On-satellite configuration layout determining method of multi-field-of-view star sensors

Abstract

Disclosed is an on-satellite configuration layout determining method of multi-field-of-view star sensors. Firstly, all possible optical axis orientations of the three star sensors are traversed according to a satellite Pro / E three-dimensional model, and then feasible solution sets which meet the requirement of a star stray radiation suppression angle of the star sensors are obtained; then feasible solution sets meeting the requirements of a sunlight suppression angle and a geogas light suppression angle at a zero attitude are obtained according to the feasible solution sets meeting the requirement of the star stray radiation suppression angle of the star sensors; and finally feasible solution sets meeting the requirements of the sunlight suppression angle and the geogas light suppression angle at a non-zero attitude are figured out, and therefore ultimate on-satellite configuration layout orientations of the multi-field-of-view star sensors are finished. Compared with the prior art, the method has the engineering practicability, is better than manual experience trial assembly in directivity and effectiveness and is excellent in practical effect.

Description

technical field [0001] The invention relates to a method for determining the on-board configuration layout of a multi-field star sensor, which is suitable for the field of view analysis and configuration layout design of the star sensor in the satellite scheme design stage. Background technique [0002] With the rapid development of satellite technology, the requirements for satellite attitude determination accuracy and image positioning accuracy have been continuously improved. The star sensor has the advantages of strong autonomy, high measurement accuracy, and no cumulative attitude error. The satellite's most important attitude measurement component, the on-board configuration layout design of the multi-field star sensor will directly affect the satellite's attitude measurement accuracy. [0003] When designing the configuration and layout of the star sensor, there are many constraints. It is necessary to consider whether the satellite body, large components installed on...

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Problems solved by technology

[0005] (1) The above method requires a high level of work experience for the designer, and there may be no experience for the star sensor layout of new satellites in the future, and it is not easy to find the available space for the star sensor layout on the star;

[0006] (2) The above method has the problem of repeated iterations of star sensor star layout and on-orbit field of view simulation analysis. Each repeated layout and simulation will bring a large workload, long design cycle, and low design efficiency.

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