Spacecraft sun-pointing target coordinate system determination method beneficial to heat balance

Abstract

A spacecraft sun-pointing target coordinate system determination method beneficial to heat balance is provided. The method comprises the following steps: (1) determining axes in the three axes of thestar body which need to respectively point to the sun vector and the geocentric vector when the satellite is in a nominal attitude in the sun-pointing target coordinate system, determining a prioritydirection, and on the basis of the priority direction, calculating the vector representation of the three-axis nominal direction of the star body in the sun-pointing target coordinate system; and (2)according to the component representation and the adjustment matrix of the sun vector and the geocentric vector in the reference coordinate system specified by the satellite attitude, giving a transformation matrix expression for the sun-pointing target coordinate system relative to the reference coordinate system. Based on ensuring that the satellite fixed windsurfing plate faces the sun-pointingfunction, when the satellite flies along the attitude of the sun-pointing target coordinate system determined by using the method provided by 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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