Load modularization method and system of CubeSat architecture

Abstract

The invention relates to a load modularization method and system of a CubeSat architecture. A main structure frame, an antenna mounting frame arranged at the top of the main structure frame, stringers arranged at the bottom of the main structure frame, a biological load cabin module, a power supply power module and a central control module are modularly assembled; the biological load cabin module is mounted in the inner side of the main structure frame through a milled vertical positioning slide way; the power supply power module and the central control module are connected and assembled into a whole and then are screwed with the main structure frame; the biological load cabin module and a propulsion module are respectively positioned at the upper and lower ends of a star and are structurally restrained and fixed by positioning pins; a positioning pin bulge structure is milled at one end of a top cover of the biological load cabin module and is connected with the assembled adapter plate of the power supply power module and the central control module in a plugging manner; and one end of the bottom surface of the biological load cabin module shell comprises a positioning pin hole structure which is connected with a stringer and a positioning pin on the antenna mounting frame in a plugging manner. The system has the advantages of high reliability, simple inner cabin and convenience in assembly and maintenance.

Description

technical field [0001] The present invention relates to a cube star architecture modularization method, in particular to a cube star architecture load modularization method and system. Background technique [0002] In recent years, as industry users and commercial users have increased their demands for rapid, flexible, and individualized satellite technology applications, commercial small satellites have developed rapidly, and various domestic commercial satellite companies have appeared one after another. Commercial small satellites are small in size, low in cost, and short in development cycle, making them especially suitable for space exploration tasks such as scientific experiments. [0003] The structural design and layout of the star directly affect the overall performance of the star and the convenience of assembly and maintenance operations. The traditional barrel and plate satellites have their own limitations. There are many components in the star, the wiring is co...

AI Technical Summary

Problems solved by technology

[0003] The structural design and layout of the star directly affect the overall performance of the star and the convenience of assembly and maintenance operations. The traditional barrel and plate satellites have their own limitations. There are many components in the star, the wiring is complicated, and the space utilization rate is not high. , and the assembly operation is not very convenient. As one of the more mature star structures, the truss-type cube star is composed of multiple main frame beams and side beams, and has broad market application prospects.

However, in actual use, due to the complex structure of the star body, the system modules such as the biological load compartment are inconvenient to disassemble, repair and replace, which directly affects the usability of the product for users, and increases the workload of assembly and debugging personnel, reducing production and production efficiency

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