A Method for Determining the Coordinate System of Spacecraft's Orientation Target to the Sun Conducive to Thermal Balance

Abstract

A method for determining the coordinate system of a spacecraft orientation target to the sun, which is beneficial to thermal balance, includes the following steps: (1) When determining the nominal attitude of the satellite in the coordinate system of the orientation target to the sun, the three axes of the star body need to point to the sun vector and the center of the earth respectively The axis of the vector, and determine the priority direction; calculate the vector representation of the three-axis nominal direction of the star body in the sun orientation target coordinate system based on the priority direction; (2) according to the reference coordinates specified in the satellite attitude by the sun vector and the earth center vector The component representation and adjustment matrix of the system give the transformation matrix expression of the sun-oriented target coordinate system relative to the reference coordinate system. On the basis of ensuring the sun-facing function of the fixed sailboard of the satellite, when the satellite is flying along the attitude of the sun-orientation target coordinate system determined by the method of the present invention, a certain side will always face the cold space.

Description

technical field [0001] The invention belongs to the field of attitude determination and control of spacecraft, and relates to a method for determining a coordinate system of an orientation target of a spacecraft to the sun. Background technique [0002] In order to ensure the energy balance of the whole satellite, satellites with fixed sailboards often need to switch between sun-orientation and ground-orientation attitudes autonomously within one orbital cycle, which poses a problem for the design of satellite thermal balance. In the sunny area, when the satellite has an imaging task, it needs to be oriented to the ground. For a satellite in the morning orbit at the descending node, its side close to the negative normal of the orbit is generally not exposed to the sun. The heat balance of the star; for satellites in the afternoon orbit at the place of the descending node, the opposite is true. And when the satellite has no imaging task in the sunny area, the satellite sailb...

AI Technical Summary

Problems solved by technology

And when the satellite has no imaging task in the sunny area, the satellite sailboard faces the sun to charge the whole star. According to the existing sun-orientation method, the orientation of the heat dissipation surface may face the cold space or the earth side. If it is on the earth side, it will have an adverse effect on the heat dissipation function

Correspondingly, for some loads with thermal insulation requirements, the heat balance design usually requires avoiding the cold space but facing the earth to make full use of the earth's radiation heating, and the existing sun-oriented method is also difficult to solve this kind of demand

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