N, and 20N.

[0072] The following example illustrates the process of attitude and orbit control for a deep-space satellite with its thrusters mounted in a coplanar configuration.

[0073] Figure 4 This is a flowchart illustrating the attitude control and multi-stage orbit control of a deep-space satellite with its thrusters coplanarly mounted, according to one embodiment of this application. (Reference) Figure 4 As shown, in step S410, satellite parameters are obtained, including the overall satellite dimensions, overall satellite inertia, and center of mass deviation provided by the satellite structure system, as well as the thrust output value of the selected thrusters in the satellite control system. In step S420, the satellite control system uses a mathematical model and Monte Carlo method to iterate through different combinations of satellite parameters and preset thruster layout parameters within each parameter range, and automatically calculates the simulated control results of the satellite (e.g., closed-loop attitude angular velocity and closed-loop attitude angle). In step S430, based on the simulated control results, a comprehensive assessment is performed. Considering factors such as the stability of orbit control thrust output, attitude control stability, attitude control accuracy, and system reliability, an optimization algorithm is used to optimize the installation layout scheme. In step S440, the optimal coplanar layout parameters of the thrusters are obtained. In step S450, the thruster control scheme is assigned by command. In steps S461, S462, S463, and S464, different combinations of thruster usage schemes are output respectively to achieve three-stage thrust output of 80N orbit control, 40N orbit control, and 20N orbit control, as well as a 5N attitude control scheme, ensuring that the satellite system has sufficient reliability.

[0074] Continue to refer to Figure 2 and Figure 4 As shown, in step S461, an 80N track control scheme is output, using... Figure 2 The four track control thrusters (corresponding to F9, F10, F11, and F12) are used; in step S462, a 40N track control scheme is output, using... Figure 2 The two track control thrusters (corresponding to F9 and F11, or F10 and F12) are used; in step S463, a 20N track control scheme is output, using... Figure 2 The four attitude control thrusters (corresponding to F1, F2, F3, F4, or F5, F6, F7, F8) are used; in step S464, a 5N attitude control scheme is output, which is used respectively. Figure 2 The eight attitude control thrusters (corresponding to F1, F2, F3, F4, F5, F6, F7, and F8) are included.

[0075] For example, when multiple attitude control thrusters are used to perform orbit control tasks, attitude adjustments must be made as needed within the same control cycle. That is, both attitude control and orbit control tasks are completed within one control cycle. During orbit control, multiple attitude control thrusters perform attitude control with backups, enhancing the reliability of the satellite system.

[0076] Figure 5This is a schematic diagram of the closed-loop attitude angle calculated during the simulated control of a satellite in one embodiment of this application. Figure 6 This is a schematic diagram of the closed-loop attitude angular velocity calculated during the simulated control of a satellite in one embodiment of this application. (Reference) Figure 5 and Figure 6 As shown, exemplarily, this application mounts satellite thrusters coplanarly on the same satellite module and simulates satellite control. Figure 5 The diagram shows the changes in the closed-loop attitude angle, which reflects the accuracy of satellite control. Figure 6 The diagram shows the changes in closed-loop attitude angular velocity, which reflects the stability of satellite control. Figure 5 and Figure 6 The data shown in the figure are mostly within the range, indicating that the coplanar layout scheme of the thruster in this application is effective.

[0077] The technical solution of this application simulates satellite control using preset parameters and generates and optimizes the coplanar layout parameters of the thrusters, achieving coplanar installation of the attitude control thrusters and orbit control thrusters on the satellite module, thus reducing the complexity of the satellite piping layout space. Simulation verification ensures that the thruster layout meets control requirements, improves the redundancy of the thruster system, and facilitates thruster installation and maintenance. With a simple and reliable thrust system layout, it can achieve multi-stage thrust output in multiple batches, providing stable attitude control and orbit control thrust output under different orbit control directions and times. This application, while significantly simplifying the layout, meets the attitude and orbit control requirements of deep-space satellites and lays the foundation for the subsequent construction of modular satellite propulsion modules.

[0078] This application also includes a coplanar layout system for a satellite thruster, comprising a memory and a processor. The memory stores instructions executable by the processor; the processor executes these instructions to implement the coplanar layout method for the satellite thruster described above.

[0079] Figure 7 This is a system block diagram of a coplanar layout system for a satellite thruster according to an embodiment of this application. (Reference) Figure 7As shown, the coplanar layout system 700 of the satellite thruster may include an internal communication bus 701, a processor 702, a read-only memory (ROM) 703, a random access memory (RAM) 704, and a communication port 705. The coplanar layout system 700 of the satellite thruster may also include a hard disk 706. The internal communication bus 701 enables data communication between the components of the coplanar layout system 700 of the satellite thruster. The processor 702 can perform judgments and issue prompts. In some embodiments, the processor 702 may consist of one or more processors. The communication port 705 enables data communication between the coplanar layout system 700 of the satellite thruster and external systems. In some embodiments, the coplanar layout system 700 of the satellite thruster can send and receive information and data from a network through the communication port 705. The coplanar layout system 700 of the satellite thruster may also include different types of program storage units and data storage units, such as a hard disk 706, a read-only memory (ROM) 703, and a random access memory (RAM) 704, capable of storing various data files used for computer processing and / or communication, as well as possible program instructions executed by the processor 702. The processor executes these instructions to implement the main part of the method. The results of the processor processing are transmitted to the user equipment via a communication port and displayed on the user interface.

[0080] The above-described coplanar layout method for satellite thrusters can be implemented as a computer program, stored in hard disk 706, and loaded into processor 702 for execution to implement the coplanar layout method for satellite thrusters of this application.

[0081] This application also includes a computer-readable medium storing computer program code that, when executed by a processor, implements the coplanar layout method of the satellite thrusters described above.

[0082] When the coplanar layout method of a satellite thruster is implemented as a computer program, it can also be stored as an article of manufacture in a computer-readable storage medium. For example, a computer-readable storage medium may include, but is not limited to, magnetic storage devices (e.g., hard disks, floppy disks, magnetic stripes), optical discs (e.g., compact discs (CDs), digital multifunction discs (DVDs)), smart cards, and flash memory devices (e.g., electrically erasable programmable read-only memory (EPROM), cards, sticks, key drives). Furthermore, the various storage media described herein can represent one or more devices and / or other machine-readable media for storing information. The term "machine-readable medium" may include, but is not limited to, wireless channels and various other media (and / or storage media) capable of storing, containing, and / or carrying code and / or instructions and / or data.

[0083] It should be understood that the embodiments described above are merely illustrative. The embodiments described herein may be implemented in hardware, software, firmware, middleware, microcode, or any combination thereof. For hardware implementation, the processor may be implemented within one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, and / or other electronic units designed to perform the functions described herein, or combinations thereof.

[0084] Some aspects of this application can be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The aforementioned hardware or software may be referred to as a "data block," "module," "engine," "unit," "component," or "system." The processor may be one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. Furthermore, aspects of this application may manifest as computer products residing in one or more computer-readable media, including computer-readable program code. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, magnetic tapes, etc.), optical discs (e.g., compressed CDs, digital multifunction DVDs, etc.), smart cards, and flash memory devices (e.g., cards, sticks, key drives, etc.).

[0085] A computer-readable medium may contain a propagated data signal containing computer program code, for example, on baseband or as part of a carrier wave. This propagated signal may take various forms, including electromagnetic, optical, and so on, or suitable combinations thereof. A computer-readable medium can be any computer-readable medium other than a computer-readable storage medium, which can be connected to an instruction execution system, apparatus, or device to enable communication, propagation, or transmission of a program for use. The program code located on the computer-readable medium can be propagated through any suitable medium, including radio, cable, fiber optic cable, radio frequency signals, or similar media, or any combination of the above media.

[0086] The basic concepts have been described above. Obviously, for those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application, and therefore remain within the spirit and scope of the exemplary embodiments of this application.

[0087] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0088] In some embodiments, numbers describing the quantity of components and attributes are used. It should be understood that such numbers used in the description of embodiments are modified in some examples with the terms "approximately," "approximately," or "generally." Unless otherwise stated, "approximately," "approximately," or "generally" indicates that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in this application are approximate values, which may be changed according to the characteristics required by individual embodiments. In some embodiments, numerical parameters should take into account specified significant digits and employ a general method of digit preservation. Although the numerical ranges and parameters used to confirm their breadth of range in some embodiments of this application are approximate values, in specific embodiments, such numerical values ​​are set as precisely as feasible.

Claims

1. A method for coplanar layout of satellite thrusters, characterized in that, The satellite thruster includes multiple attitude control thrusters and multiple orbit control thrusters, and the method includes: The simulation control of the satellite is performed based on satellite parameters and preset thruster layout parameters to obtain the simulation control results of the satellite. This includes: generating initial thruster coplanar layout parameters based on the satellite parameters and preset thruster layout parameters; and simulating the satellite performing orbit control and / or attitude control tasks based on the Monte Carlo method and the initial thruster coplanar layout parameters to obtain the simulation control results, which include closed-loop attitude angular velocity and / or closed-loop attitude angle. Generating thruster coplanar layout parameters based on the simulation control results includes: in response to the simulation control results being within a preset threshold range, using the initial thruster coplanar layout parameters corresponding to the simulation control results as the thruster coplanar layout parameters; or in response to the simulation control results being outside the preset threshold range, regenerating the initial thruster coplanar layout parameters, and resimulating the satellite performing orbit control and / or attitude control tasks; According to the coplanar layout parameters of the thrusters, the multiple attitude control thrusters and the multiple orbit control thrusters are coplanarly mounted on the same satellite module; when the orbit control thrust is output, the rated multi-stage thrust is generated by different combinations of thrusters.

2. The coplanar layout method for satellite thrusters as described in claim 1, characterized in that, The satellite parameters include one or any combination of the following: overall satellite size, overall satellite inertia, center of mass deviation, and thrust value; The preset thruster layout parameters include one or any combination of the tilt angle of the attitude control thruster, the layout position of the attitude control thruster, and the layout position of the orbit control thruster.

3. The coplanar layout method for satellite thrusters as described in claim 1, characterized in that, The coplanar layout parameters of the thrusters include: A attitude control thrusters, where A is an even number greater than or equal to eight. Every two attitude control thrusters form an attitude control thruster group. In each attitude control thruster group, one of them serves as the main attitude control thruster and the other serves as the backup attitude control thruster. All attitude control thruster groups are evenly distributed on the edge of the satellite module, and each attitude control thruster is tilted at a preset angle.

4. The coplanar layout method for satellite thrusters as described in claim 3, characterized in that, The coplanar layout parameters of the thrusters include: B orbital control thrusters, where B is an even number greater than or equal to four. Every two orbital control thrusters form an orbital control thruster group. In each orbital control thruster group, one of them serves as the main orbital control thruster and the other serves as the backup orbital control thruster. All orbital control thruster groups are evenly distributed on a ring constructed with the centroid of the satellite module as the reference and according to a preset radius.

5. The coplanar layout method for satellite thrusters as described in claim 4, characterized in that, The satellite module is rectangular, and the preset radius is less than or equal to half the length of the shorter side of the satellite module.

6. The coplanar layout method for satellite thrusters as described in claim 4, characterized in that, The satellite thruster satisfies one or any combination of the following conditions: The thrust values ​​are the same in the same attitude control thruster group; The thrust values ​​are the same in the same track control thruster group; The thrust values ​​may be the same or different between different attitude control thruster groups; The thrust values ​​of different track control thruster groups may be the same or different.

7. A coplanar layout system for a satellite thruster, characterized in that, include: Memory is used to store instructions executed by the processor; A processor for executing the instructions to implement the coplanar layout method of the satellite thruster as described in any one of claims 1-6.

8. A computer-readable medium storing computer program code, characterized in that, The computer program code, when executed by a processor, implements the coplanar layout method of the satellite thruster as described in any one of claims 1-6.

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