A two-dimensional centroid trimming device for a cube star

Abstract

The invention discloses a two-dimensional center of mass balance device for a cube star, which includes a mass block mounting plate, four coarse adjustment mass blocks and four fine adjustment mass blocks. The axis Y is divided into four areas, each area is provided with an empty slot, and the four empty slots are symmetrically arranged along the center point, and a guide rail slot is provided between every two adjacent empty slots, and the four guide rail slots are arranged along the center point. The center point is symmetrically arranged, and there are multiple mounting holes evenly distributed around each empty slot. There is a bar-shaped hole on both sides of the coarse adjustment mass. The fine adjustment mass can be embedded in the guide rail groove and move axially along the guide rail groove. At least one first threaded hole is provided through the fine adjustment mass. The present invention can quickly and accurately realize the balance of the two-dimensional center of mass of the cubesat by using the two-dimensional centroid adjustment module installed on the top of the cubesat without affecting the satellite assembly test and changing the internal structure design of the satellite.

Description

technical field [0001] The invention relates to the technical field of cube stars, in particular to a two-dimensional center-of-mass trimming device for a cube star. Background technique [0002] With the development of machinery, electronics and other industries towards miniaturization and intelligence, cube satellites have become one of the mainstream research directions in spacecraft. At present, the orbital maneuverability of cubesats is relatively immature compared with other platforms on the star. Solid propulsion technology has become the current technology due to its advantages such as high density impulse, small volume occupied in the star, simple structure, short working time, and reliable performance. Among the various propulsion system modes of CubeSat orbital maneuvering missions, one propulsion mode with obvious advantages has wide application prospects. In the solid propulsion system, the offset of the center of mass of the satellite leads to a deviation betw...

AI Technical Summary

Problems solved by technology

In the solid propulsion system, the offset of the center of mass of the satellite leads to a deviation between the inertial axis of the star and the longitudinal axis of the thruster, which will inevitably cause the thrust eccentricity of the solid rocket thruster

Due to the large solid propulsion thrust, the resulting thrust eccentric moment can easily cause the satellite attitude to flip out of control

[0003] At present, there is a counterweight method for the center of mass balance, such as the patent CN201110273085.7, which achieves the balance of the center of mass by increasing the counterweight. large, less accurate

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