CN-121973955-A - Integrated ultra-flat satellite total architecture

CN121973955ACN 121973955 ACN121973955 ACN 121973955ACN-121973955-A

Abstract

An integrated ultra-flat satellite total architecture belongs to the technical field of satellite structure design. The invention aims at solving the problem that the main structure size of the existing satellite can not be adjusted according to the requirement, and the independent deployment of the flywheel causes structural redundancy. The solar cell module comprises a main structure plate, an electronic board, an external plug-in unit, a solar cell array, a flywheel, an X-direction attitude control flywheel and a Y-direction attitude control flywheel, wherein the main structure plate is of a sandwich structure formed by compositing an asphalt-based carbon fiber skin and a cyanate ester core, the electronic board is buried in the cyanate ester core of the main structure plate, the external plug-in unit is vertically arranged on the electronic board and extends out through a reserved hole site on the asphalt-based carbon fiber skin, the back of the main structure plate is stuck with the solar cell array, the shape and the thickness of the main structure plate are cut and adjusted according to satellite task requirements, and a selected area of the main structure plate is cut to obtain the flywheel, and the X-direction attitude control flywheel and the Y-direction attitude control flywheel are mutually and orthogonally arranged on the main structure plate. The invention can greatly save the internal space of the satellite and improve the running stability of the flywheel.

Inventors

GUO JINSHENG
WU FAN
LI ANKANG
SUN MAOJIN
WANG GUANQI
LU YICHENG
XIE QIHANG
ZHAO ZICHEN

Assignees

哈尔滨工业大学

Dates

Publication Date: 20260505
Application Date: 20260316

Claims (10)

1. An integrated ultra-flat satellite total architecture is characterized by comprising a flat satellite unit, wherein the flat satellite unit comprises a main structural board serving as a satellite platform, an electronic board, an external plug-in unit, a solar cell array and a flywheel, The main structural plate is of a sandwich structure formed by compositing an asphalt-based carbon fiber skin and a cyanate ester core; the electronic board is buried in the cyanate ester core of the main structure board; the external plug-in is vertically arranged on the electronic board, extends out from a reserved hole site on the asphalt-based carbon fiber skin and is used for being connected with each platform or each loading single machine; the shape and thickness of the main structure plate are cut and adjusted according to satellite task requirements, and a selected area of the main structure plate is cut to obtain a flywheel, wherein the flywheel comprises an X-direction attitude control flywheel and a Y-direction attitude control flywheel, and the X-direction attitude control flywheel and the Y-direction attitude control flywheel are mutually orthogonally arranged on the main structure plate.
2. The integrated ultra-flat satellite total architecture according to claim 1, wherein a driving motor and a speed sensor are respectively integrated in the X-direction attitude control flywheel and the Y-direction attitude control flywheel, the X-direction attitude control flywheel and the Y-direction attitude control flywheel are driven by the driving motor to rotate around a central axis of the driving motor, and the stable control of the attitude of the main structural plate in the X-axis and the Y-axis directions is realized by utilizing an angular momentum effect; The X-direction attitude control flywheel and the Y-direction attitude control flywheel are provided with embedded reinforcing structures at the connection positions with the main structural plate, the profile edges of the X-direction attitude control flywheel and the Y-direction attitude control flywheel are provided with counterweight structures, and the X-direction attitude control flywheel and the Y-direction attitude control flywheel are locked in state through electromagnetic valve rotation locking mechanisms arranged on the main structural plate.
3. The integrated ultra-flat satellite total architecture according to claim 2, wherein a standardized antenna connection interface and a positioning pin are preset on an antenna installation surface of the main structural board, and are used for integrally hoisting and fixing the SAR phased array antenna on the installation surface.
4. The integrated ultra-flat satellite total architecture according to claim 3, wherein a clipping identifier is preset on the main structural board for marking clipping tabu areas.
5. The integrated ultra-flat satellite total architecture according to claim 1, wherein the cutting cuts of the main structural plate, the X-direction attitude control flywheel and the Y-direction attitude control flywheel are subjected to edge sealing treatment by adopting high-temperature-resistant sealant.
6. The integrated ultra-flat satellite total architecture according to claim 1, wherein the number of the flat satellite units is plural, standardized positioning grooves are formed in the outer contour of each flat satellite unit, the plurality of flat satellite units are connected with the standardized positioning grooves at corresponding positions through a distribution mechanism to form a stacked state, and locking electromagnetic valves are arranged on the distribution mechanism to fix all the flat satellite units into a whole.
7. The integrated ultra-flat satellite total architecture according to claim 6, wherein the distribution mechanisms are uniformly arranged in four sets along the outer contour of the flat satellite unit, each set of distribution mechanisms comprises a vertical guide rail, a plurality of locking solenoid valves, a plurality of star connecting blocks, a push block and a hydraulic rod, and the four sets of distribution mechanisms are all connected to a central supporting structure; The device comprises a vertical guide rail, a plurality of locking electromagnetic valves, a star connecting block, a plurality of locking electromagnetic valves, a locking electromagnetic valve and a locking electromagnetic valve, wherein the vertical guide rail is used as a track for stacking and sliding flat satellite units; the central supporting structure is fixed on the rocket or the female satellite platform, and is connected with the corresponding pushing blocks through each hydraulic rod, and the pushing blocks push the star connecting blocks to move upwards along the vertical guide rails through the extension of the hydraulic rods, so that the flat satellite units are separated from the vertical guide rails, and further separated from the rocket or the female satellite platform.
8. The integrated ultra-flat satellite architecture according to claim 7, wherein standardized mechanical arm connection interfaces and high-speed communication interfaces are integrated on the outer profile of the flat satellite unit.
9. The integrated ultra-flat satellite total architecture according to claim 8, wherein the flat satellite unit further comprises a small robotic arm for implementing connection with a standardized robotic arm connection interface on-orbit and coordinated control via a high-speed communication interface.
10. The integrated ultra-flat satellite architecture according to claim 9, wherein a plurality of flat satellite units are connected in-orbit by a small robotic arm to form a flat plate.

Description

Integrated ultra-flat satellite total architecture Technical Field The invention relates to an integrated ultra-flat satellite total architecture, and belongs to the technical field of satellite structure design. Background At present, with the rapid development of technology in the aerospace field, the threshold of satellite design and emission is continuously reduced, the demands of various industries on satellites are increasing, and higher requirements on the integration level, load adaptability, emission efficiency and task flexibility of the satellites are provided. The traditional satellite development adopts a mode of load demand-platform customization, and each subsystem of electronics, structure, attitude and orbit control and the like is independently developed and then combined test and assembly are carried out, so that a plurality of inherent short plates exist: firstly, the independent design of the subsystem leads to low integration level, and the assembly of the electronic components and the structural parts is complicated, so that the assembly efficiency is obviously reduced, and the problems of poor heat dissipation performance, poor mechanical stability and the like are also caused; secondly, the attitude control depends on flywheel components which are independently arranged, occupies a large amount of internal space and causes structural redundancy; thirdly, the satellite main structure size is fixed, can not be flexibly adjusted according to load requirements, and has poor universality. Disclosure of Invention Aiming at the problem that the main structure size of the existing satellite can not be adjusted according to the requirement, and the independent deployment of the flywheel causes structural redundancy, the invention provides an integrated ultra-flat satellite total architecture. The invention relates to an integrated ultra-flat satellite total architecture, which comprises a flat satellite unit, wherein the flat satellite unit comprises a main structural board serving as a satellite platform, an electronic board, an external plug-in unit, a solar cell array and a flywheel, The main structural plate is of a sandwich structure formed by compositing an asphalt-based carbon fiber skin and a cyanate ester core; the electronic board is buried in the cyanate ester core of the main structure board; the external plug-in is vertically arranged on the electronic board, extends out from a reserved hole site on the asphalt-based carbon fiber skin and is used for being connected with each platform or each loading single machine; the shape and thickness of the main structure plate are cut and adjusted according to satellite task requirements, and a selected area of the main structure plate is cut to obtain a flywheel, wherein the flywheel comprises an X-direction attitude control flywheel and a Y-direction attitude control flywheel, and the X-direction attitude control flywheel and the Y-direction attitude control flywheel are mutually orthogonally arranged on the main structure plate. According to the integrated ultra-flat satellite total architecture, the driving motor and the speed measuring sensor are respectively integrated in the X-direction attitude control flywheel and the Y-direction attitude control flywheel, the X-direction attitude control flywheel and the Y-direction attitude control flywheel are driven to rotate around the central axis of the flywheel by the driving motor, and the stable control of the attitude of the main structural plate in the X-axis and the Y-axis directions is realized by utilizing the angular momentum effect; The X-direction attitude control flywheel and the Y-direction attitude control flywheel are provided with embedded reinforcing structures at the connection positions with the main structural plate, the profile edges of the X-direction attitude control flywheel and the Y-direction attitude control flywheel are provided with counterweight structures, and the X-direction attitude control flywheel and the Y-direction attitude control flywheel are locked in state through electromagnetic valve rotation locking mechanisms arranged on the main structural plate. According to the integrated ultra-flat satellite total architecture, the antenna installation surface of the main structural plate is preset with a standardized antenna connection interface and a positioning pin, and the standardized antenna connection interface and the positioning pin are used for integrally hoisting and fixing the SAR phased array antenna on the installation surface. According to the integrated ultra-flat satellite total architecture, the cutting mark is preset on the main structural board and is used for marking the cutting tabu area. According to the integrated ultra-flat satellite total architecture, the cutting cuts of the main structural plate, the X-direction attitude control flywheel and the Y-direction attitude control flywheel are subjected to edge sealing treatment by adopt