Satellite thruster coplanar layout method and system and computer readable medium

Abstract

The invention relates to a coplanar layout method and system for satellite thrusters and a computer readable medium, the satellite thrusters comprise a plurality of attitude control thrusters and a plurality of orbit control thrusters, and the method comprises the following steps: simulating and controlling a satellite according to satellite parameters and preset thruster layout parameters to obtain a simulation control result of the satellite; thruster coplanar layout parameters are generated according to the simulation control result; and the multiple attitude control thrusters and the multiple orbit control thrusters are installed on the same satellite deck in a coplanar mode according to the thruster coplanar layout parameters. According to the invention, the complexity of a satellite pipeline layout space can be reduced, and the requirements of a deep space satellite for high reliability, low complexity and easy integration can be met.

Description

TECHNICAL FIELD

[0001] The present application mainly relates to the technical field of aircraft general design, in particular to a satellite thruster coplanar layout method, system and computer readable medium. BACKGROUND

[0002] In deep space exploration missions, satellites need to meet complex orbit control requirements, usually requiring the propulsion system to have high reliability and multi-stage thrust output capability to achieve precise orbit maneuvering and attitude adjustment.

[0003] Most of the current satellite propulsion systems use non-coplanar installation methods, such as attitude control thrusters and orbit control thrusters installed separately on different satellite cabin panels. This layout method increases the complexity of pipeline layout, the difficulty of satellite integration, and the difficulty of redundancy backup, which is not conducive to the high-reliability and simple design of deep space satellites.

[0004] The non-coplanar installation layout of satellite thrusters in existing propulsion systems can cause high complexity of satellite pipeline layout space, making it difficult to meet the needs of deep space satellites for high reliability, low complexity, and easy integration, and there is an urgent need for a more optimized thruster layout scheme. SUMMARY

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

[0006] The technical solution adopted by the present application to solve the above technical problem is a satellite thruster coplanar layout method, 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 installing the plurality of attitude control thrusters and the plurality of orbit control thrusters coplanarly on the same satellite cabin panel according to the thruster coplanar layout parameters.

[0007] In an embodiment of the present application, simulating control of a satellite according to satellite parameters and preset thruster layout parameters to obtain a simulation control result of the satellite comprises: generating initial thruster coplanar layout parameters according to the satellite parameters and the preset thruster layout parameters; and simulating the satellite performing an orbit control task and / or an attitude control task according to a Monte Carlo method and the initial thruster coplanar layout parameters to obtain the simulation control result, the simulation control result comprising a closed-loop attitude angular velocity and / or a closed-loop attitude angle.

[0008] In an embodiment of the present application, the thruster coplanar layout parameter is generated according to the simulation control result, including: in response to the simulation control result being within a preset threshold range, taking the initial thruster coplanar layout parameter corresponding to the simulation control result as the thruster coplanar layout parameter; or in response to the simulation control result being outside the preset threshold range, re-generating the initial thruster coplanar layout parameter, and re-simulating the satellite to perform the orbit control task and / or the attitude control task.

[0009] In an embodiment of the present application, the satellite parameters include one or any combination of the following: overall satellite size, overall satellite inertia, mass center deviation, and thruster value; and 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 an embodiment of the present application, the thruster coplanar layout parameter includes: A attitude control thrusters, A being an even number greater than or equal to eight, each two attitude control thrusters being an attitude control thruster group, one of each attitude control thruster group being a main attitude control thruster and the other being a backup attitude control thruster, all attitude control thruster groups being uniformly distributed on the edge of the satellite cabin panel, and each attitude control thruster being tilted at a preset angle.

[0011] In an embodiment of the present application, the thruster coplanar layout parameter includes: B orbit control thrusters, B being an even number greater than or equal to four, each two orbit control thrusters being an orbit control thruster group, one of each orbit control thruster group being a main orbit control thruster and the other being a backup orbit control thruster, all orbit control thruster groups being uniformly distributed on a circular ring constructed according to a preset radius and with respect to the centroid of the satellite cabin panel.

[0012] In an embodiment of the present application, the satellite cabin panel is rectangular, and the preset radius is less than or equal to one half of the length of the short side of the satellite cabin panel.

[0013] In an embodiment of the present application, the satellite thrusters satisfy one or any combination of the following conditions: thruster values in the same attitude control thruster group are the same; thruster values in the same orbit control thruster group are the same; thruster values between different attitude control thruster groups are the same or different; and thruster values between different orbit control thruster groups are the same or different.

[0014] The present application also proposes a satellite thruster coplanar layout system to solve the above technical problems, including: a memory for storing instructions executable by a processor; and the processor for executing the instructions to implement the satellite thruster coplanar layout method as above.

[0015] The application also provides a computer readable medium storing computer program codes, which, when executed by a processor, implement the coplanar layout method of the satellite thruster.

[0016] The technical solution of the application realizes coplanar installation of the attitude control thruster and the orbit control thruster on the satellite cabin plate by presetting parameters to simulate control of the satellite and generate and optimize coplanar layout parameters of the thruster, can reduce the complexity of the layout space of the satellite pipeline, ensures that the thruster layout meets the control requirements through simulation verification, improves the redundancy of the thruster system, and facilitates installation and maintenance of the thruster, and can realize multi-batch multi-stage thrust output under the simple and reliable thruster system layout, thereby providing stable output of attitude control and orbit control thrust in different orbit control directions and orbit control times. While simplifying the layout, the application can meet the attitude and orbit control requirements of deep space satellites and lays a foundation for subsequent construction of a modular satellite propulsion cabin plate. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to make the above-mentioned purposes, features and advantages of the application more obvious and easy to understand, the specific embodiments of the application are described in detail below with reference to the drawings, in which:

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

[0019] Figure 2 is a schematic diagram of coplanar installation of the satellite thruster on the same satellite cabin plate according to an embodiment of the application;

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

[0021] Figure 4 is a flowchart of deep space satellite attitude control and multi-stage orbit control under coplanar installation of the satellite thruster according to an embodiment of the application;

[0022] Figure 5 is a schematic diagram of the calculated closed-loop attitude angle in the process of simulating control of the satellite according to an embodiment of the application;

[0023] Figure 6 is a schematic diagram of the calculated closed-loop attitude angular velocity in the process of simulating control of the satellite according to an embodiment of the application;

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

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

[0026] 210. attitude control thruster;

[0027] 220. orbit control thruster;

[0028] 230. satellite deck plate;

[0029] 240. torus. DETAILED DESCRIPTION

[0030] In order to make the above objectives, features and advantages of the present application more apparent, the specific embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0031] In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, the present application can be practiced without the specific details. In other instances, well-known methods, procedures, components, and circuits have not been described in detail so as not to obscure the present application.

[0032] As used in the present application, unless the context clearly indicates otherwise, the words "a", "an", "the", and / or "at least one" do not denote a singular entity, but include elements both singular and plural. Generally, the term "comprises" or "comprising" is used in the sense of "including" or "including without limitation" to provide an inclusive scope of meaning.

[0033] Flow diagrams are used in the present application to illustrate the operations performed by systems according to embodiments of the present application. It should be understood that the operations previously or hereafter described do not necessarily have to be performed in the order shown. Instead, various steps can be processed in reverse order, or at the same time, or with other operations added or removed from the processes.

[0034] The present application proposes a coplanar layout method of a satellite thruster, the satellite thruster comprising a plurality of attitude control thrusters and a plurality of orbit control thrusters. The present application is equivalent to a coplanar installation method of deep space satellite attitude control thrusters and orbit control thrusters. The application scenarios that can be applied include: deep space satellite complex multi-batch multi-parameter orbit control task scenarios that need to have multi-stage thrust output support of system reliability; satellites that need to be modularly assembled and miniaturized designed; satellites that need to optimize the layout design of propelling pipelines, etc.

[0035] The coplanar layout method of the satellite thruster of the present application can be run on a ground station, for example, in a controller of a ground station computer, and can also be run in a cloud platform. When the coplanar layout method of the satellite thruster is run in the cloud platform, the data of the ground station computer end and the cloud platform data are interacted through a wireless network. Exemplarily, the cloud platform can include a private cloud, a public cloud, a hybrid cloud, a community cloud, a distributed cloud, an interconnected cloud, and a multiple cloud, etc. or any combination thereof. The present application does not limit the running environment of the coplanar layout method of the satellite thruster.

[0036] Figure 1 is an exemplary flowchart of a method for coplanar layout of satellite thrusters according to an embodiment of the present application, referring to Figure 1 the method for coplanar layout of satellite thrusters according to the embodiment includes the following steps:

[0037] Step S110: simulating control of the satellite according to satellite parameters and preset thruster layout parameters to obtain a simulation control result of the satellite.

[0038] Step S120: generating thruster coplanar layout parameters according to the simulation control result.

[0039] Step S130: mounting multiple attitude control thrusters and multiple orbit control thrusters coplanarly on a same satellite panel according to the thruster coplanar layout parameters.

[0040] The above steps S110 to S130 are described in detail as follows:

[0041] In step S110, the satellite is simulated according to satellite parameters and preset thruster layout parameters to obtain a simulation control result of the satellite. For example, the satellite is simulated according to preset parameters to verify the rationality of the thruster layout in advance, so as to optimize the installation position and configuration mode of the thrusters, thereby reducing the design risk in actual engineering and improving the control accuracy and reliability of the propulsion system.

[0042] In some embodiments, the satellite parameters include one or any combination of the whole satellite size (i.e. the structural size of the whole satellite), the whole satellite inertia, the mass center deviation, and the thrust value (i.e. the thrust size). The preset thruster layout parameters include one or any combination of the inclination angle of the attitude control thruster, the layout position of the attitude control thruster, and the layout position of the orbit control thruster.

[0043] For example, by pre-designing the satellite parameters and the thruster layout parameters, the matching accuracy of the thruster layout and the physical characteristics of the satellite can be improved, the adaptability and reliability of the control system can be effectively improved, and a basis is provided for subsequent optimization of the thruster coplanar layout.

[0044] In some embodiments, simulating control of the satellite according to satellite parameters and preset thruster layout parameters to obtain a simulation control result of the satellite includes:

[0045] generating initial thruster coplanar layout parameters according to the satellite parameters and the preset thruster layout parameters;

[0046] simulating the satellite to perform orbit control tasks and / or attitude control tasks according to the Monte Carlo method and the initial thruster coplanar layout parameters to obtain a simulation control result, the simulation control result including closed-loop attitude angular velocity and / or closed-loop attitude angle.

[0047] For example, the Monte Carlo method is to combine the target to-be-determined parameters (such as the initial thruster coplanar layout parameters), traverse the possible range, and then select the optimal parameter combination by evaluating the effect of each parameter combination, which includes the tilt angle and layout position of the thruster. In practical applications, the Monte Carlo method can be constructed in the mathematical model of the satellite control system, and the installation parameter design under different satellite parameters can be realized through the satellite control system.

[0048] The application can generate an initial coplanar layout scheme by combining the satellite parameters and the preset thruster layout parameters, and can comprehensively and reliably evaluate the control performance of the thruster layout by using the Monte Carlo method to simulate the satellite performing a task. The control accuracy and control stability can be quantitatively evaluated by parameters such as closed-loop attitude angular velocity and closed-loop attitude angle, which facilitates layout optimization.

[0049] In step S120, the thruster coplanar layout parameters are generated according to the simulation control result. In some embodiments, the method comprises:

[0050] In response to the simulation control result being within the preset threshold range, the initial thruster coplanar layout parameters corresponding to the simulation control result are taken as the thruster coplanar layout parameters; or, in response to the simulation control result being outside the preset threshold range, the initial thruster coplanar layout parameters are re-generated, and the satellite performing the orbit control task and / or the attitude control task is re-simulated.

[0051] For example, the application can efficiently determine the thruster coplanar layout parameters that meet the accuracy requirements by presetting the threshold range to automatically judge and optimize the simulation control result. When the simulation control result is within the preset threshold range, the optimal parameters are directly output; when the simulation control result exceeds the preset threshold range, the iterative process of re-generation and simulation verification is automatically executed, and the automatic optimization of the layout parameters is realized through the closed-loop feedback mechanism, so that a thruster coplanar layout scheme with high reliability and strong adaptability can be obtained.

[0052] The following describes the process of obtaining the optimal thruster coplanar layout parameters according to an embodiment of the application.

[0053] Figure 3 is an exemplary flowchart of a satellite thruster coplanar layout method according to another embodiment of the application. Referring to Figure 3As shown in FIG. 13, in step S310, satellite parameters are obtained, including the overall satellite size, the overall satellite inertia, the mass center deviation, and the thrust value size; in step S320, preset thruster layout parameters are obtained, including the inclination 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 taken as the controlled object characteristic parameters, the preset thruster layout parameters are taken as the installation parameters, and the satellite control system mathematical model is used to traverse the data; in step S340, the data is traversed using the Monte Carlo method; and in step S350, the optimal thruster coplanar layout parameters are obtained through an optimization algorithm.

[0054] The other steps of the present application will be further introduced below.

[0055] In step S130, the multiple attitude control thrusters and the multiple orbit control thrusters are installed coplanarly on the same satellite panel according to the thruster coplanar layout parameters. Exemplarily, a mechanical hand can be used to install the attitude control thruster and the orbit control thruster. Through the coplanar installation of the attitude control thruster and the orbit control thruster, the present application can realize the optimized layout of the satellite and the pipeline, is conducive to the modular assembly of the satellite, and is suitable for the miniaturization design of the satellite.

[0056] Figure 2 FIG. 1 is a schematic diagram of the coplanar installation of the satellite thrusters on the same satellite panel in an embodiment of the present application. Referring to FIG. 1, Figure 2 As shown in FIG. 13, in some embodiments, the thruster coplanar layout parameters include: A attitude control thrusters 210, A is an even number greater than or equal to eight (such as Figure 2 As shown in FIG. 1, eight attitude control thrusters are shown, which correspond to F1, F2, F3, F4, F5, F6, F7, and F8 respectively, each attitude control thruster is set to 5N, and N represents Newton. Every two attitude control thrusters are taken as an attitude control thruster group (for example Figure 2 F1 and F5 in FIG. 1 are an attitude control thruster group), one of each attitude control thruster group is taken as a main attitude control thruster and the other is taken as a backup attitude control thruster, all the attitude control thruster groups are uniformly distributed on the edge of the satellite panel, and each attitude control thruster 210 is inclined at a preset angle.

[0057] Exemplarily, through the main-backup configuration of the attitude control thruster group, the present application can improve the reliability of the satellite control system. Through the grouping configuration of the multiple attitude control thrusters 210, each group contains a main-backup dual-redundancy thruster, and these attitude control thrusters 210 are inclined at a preset angle and uniformly installed on the edge of the same satellite panel 230, so that the high-reliability operation of the thruster system can be realized, and the balanced control moment in each direction is guaranteed.

[0058] Continuing to refer to FIG. 13, Figure 2 As shown in FIG. 13, in some embodiments, the thruster coplanar layout parameters include: B orbit control thrusters 220, B is an even number greater than or equal to four (such asFigure 2 Four orbit control thrusters are shown in FIG. 9, corresponding to F9, F10, F11, and F12, respectively, and each two orbit control thrusters are as an orbit control thruster group (for example Figure 2 F9 and F11 in FIG. 9 are an orbit control thruster group), one of each orbit control thruster group is as a main orbit control thruster and the other is as a standby orbit control thruster, and all orbit control thruster groups are evenly distributed on a circular ring 240 constructed according to a preset radius with respect to the centroid of the satellite cabin plate 230.

[0059] Exemplarily, the present application can improve the reliability of the satellite control system by configuring the orbit control thruster groups as main and standby. Figure 2 The four orbit control thrusters shown in FIG. 9 (corresponding to F9-F12) are all set to 20N, N representing Newton. Figure 2 The four orbit control thrusters in FIG. 9 are located on the circular ring 240 constructed according to a preset radius with respect to the centroid of the satellite cabin plate 230 (i.e., around the satellite centroid), which can realize three combination usage modes of the orbit control thrusters, the first combination being F9 and F11, the second combination being F10 and F12, and the third combination being F9, F10, F11, and F12. The layout of the orbit control thrusters 220 of the present application will not generate large bias torque interference.

[0060] The present application ensures that the failure of a single orbit control thruster 220 does not affect the orbit control function through the main and standby redundant design, and ensures the symmetry of the thrust direction and the control accuracy through the uniform circular ring layout, forming an optimal layout scheme of control accuracy and propulsion efficiency.

[0061] In some embodiments, the satellite cabin plate 230 is rectangular, the rectangular satellite cabin plate 230 includes a short side and a long side, and the preset radius is less than or equal to one half of the length of the short side of the satellite cabin plate 230. Exemplarily, Figure 2 The satellite cabin plate 230 shown in FIG. 9 is approximately rectangular, and the preset radius of the circular ring 240 is 350mm, mm representing millimeter. In actual application, the sides of the rectangular satellite cabin plate 230 are all equal, and then the preset radius can be set to be less than or equal to one half of the length of the side.

[0062] The present application can ensure that the installation position of the orbit control thruster 220 is always located within the effective structure range of the satellite cabin plate 230 by limiting the radius of the circular ring on the satellite cabin plate 230 to be within one half of the length of the short side of the satellite cabin plate 230, and the thruster layout structure on the satellite cabin plate 230 is compact, improving the space utilization of the satellite cabin plate 230.

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

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

[0065] The thrust values of the same orbit control thruster group are the same;

[0066] The thrust values of different attitude control thruster groups are the same or different;

[0067] The thrust values of different orbit control thruster groups are the same or different.

[0068] For example, by configuring the thrust values of the attitude control thrusters 210 and the orbit control thrusters 220, a multi-stage thrust output scheme can be generated when orbit control is performed, the reliability of the orbit control task is improved, the complex multi-batch multi-parameter orbit control requirements of the deep space satellite can be met, and the balance of the satellite propulsion system in control accuracy, task adaptability and energy efficiency is achieved.

[0069] Hereinafter Figure 2 Embodiments in which multiple attitude control thrusters 210 and multiple orbit control thrusters 220 are coplanarly installed on the same satellite deck 230 of a satellite are described.

[0070] Referring to Figure 2 As shown in the figure, eight 5N attitude control thrusters 210 are configured on the satellite deck 230 of the deep space satellite for attitude control, and the eight attitude control thrusters correspond to F1, F2, F3, F4, F5, F6, F7 and F8 respectively. Each attitude control thruster is inclined at a certain angle (such as 25°) to generate sufficient attitude control torque. Each two attitude control thrusters form a group and are the main and backup of each other. Four 20N orbit control thrusters 220 are configured for orbit control, and the four orbit control thrusters correspond to F9, F10, F11 and F12 respectively. The orbit control thrusters are installed without inclination to generate maximum orbit control efficiency. Each two orbit control thrusters form a group and are the main and backup of each other. These thrusters are coplanarly installed at the satellite deck 230 at the bottom of the satellite. Among them, the eight 5N attitude control thrusters 210 are installed at the edges of the satellite deck 230, and the four 20N orbit control thrusters 220 are installed on the circular ring 240 with a center φ = 350 mm of the bottom plate. The connecting lines of the opposite two thrusters are parallel to the two edges of the bottom plate.

[0071] In actual application, the following Figure 2 way can be used to set eight 5N attitude control thrusters 210 (four 5N attitude control thrusters are used as the main part or backup in normal operation) and four 20N orbit control thrusters 220, or two 20N orbit control thrusters 220, or four 5N orbit control thrusters 220 on the same satellite deck 230. When the orbit control thrust is output, the deep space satellite can generate rated multi-stage thrust through different thruster combinations, such as three stages of 80N, 40N and 20N thrust.

[0072] The following describes the process of deep space satellite attitude control and orbit control under coplanar installation of satellite thrusters with an embodiment.

[0073] Figure 4 is a flowchart of deep space satellite attitude control and multi-stage orbit control under coplanar installation of satellite thrusters in an embodiment of the present application. Referring to Figure 4 , satellite parameters are obtained in step S410, including the overall satellite size provided by the satellite structural system, the overall satellite inertia, the mass center deviation, and the thrust value of the thruster output selected by the satellite control system; in step S420, different combinations in the parameter range of the satellite parameters and the preset thruster layout parameters are traversed through the mathematical model of the satellite control system and the Monte Carlo method to simulate the satellite control and automatically calculate the simulation control results of the satellite (such as closed-loop attitude angular velocity and closed-loop attitude angle); in step S430, the optimal installation layout scheme is optimized by using an optimization algorithm according to the simulation control results and by comprehensively considering factors such as orbit control thrust output stability, attitude control stability, attitude control accuracy, system reliability, etc.; in step S440, the optimal thruster coplanar layout parameters are obtained; in step S450, the thruster control scheme is instructed; in steps S461, S462, S463, and S464, different use combination schemes of the thrusters are output respectively to realize three-stage thrust output of 80N orbit control, 40N orbit control, and 20N orbit control and 5N attitude control scheme, and to ensure sufficient reliability of the satellite system.

[0074] Continuing to refer to Figure 2 and Figure 4 , the 80N orbit control scheme is output in step S461, using 4 orbit control thrusters (corresponding to F9, F10, F11, and F12) in Figure 2 ; the 40N orbit control scheme is output in step S462, using 2 orbit control thrusters (corresponding to F9 and F11, or F10 and F12) in Figure 2 ; the 20N orbit control scheme is output in step S463, using 4 attitude control thrusters (corresponding to F1, F2, F3, F4, or F5, F6, F7, F8) in Figure 2 ; and the 5N attitude control scheme is output in step S464, using 8 attitude control thrusters (corresponding to F1, F2, F3, F4, F5, F6, F7, F8) in Figure 2 .

[0075] For example, when multiple attitude control thrusters are used to perform orbit control tasks, attitude adjustment is performed as needed in the same control cycle, that is, both attitude control tasks and orbit control tasks are completed in one control cycle. In the orbit control process, multiple attitude control thrusters perform attitude control and have backups, enhancing the reliability of the satellite system.

[0076] Figure 5is a schematic diagram of the closed-loop attitude angle calculated in the simulation of controlling the satellite in an embodiment of the present application, Figure 6 is a schematic diagram of the closed-loop attitude angular velocity calculated in the simulation of controlling the satellite in an embodiment of the present application. Reference is made to Figure 5 and Figure 6 As shown, the satellite thruster coplanar installation is mounted on the same satellite cabin panel and the satellite is simulated and controlled in an example of the present application, Figure 5 The change of the closed-loop attitude angle is shown in the figure, and the closed-loop attitude angle can reflect the accuracy of the satellite control. Figure 6 The change of the closed-loop attitude angular velocity is shown in the figure, and the closed-loop attitude angular velocity can reflect the stability of the satellite control. Figure 5 and Figure 6 The data shown in the figures basically changes in the interval range, indicating that the thruster coplanar layout scheme of the present application is good.

[0077] The technical scheme of the present application simulates the control of the satellite by preset parameters, generates and optimizes the thruster coplanar layout parameters, realizes the coplanar installation of the attitude control thruster and the orbit control thruster on the satellite cabin panel, and can reduce the complexity of the satellite pipeline layout space. Through simulation verification, it is ensured that the thruster layout meets the control requirements, improves the redundancy of the thruster system, and facilitates the installation and maintenance of the thruster. Under the simple and reliable thruster system layout, multiple batches of multi-stage thrust output can be realized, thereby providing attitude control and orbit control thrust stable output under different orbit control directions and orbit control times. While simplifying the layout, the present application can realize the attitude and orbit control requirements of deep space satellites, and also lays a foundation for subsequent realization of the construction of modular satellite propulsion cabin panels.

[0078] The present application also includes a satellite thruster coplanar layout system, comprising a memory and a processor. The memory is used to store instructions executable by the processor; the processor is used to execute the instructions to realize the satellite thruster coplanar layout method described above.

[0079] Figure 7 is a system block diagram of the satellite thruster coplanar layout system of an embodiment of the present application. Reference is made to Figure 7As shown, the satellite thruster's coplanar layout system 700 can 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 satellite thruster's coplanar layout system 700 can also include a hard disk 706. The internal communication bus 701 can enable data communication between the components of the satellite thruster's coplanar layout system 700. The processor 702 can make decisions and issue prompts. In some embodiments, the processor 702 can be composed of one or more processors. The communication port 705 can enable external data communication of the satellite thruster's coplanar layout system 700. In some embodiments, the satellite thruster's coplanar layout system 700 can send and receive information and data from a network through the communication port 705. The satellite thruster's coplanar layout system 700 can also include different forms of program storage units and data storage units, such as the hard disk 706, the read only memory (ROM) 703, and the random access memory (RAM) 704, which can store various data files used by the computer processing and / or communication, and possible program instructions executed by the processor 702. The processor executes these instructions to implement the main parts of the method. The results of the processor processing are transmitted to the user equipment through the communication port, and displayed on the user interface.

[0080] The satellite thruster's coplanar layout method described above can be implemented as a computer program, saved in the hard disk 706, and loaded into the processor 702 for execution, to implement the satellite thruster's coplanar layout method of the present application.

[0081] The present application also includes a computer readable medium storing computer program code, which, when executed by a processor, implements the satellite thruster's coplanar layout method described above.

[0082] When the satellite thruster's coplanar layout method is implemented as a computer program, it can also be stored in a computer readable storage medium as an article of manufacture. For example, the computer readable storage medium can include, but is not limited to, magnetic storage devices (e.g., hard disk, floppy disk, magnetic strips), optical disks (e.g., compact disk (CD), digital versatile disk (DVD)), smart cards, and flash memory devices (e.g., electrically erasable programmable read only memory (EPROM), card, stick, key drive). In addition, the various storage mediums described herein can represent one or more devices and / or other machine-readable media for storing information. The term "machine-readable medium" can include, without limitation, wireless channels and various other media (and / or storage media) that can store, contain, and / or carry the code and / or instructions and / or data.

[0083] It should be understood that the above-described embodiments are only illustrative. The embodiments described herein can be implemented in hardware, software, firmware, middleware, microcode, or any combination thereof. For a hardware implementation, the processing units can 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, micro-controllers, microprocessors, and / or other electronic units designed to perform the functions described herein and / or combinations thereof.

[0084] Some aspects of the application can be performed entirely in hardware, entirely in software (including firmware, resident software, micro-code, etc.), or in a combination of hardware and software. The above hardware or software can be referred to as a "block," "module," "engine," "unit," "component," or "system." The processor can 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, micro-controllers, microprocessors, or combinations thereof. Furthermore, aspects of the application can be presented in a computer program product, which can include a computer-readable medium having computer program code embodied therein. The computer-readable medium can include, but is not limited to, magnetic storage devices (e.g., hard disk; floppy disk; magnetic strips), optical disks (e.g., compact disk (CD); digital versatile disk (DVD)), smart cards, and flash memory devices (e.g., card; stick; key drive). The computer program code can include any suitable type of code, such as source code, object code, executable code, and the like.

[0085] The computer program code can include any suitable type of code, such as source code, object code, executable code, and the like. The computer program code can be embodied in a computer-readable medium, which can include any medium that can be read and accessed by a computer. Such computer-readable media can include, but are not limited to, portable storage articles (e.g., compact discs (CDs), digital versatile discs (DVDs), and the like), hard disks, memory (e.g., random access memory (RAM), read-only memory (ROM), and the like), and the like. The computer program code can be distributed over such a computer-readable medium, or can be embodied in a computer program product distributed over a variety of computer-readable media.

[0086] Having described basic concepts, it is obvious that the above-described application discloses only examples and does not limit the application. Although not explicitly described, those skilled in the art can make various modifications, improvements, and corrections to the application. Such modifications, improvements, and corrections are suggested in the application, so such modifications, improvements, and corrections still belong to the spirit and scope of the exemplary embodiments of the application.

[0087] Also, the use of "a" or "an" or "the" are intended to include "one or more" and any singular form "a" or "an" or "the" is intended to include the plural forms as well, unless the context clearly indicates otherwise. Also, the term "comprising" is intended to include the terms "including", "including but not limited to", "including one or more of", and "including at least", and is intended not to be limited to "consisting of".

[0088] Some embodiments use numerical descriptors to describe components, quantities of attributes. It should be understood that such numerical descriptors used in the description of embodiments are, in some examples, modified by the modifier "about," "approximately," or "generally." Unless otherwise stated, "about," "approximately," or "generally" indicates that a deviation of ±20% is allowed for the number in question. Accordingly, in some embodiments, numerical parameters used in the application are approximations, and as such, the numerical parameters used in the application are intended to encompass a range whose boundaries are typically defined by the numerical limits in connection with the individual significant digits of the limit. Although the numerical ranges and parameters setting forth the broad scope of the embodiments of the application are approximations, the numerical values set forth in the specific examples are reported as precisely as practicable.

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 satellite is controlled by simulation based on satellite parameters and preset thruster layout parameters to obtain the simulation control results of the satellite; Based on the simulation control results, the thruster coplanar layout parameters are generated; 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.

2. The coplanar layout method for satellite thrusters as described in claim 1, characterized in that, The satellite is controlled by simulation based on satellite parameters and preset thruster layout parameters, and the simulation control results of the satellite are obtained, including: Initial thruster coplanar layout parameters are generated based on the satellite parameters and the preset thruster layout parameters; The satellite is simulated to perform orbit control and / or attitude control tasks based on the Monte Carlo method and the initial thruster coplanar layout parameters, and the simulation control results are obtained, including closed-loop attitude angular velocity and / or closed-loop attitude angle.

3. The coplanar layout method for satellite thrusters as described in claim 2, characterized in that, Based on the simulation control results, thruster coplanar layout parameters are generated, including: In response to the simulation control result being within a preset threshold range, the initial thruster coplanar layout parameters corresponding to the simulation control result are used as the thruster coplanar layout parameters; or In response to the simulation control results being outside the preset threshold range, the initial thruster coplanar layout parameters are regenerated, and the satellite's orbit control and / or attitude control tasks are re-simulated.

4. The method for coplanar layout of satellite thrusters as described in any one of claims 1-3, 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.

5. 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.

6. The coplanar layout method for satellite thrusters as described in claim 5, 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.

7. The coplanar layout method for satellite thrusters as described in claim 6, 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.

8. The coplanar layout method for satellite thrusters as described in claim 6, 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.

9. 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 1-8.

10. 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 1-8.

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