Cubesat two-dimensional centroid adjusting method

Abstract

The invention discloses a cubesat two-dimensional centroid adjusting method. The method comprises the following steps of step one, adjusting an upper surface of a horizontal table board to horizontalthrough a horizontal adjusting mechanism; step two, establishing a satellite body coordinate system and a triaxial accelerometer body coordinate system; step three, placing a triaxial accelerometer measurement module on the horizontal table board, and calibrating a triaxial accelerometer; step four, suspending the triaxial accelerometer measurement module, and adjusting the centroid of the measurement module to a center of form location; step five, installing the triaxial accelerometer measurement module on the top of the cubesat; step six, suspending the cubesat through a suspending mechanism, and reading a measurement value of the triaxial accelerometer measurement module in the premise that the satellite is stable, and judging a centroid offset direction and an offset location size; andstep seven, adjusting the cubesat to the geometric longitudinal axis location through the centroid adjusting module. The centroid adjusting method disclosed by the invention is high in precision, good in practicability and convenience.

Description

technical field [0001] The invention relates to the technical field of cube stars, in particular to a method for adjusting a two-dimensional center of mass of a cube star. Background technique [0002] With the rapid development of information technology and miniaturization technology, cube satellites are showing a new trend of rapid development in the field of space science, because they have low cost, batch production, rapid launch of multiple satellites with one arrow, and rapid networking that cannot be compared with traditional large satellites. The application prospects in the military and commercial fields have attracted great attention from all countries, and are regarded as the commanding heights of technological and economic development in the aerospace field. "Clustering" and "distributed" applications require micro-nano satellites to have strong orbital maneuverability. The application of solid rocket thrusters to cube satellites has many advantages, and is usua...

AI Technical Summary

Problems solved by technology

The deviation of the center of mass of the satellite system will lead to a deviation between the actual principal axis of inertia and the geometric longitudinal axis. This is one of the factors that cause the thrust eccentricity of the solid rocket thruster. The thrust eccentric moment will cause the satellite attitude to flip, thus making the rapid orbit maneuver mission fail.

The existing centroid adjustment methods include inclined platform method, multi-point support method, etc. Most of these methods demonstrate the feasibility of the method from the perspective of theore

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