Satellite momentum wheel bracket design method, device, equipment, medium and program product

Abstract

This application relates to the field of aerospace technology. Specifically, it relates to a design method, device, equipment, medium, and program product for a satellite momentum wheel bracket. Draw the upper plane L0 of the satellite and draw a rectangular coordinate system that coincides with the satellite body coordinate system, so that the X-axis and Y-axis of the rectangular coordinate system are located within the plane L0; obtain the intersection line S1 of the conical surface Y1, conical surface Y2, and conical surface Y3 in the rectangular coordinate system according to the pre-acquired installation angles α, β, and γ of the momentum wheel; draw the plane L1 with the intersection line S1 as the normal line and obtain the corresponding installation section C1 of this plane L1; project the installation section C1 onto the plane L0 to obtain the section C2, and stretch and form a solid Z1 between the installation section C1 and the section C2. The purpose of this application is to provide a design method, device, equipment, medium, and program product for a satellite momentum wheel bracket for at least one technical problem involved in the prior art.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a satellite momentum wheel bracket design method, device, equipment, medium and program product. Background Art

[0002] The momentum wheel is an inertial actuator in the attitude control system of a spacecraft. In the spacecraft attitude control system, the momentum wheel provides appropriate control torque according to the instructions of the attitude control system to correct the attitude deviation of the spacecraft or complete a certain predetermined attitude adjustment.

[0003] Generally speaking, there are two common configurations for the flywheel configuration of four momentum wheels: three orthogonal and one oblique installation and pyramid configuration. The pyramid configuration is more flexible than the three orthogonal and one oblique installation, but the angular momentum direction of each momentum wheel in the pyramid configuration is at a certain angle to the satellite's XYZ axis, and all need to be installed through a bracket; while in the three orthogonal and one oblique installation method, only the oblique flywheel needs to be installed through a bracket, and the other three orthogonal flywheels can be directly installed on the satellite cabin board, which can save the weight of the satellite structure and save launch costs.

[0004] like Figure 2 As shown, the momentum wheel has three orthogonal and one oblique configurations, and the installation requirements are as follows: the X-angular momentum direction of the momentum wheel is in the same direction as the X-axis of the satellite body, the Y-angular momentum direction of the momentum wheel is in the same direction as the Y-axis of the satellite body, the Z-angular momentum direction of the momentum wheel is in the same direction as the +Z-axis of the satellite body, the S-angular momentum direction of the momentum wheel is at an angle α to the +X-axis of the satellite body, the S-angular momentum direction of the momentum wheel is at an angle β to the +Y-axis of the satellite body, and the S-angular momentum direction of the momentum wheel is at an angle γ to the +Z-axis of the satellite body.

[0005] The three installation angles α, β and γ of the momentum wheel S are calculated based on the angular momentum of the momentum wheel, the moment of inertia of the satellite and the attitude maneuvering requirements of the satellite. Therefore, satellites of different weights or the same satellite using different models of momentum wheels S will have different α, β and γ, and the momentum wheel bracket needs to be redesigned. However, the existing momentum wheel bracket design method has complicated steps and is not fixed, which is not conducive to improving production efficiency. Summary of the invention

[0006] The purpose of the present application is to provide a satellite momentum wheel bracket design method, device, equipment, medium and program product in response to at least one technical problem involved in the background technology.

[0007] In order to achieve the above objectives, this application adopts the following technical solutions:

[0008] The present application provides a satellite momentum wheel bracket design method, comprising:

[0009] Draw the satellite upper plane L 0, and draw a rectangular coordinate system that coincides with the satellite body coordinate system so that the X axis and Y axis of the rectangular coordinate system are located on the plane L 0 Inside;

[0010] The cone surface Y is obtained in the rectangular coordinate system according to the pre-acquired installation angle α, installation angle β and installation angle γ of the momentum wheel. 1 、Conical surface Y 2 and cone surface Y 3 The intersection line S 1 ;

[0011] Draw the intersection line S 1 The plane L is the normal 1 , and obtain the plane L 1 Corresponding installation cross section C 1 ;

[0012] The installation section C 1 Projected onto the plane L 0 To obtain the cross section C 2 , at the installation section C 1 With the section C 2 Stretching between them to form a solid Z 1 ;

[0013] Among them, the installation angle α is the angle between the angular momentum direction of the momentum wheel and the +X axis, the installation angle β is the angle between the angular momentum direction of the momentum wheel and the +Y axis, and the installation angle γ is the angle between the angular momentum direction of the momentum wheel and the +Z axis.

[0014] Optionally, the cone surface Y is obtained in the rectangular coordinate system according to the pre-acquired installation angle α, installation angle β and installation angle γ of the momentum wheel. 1 、Conical surface Y 2 and cone surface Y 3 The intersection line S 1 ,include:

[0015] Obtaining the installation angle α, the installation angle β and the installation angle γ of the momentum wheel;

[0016] Draw the conical surface Y with the +X axis, +Y axis and +Z axis of the rectangular coordinate system as the axis 1 、Conical surface Y 2 and cone surface Y 3 , get the cone surface Y 1 、Conical surface Y 2 and cone surface Y 3 The intersection line S 1 .

[0017] Optionally, obtaining the installation angle α, the installation angle β and the installation angle γ of the momentum wheel includes:

[0018] Receive the installation angle α, installation angle β and installation angle γ calculated by the attitude control subsystem.

[0019] Optionally, the drawing is performed with the intersection line S 1 The plane L is the normal 1 , and obtain the plane L 1 Corresponding installation cross section C 1 ,include:

[0020] Draw the intersection line S 1 The plane L is the normal 1 , the plane L 1 Translate the preset distance to obtain the momentum wheel mounting surface L on the bracket 2 ;

[0021] According to the size of the momentum wheel, the momentum wheel mounting surface L on the bracket 2 Cut the installation section C from above 1 .

[0022] Optionally, in the installation section C 1 Projection to L 0 Get section C 2 , at the installation section C 1 With the section C 2 Stretching between them to form a solid Z 1 After that, it also includes:

[0023] According to the size of the momentum wheel, install the section C 1 Draw the bracket installation interface J on 1 ;

[0024] Draw the installation interface between the bracket and the satellite according to the installation position and size of the satellite momentum wheel bracket on the satellite 2 ;

[0025] For entity Z 1 Perform weight reduction and process optimization.

[0026] Optionally, the installation angle α is 100.025°, and the installation angle β and the installation angle γ are both 134.1317°.

[0027] Another aspect of the present application provides a satellite momentum wheel bracket design device, comprising:

[0028] Coordinate system drawing module, used to draw the satellite upper plane L 0 , and draw a rectangular coordinate system that coincides with the satellite body coordinate system so that the X axis and Y axis of the rectangular coordinate system are located on the plane L 0 Inside;

[0029] The intersection line acquisition module is used to draw the cone surface Y with +X axis as the axis, +Y axis as the axis and +Z axis as the axis according to the installation angle α, installation angle β and installation angle γ of the momentum wheel calculated by the attitude control subsystem. 1 、Conical surface Y 2 and cone surface Y 3 , get the cone surface Y 1 、Conical surface Y 2 and cone surface Y 3 The intersection line S 1 ;

[0030] Install the surface drawing module to draw the intersection line S 1 The plane L is the normal 1 , the plane L 1 Translate the preset distance to obtain the momentum wheel mounting surface L on the bracket 2 , according to the size of the momentum wheel, the momentum wheel mounting surface L on the bracket 2 Cut the installation section C from above 1 ;

[0031] The mounting frame entity drawing module is used to draw the mounting section C 1 Projection to L 0 Get section C 2 , at the installation section C 1 With the section C 2 Stretch entities between.

[0032] The third aspect of the present application provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the satellite momentum wheel bracket design method provided in the present application when executing the computer program.

[0033] The fourth aspect of the present application provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the satellite momentum wheel bracket design method provided in the present application.

[0034] The fifth aspect of the present application provides a computer program product, including a computer program, which, when executed by a processor, implements the satellite momentum wheel bracket design method provided in the present application.

[0035] The technical solution provided by this application can achieve at least one of the following beneficial effects:

[0036] The satellite momentum wheel bracket design method, device, equipment, medium and program product provided in this application are suitable for the design of a satellite momentum wheel bracket of a momentum wheel S. The bracket is designed quickly and accurately using standard fixed steps, which is conducive to improving production efficiency.

[0037] The additional technical features and advantages of the present application will be more clearly explained in the following description, or can be understood through the specific practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the technical solutions of the specific implementation methods of the present application, the following is a brief introduction to the drawings required for the description of the specific implementation methods. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0039] Figure 1 A schematic flow chart of an implementation method of a satellite momentum wheel bracket design method provided in an embodiment of the present application;

[0040] Figure 2 A schematic diagram of the principle of a three-orthogonal and one-oblique flywheel configuration provided in an embodiment of the present application;

[0041] Figure 3 The conical surface Y is drawn according to the satellite momentum wheel bracket design method provided in the embodiment of the present application. 1 、Conical surface Y 2 and cone surface Y 3 Schematic diagram after the circle;

[0042] Figure 4 A schematic diagram after completing step 200 in the satellite momentum wheel bracket design method provided in an embodiment of the present application;

[0043] Figure 5 This is a schematic diagram after completing step 310 in the satellite momentum wheel bracket design method provided in an embodiment of the present application;

[0044] Figure 6 The section C is drawn in the satellite momentum wheel bracket design method provided in the embodiment of the present application. 2 Schematic diagram after

[0045] Figure 7 A schematic diagram after completing step 400 in the satellite momentum wheel bracket design method provided in an embodiment of the present application;

[0046] Figure 8 and Fig. 9 They are schematic diagrams at different angles after completing step 030 in the satellite momentum wheel bracket design method provided in the embodiments of the present application;

[0047] Fig.10 It is a schematic structural diagram of a momentum wheel behind a satellite momentum wheel bracket designed according to the satellite momentum wheel bracket design method provided in an embodiment of the present application;

[0048] Fig.11 A structural schematic diagram of an implementation scheme of a satellite momentum wheel bracket design device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the implementation modes and the accompanying drawings. Here, the illustrative implementation modes and descriptions of the present application are used to explain the present application, but are not intended to limit the present application.

[0050] It should also be noted here that in order to avoid obscuring the present application due to unnecessary details, only the structures and / or processing steps closely related to the scheme according to the present application are shown in the accompanying drawings, while other details that are not very relevant to the present application are omitted.

[0051] It should be emphasized that the term “include / comprises” when used herein refers to the presence of features, elements, steps or components, but does not exclude the presence or addition of one or more other features, elements, steps or components.

[0052] It should also be noted that, unless otherwise specified, the term “connection” herein may refer not only to a direct connection but also to an indirect connection involving an intermediate.

[0053] Hereinafter, embodiments of the present application will be described with reference to the accompanying drawings. In the accompanying drawings, the same reference numerals represent the same or similar components, or the same or similar steps.

[0054] The details are described in detail through the following examples.

[0055] Based on this, Figure 1 As shown, the present application provides a satellite momentum wheel bracket design method, comprising:

[0056] Step 100: Draw the satellite upper plane L 0 , and draw a rectangular coordinate system that coincides with the satellite body coordinate system so that the X axis and Y axis of the rectangular coordinate system are located on the plane L 0 Inside;

[0057] Step 200: Obtain the conical surface Y in the rectangular coordinate system according to the pre-obtained installation angle α, installation angle β and installation angle γ of the momentum wheel 1 、Conical surface Y 2 and cone surface Y 3 The intersection line S 1 ;

[0058] Step 300: Draw the intersection line S 1 The plane L is the normal 1 , and obtain the plane L 1 Corresponding installation cross section C1 ;

[0059] Step 400: Install the section C 1 Projected onto the plane L 0 To obtain the cross section C 2 , at the installation section C 1 With the section C 2 Stretching between them to form a solid Z 1 ;

[0060] Among them, the installation angle α is the angle between the angular momentum direction of the momentum wheel and the +X axis, the installation angle β is the angle between the angular momentum direction of the momentum wheel and the +Y axis, and the installation angle γ is the angle between the angular momentum direction of the momentum wheel and the +Z axis.

[0061] The satellite momentum wheel bracket design method provided in the present application is applicable to the design of a satellite momentum wheel bracket of a momentum wheel S, and adopts standard fixed steps to quickly and accurately design the bracket, which is conducive to improving production efficiency; moreover, the satellite momentum wheel bracket obtained by the satellite momentum wheel bracket design method provided in the present application occupies a small space and has high installation accuracy. When the inertia of the whole satellite changes or the momentum wheel selection changes causing the installation α, β and γ angles to change, the original bracket design can be quickly modified, saving the design and modification time of the momentum wheel S installation bracket.

[0062] like Figure 3 and Figure 4 As shown, in order to further improve production efficiency, in the satellite momentum wheel bracket design method provided in the embodiment of the present application, step 200 of the satellite momentum wheel bracket design method further specifically includes the following contents:

[0063] Step 210: Obtaining the installation angle α, the installation angle β and the installation angle γ of the momentum wheel;

[0064] Step 220: Draw the conical surface Y with the +X axis, +Y axis and +Z axis of the rectangular coordinate system as the axis 1 、Conical surface Y 2 and cone surface Y 3 , get the cone surface Y 1 、Conical surface Y 2 and cone surface Y 3 The intersection line S 1 .

[0065] Optionally, the step 210 of the satellite momentum wheel bracket design method further specifically includes the following contents:

[0066] Step 211: Receive the installation angle α, installation angle β and installation angle γ calculated by the attitude control subsystem.

[0067] like Figures 5 to 7As shown, in order to further improve production efficiency, in the satellite momentum wheel bracket design method provided in the embodiment of the present application, the step 300 of the satellite momentum wheel bracket design method includes:

[0068] Step 310: Draw the intersection line S 1 The plane L is the normal 1 , the plane L 1 Translate the preset distance to obtain the momentum wheel mounting surface L on the bracket 2 ;

[0069] Step 320: Mount the momentum wheel on the bracket according to the size of the momentum wheel. 2 Cut the installation section C from above 1 .

[0070] In the embodiment of the present application, the installation section C 1 The size should be slightly larger than the size of the contact surface on the momentum wheel for contact with the momentum wheel bracket. 2 Cut the installation section C from above 1 , and obtain C accordingly 2 , so that the size of the satellite momentum wheel bracket is close to the size of the momentum wheel, thereby making the satellite momentum wheel bracket occupy less space.

[0071] like Figures 8 to 10 As shown, in order to further improve production efficiency, after step 400 of the satellite momentum wheel bracket design method provided in the embodiment of the present application, the following steps are further included:

[0072] Step 010: Install section C according to the size of the momentum wheel 1 Draw the bracket installation interface J on 1 ;

[0073] Step 020: Draw the bracket and satellite installation interface J according to the installation position and size of the satellite momentum wheel bracket on the satellite 2 ;

[0074] Step 030: Entity Z 1 Weight reduction and process optimization. 1 After optimization, the final satellite momentum wheel bracket Z is obtained. 2 . For entity Z 1 After weight reduction and process optimization, a hollow J 3 .

[0075] In the satellite momentum wheel bracket design method provided in the embodiment of the present application, the installation angle α is 100.025°, and the installation angle β and the installation angle γ are both 134.1317°.

[0076] like Fig.11As shown, from the software level, the present application also provides a satellite momentum wheel bracket design device for executing all or part of the contents of the satellite momentum wheel bracket design method, and the satellite momentum wheel bracket design device specifically includes the following contents:

[0077] Coordinate system drawing module 10, used to draw the satellite upper plane L 0 , and draw a rectangular coordinate system that coincides with the satellite body coordinate system so that the X axis and Y axis of the rectangular coordinate system are located on the plane L 0 Inside.

[0078] The intersection line acquisition module 20 is used to draw the conical surface Y with the +X axis as the axis, the +Y axis as the axis and the +Z axis as the axis according to the installation angle α, the installation angle β and the installation angle γ of the momentum wheel calculated by the attitude control subsystem. 1 、Conical surface Y 2 and cone surface Y 3 , get the cone surface Y 1 、Conical surface Y 2 and cone surface Y 3 The intersection line S 1 .

[0079] The installation surface drawing module 30 is used to draw the intersection line S 1 The plane L is the normal 1 , the plane L 1 Translate the preset distance to obtain the momentum wheel mounting surface L on the bracket 2 , according to the size of the momentum wheel, the momentum wheel mounting surface L on the bracket 2 Cut the installation section C from above 1 ;

[0080] The mounting frame entity drawing module 40 is used to draw the mounting section C 1 Projection to L 0 Get section C 2 , at the installation section C 1 With the section C 2 Stretch entities between.

[0081] The embodiment of the satellite momentum wheel bracket design device provided in the present application can be specifically used to execute the processing flow of the embodiment of the satellite momentum wheel bracket design method in the above-mentioned embodiment. Its functions will not be repeated here, and reference can be made to the detailed description of the above-mentioned satellite momentum wheel bracket design method embodiment.

[0082] The satellite momentum wheel bracket design device can be used to design the satellite momentum wheel bracket in a server or client device. The specific selection can be based on the processing capability of the client device and the limitations of the user's usage scenario. This application does not limit this. If all operations are completed in the client device, the client device may also include a processor for specific processing of the satellite momentum wheel bracket design.

[0083] The client device may have a communication module (i.e., a communication unit) that can communicate with a remote server to achieve data transmission with the server. The server may include a server on the task scheduling center side, and other implementation scenarios may also include a server on an intermediate platform, such as a server on a third-party server platform that has a communication link with the task scheduling center server. The server may include a single computer device, or a server cluster consisting of multiple servers, or a server structure of a distributed device.

[0084] The server and the client device may communicate with each other using any suitable network protocol, including network protocols that have not yet been developed on the date of filing this application. The network protocols may include, for example, TCP / IP, UDP / IP, HTTP, HTTPS, etc. Of course, the network protocols may also include, for example, RPC (Remote Procedure Call Protocol) and REST (Representational State Transfer) protocols used on top of the above protocols.

[0085] The embodiment of the present application also provides an electronic device, which may include a processor, a memory, a receiver and a transmitter, wherein the processor is used to execute the satellite momentum wheel bracket design method mentioned in the above embodiment, wherein the processor and the memory may be connected via a bus or other means, such as by bus connection. The receiver may be connected to the processor and the memory via wired or wireless means.

[0086] The processor may be a central processing unit (CPU). The processor may also be other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or a combination of the above chips.

[0087] As a non-transient computer-readable storage medium, the memory can be used to store non-transient software programs, non-transient computer executable programs and modules, such as the program instructions / modules corresponding to the satellite momentum wheel bracket design method in the embodiment of the present application. The processor executes various functional applications and data processing of the processor by running the non-transient software programs, instructions and modules stored in the memory, that is, the satellite momentum wheel bracket design method in the above method embodiment is implemented.

[0088] The memory may include a program storage area and a data storage area, wherein the program storage area may store an operating system, an application required for at least one function; the data storage area may store data created by the processor, etc. In addition, the memory may include a high-speed random access memory, and may also include a non-volatile memory, such as at least one disk storage device, a flash memory device, or other non-volatile solid-state storage device. In some embodiments, the memory may optionally include a memory remotely arranged relative to the processor, and these remote memories may be connected to the processor via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0089] The one or more modules are stored in the memory, and when executed by the processor, the satellite momentum wheel bracket design method in the embodiment is executed.

[0090] In some embodiments of the present application, the user equipment may include a processor, a memory, and a transceiver unit, which may include a receiver and a transmitter. The processor, memory, receiver, and transmitter may be connected through a bus system. The memory is used to store computer instructions, and the processor is used to execute the computer instructions stored in the memory to control the transceiver unit to send and receive signals.

[0091] As an implementation method, the functions of the receiver and the transmitter in the present application can be considered to be implemented through a transceiver circuit or a dedicated chip for transceiver, and the processor can be considered to be implemented through a dedicated processing chip, a processing circuit or a general chip.

[0092] As another implementation method, it is possible to use a general-purpose computer to implement the server provided in the embodiment of the present application, that is, to store the program code for implementing the functions of the processor, receiver, and transmitter in a memory, and the general-purpose processor implements the functions of the processor, receiver, and transmitter by executing the code in the memory.

[0093] The embodiment of the present application also provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the steps of the satellite momentum wheel bracket design method are implemented. The computer-readable storage medium can be a tangible storage medium, such as a random access memory (RAM), a memory, a read-only memory (ROM), an electrically programmable ROM, an electrically erasable programmable ROM, a register, a floppy disk, a hard disk, a removable storage disk, a CD-ROM, or any other form of storage medium known in the technical field.

[0094] An embodiment of the present application also provides a computer program product, including a computer program, which, when executed by a processor, implements the steps of the aforementioned satellite momentum wheel bracket design method.

[0095] It should be understood by those skilled in the art that the exemplary components, systems and methods described in conjunction with the embodiments disclosed herein can be implemented in hardware, software or a combination of the two. Whether it is performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application. When implemented in hardware, it can be, for example, an electronic circuit, an application-specific integrated circuit (ASIC), appropriate firmware, a plug-in, a function card, etc. When implemented in software, the elements of this application are programs or code segments used to perform the required tasks. The program or code segment can be stored in a machine-readable medium, or transmitted on a transmission medium or a communication link via a data signal carried in a carrier.

[0096] It should be clear that the present application is not limited to the specific configuration and processing described above and shown in the figures. For the sake of simplicity, a detailed description of the known method is omitted here. In the above embodiments, several specific steps are described and shown as examples. However, the method process of the present application is not limited to the specific steps described and shown, and those skilled in the art can make various changes, modifications and additions, or change the order between the steps after understanding the spirit of the present application.

[0097] In the present application, features described and / or illustrated for one embodiment may be used in the same manner or in a similar manner in one or more other embodiments, and / or combined with features of other embodiments or replace features of other embodiments.

[0098] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the embodiments of the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A satellite momentum wheel bracket design method, characterized in that: include: Draw a plane L0 on the satellite, and draw a rectangular coordinate system that coincides with the satellite body coordinate system, so that the X axis and Y axis of the rectangular coordinate system are located in the plane L0; Obtaining the intersection line S1 of the conical surface Y1, the conical surface Y2 and the conical surface Y3 in the rectangular coordinate system according to the pre-obtained installation angle α, the installation angle β and the installation angle γ of the momentum wheel; Draw a plane L1 with the intersection line S1 as the normal, and obtain the installation section C1 corresponding to the plane L1; Projecting the installation section C1 onto the plane L0 to obtain the section C2, and stretching and forming a solid Z1 between the installation section C1 and the section C2; Among them, the installation angle α is the angle between the angular momentum direction of the momentum wheel and the +X axis, the installation angle β is the angle between the angular momentum direction of the momentum wheel and the +Y axis, the installation angle γ is the angle between the angular momentum direction of the momentum wheel and the +Z axis, and the conical surface Y1, the conical surface Y2 and the conical surface Y3 are drawn with the +X axis, the +Y axis and the +Z axis of the rectangular coordinate system as axes, respectively.

2. The satellite momentum wheel bracket design method according to claim 1, characterized in that: The method of obtaining the intersection line S1 of the conical surface Y1, the conical surface Y2 and the conical surface Y3 in the rectangular coordinate system according to the pre-acquired installation angle α, the installation angle β and the installation angle γ of the momentum wheel comprises: The installation angle α, the installation angle β and the installation angle γ of the momentum wheel are obtained.

3. The satellite momentum wheel bracket design method according to claim 2, characterized in that: The step of obtaining the installation angle α, the installation angle β and the installation angle γ of the momentum wheel comprises: Receive the installation angle α, installation angle β and installation angle γ calculated by the attitude control subsystem.

4. The satellite momentum wheel bracket design method according to claim 1, characterized in that: The drawing of the plane L1 with the intersection line S1 as the normal and obtaining the installation section C1 corresponding to the plane L1 includes: Draw a plane L1 with the intersection line S1 as the normal, and translate the plane L1 by a preset distance to obtain a momentum wheel mounting surface L2 on the bracket; According to the size of the momentum wheel, a mounting section C1 is cut from the momentum wheel mounting surface L2 on the bracket.

5. The satellite momentum wheel bracket design method according to claim 4, characterized in that: After projecting the installation section C1 to L0 to obtain the section C2, and stretching and forming a solid Z1 between the installation section C1 and the section C2, the method further includes: Draw the bracket mounting interface J1 on the mounting section C1 according to the size of the momentum wheel; Draw the bracket and satellite installation interface J2 according to the installation position and size of the satellite momentum wheel bracket on the satellite; The physical Z1 is reduced in weight and its process is optimized.

6. The satellite momentum wheel bracket design method according to any one of claims 1 to 5, characterized in that: The installation angle α is 100.025°, and the installation angle β and the installation angle γ are both 134.1317°.

7. Satellite momentum wheel bracket design device, characterized in that: include: A coordinate system drawing module is used to draw a plane L0 on the satellite and draw a rectangular coordinate system that coincides with the satellite body coordinate system, so that the X axis and the Y axis of the rectangular coordinate system are located in the plane L0; The intersection line acquisition module is used to draw the conical surface Y1, the conical surface Y2 and the conical surface Y3 with the +X axis as the axis, the +Y axis as the axis and the +Z axis as the axis according to the installation angle α, the installation angle β and the installation angle γ of the momentum wheel calculated by the attitude control subsystem, and obtain the intersection line S1 of the conical surface Y1, the conical surface Y2 and the conical surface Y3; The installation surface drawing module is used to draw a plane L1 with the intersection line S1 as the normal, translate the plane L1 by a preset distance to obtain the momentum wheel installation surface L2 on the bracket, and cut the installation section C1 on the momentum wheel installation surface L2 on the bracket according to the size of the momentum wheel; The mounting frame entity drawing module is used to project the mounting section C1 to L0 to obtain the section C2, and to stretch the entity between the mounting section C1 and the section C2.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the satellite momentum wheel bracket design method as described in any one of claims 1 to 6 is implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the satellite momentum wheel bracket design method as described in any one of claims 1 to 6 is implemented.

10. Computer program product comprising a computer program, characterized in that When the computer program is executed by a processor, the satellite momentum wheel bracket design method as described in any one of claims 1 to 6 is implemented.

Images