Satellite star sensor pointing on-orbit thermal deformation correction system

Abstract

The invention provides an on-orbit correction system for pointing thermal deformation of a satellite star sensor. The on-orbit correction system comprises a symmetrically designed large planar antennaload, a temperature sensor, the star sensor and ground high-precision angle measurement equipment; the star sensor is installed in the center of the symmetrically-designed large planar antenna load,and the temperature sensor is installed in the middle of the symmetrically-designed large planar antenna load. During the power-up test of the ground large-scale planar antenna load, the real-time deformation data pointed by the star sensor and measured by the ground high-precision angle measuring equipment is collected; and the temperature sensor collects temperature change data of the ground large planar antenna in a load power-up period, and corrects the on-orbit star sensor pointing direction according to the relationship between the real-time deformation data of the star sensor pointing direction and the temperature change data of the temperature sensor. The system has the advantages of being simple in implementation system and capable of achieving on-orbit real-time correction.

Description

technical field [0001] The invention relates to an on-orbit correction system, in particular to an on-orbit correction system for pointing thermal deformation of a satellite star sensor. Background technique [0002] The star sensor is the most accurate pointing measurement element on the satellite, and its pointing measurement accuracy directly determines the accuracy of the satellite attitude and orbit control, thus directly affecting the pointing accuracy of the satellite payload. In the conventional design method, the thermal deformation control needs to be carried out separately in the design of the large planar antenna load and the design of the star sensor bracket. [0003] The large-scale planar antenna has a large load area. In the conventional design, the support structures such as the mounting frame, mounting plate, and deployment mechanism are all made of materials with low thermal expansion coefficients. However, temperature changes still have a certain impact o...

AI Technical Summary

Problems solved by technology

[0006] In the conventional design, when the large-scale planar antenna load and the star sensor bracket are respectively installed on the satellite body, the thermal deformation of the satellite body caused by temperature changes has a certain influence on the pointing of the star sensor and the large-scale planar antenna load; the large-scale planar antenna load When the star sensor bracket is integrated with the design, it fails to consider the thermal deformation and pointing correction of the star sensor in orbit

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