Modular assembly small satellite platform with adjustable quality characteristic

Abstract

The invention discloses a modular assembly small satellite platform with adjustable quality characteristic, and relates to the field of precise attitude and orbit control of satellite; the modular assembly small satellite platform comprises an attitude and orbit control module, two solar panel modules, a vertebral column module, a load module, a communication module and n centroid adjusting modules; the vertebral column module is of a square column structure; the vertebral column module is vertically arranged; the attitude and orbit control module is fixedly arranged on the upper surface of the vertebral column module; two solar panel modules are symmetrically and fixedly arranged on the two sides of the top end of the vertebral column module; the load module is fixedly arranged at the bottom of the vertebral column module; the communication module is fixedly arranged at one side of the load module; the n centroid adjusting modules are fixedly arranged inside the vertebral column module or the other side of the load module; and n is an integer greater than or equal to 1. The existing design process of design, test and balance weight of the quality characteristics of the small satellite are changed, development cycle is shortened, and the quality characteristics control of the modular assembly small satellite on orbit can be realized at the same time.

Description

technical field [0001] The invention relates to the field of precise attitude and orbit control of satellites, in particular to a modular assembly small satellite platform with adjustable mass characteristics. Background technique [0002] Satellite mass characteristics mainly include satellite mass center, mass, moment of inertia and product of inertia, which is an important factor affecting the satellite's precise attitude and orbit control. [0003] In order to achieve high-precision attitude and orbit control in complex tasks, a very small number of foreign satellites have begun to use mass characteristic adjustment mechanisms. For example, the Gravity Probe B (GP.B) satellite developed by Stanford University in the United States is used to verify Einstein’s general theory of relativity. The center of mass and the moment of inertia make the deviation between the attitude and orbit control coordinate system and the satellite body coordinate system as small as possible, s...

AI Technical Summary

Problems solved by technology

This counterweight method leads to a long satellite design cycle and complicated process, which is not conducive to the rapid response of small satellite development and production

In addition, the counterweight is fixedly connected to the satellite structure, and position adjustment cannot be achieved during the orbital flight phase

Images