Double star formation control closed loop testing system and method under whole start condition

Abstract

The invention provides a double star formation control closed loop testing system and method under the whole start condition. The system comprises an attitude and orbit control computer, a star sensor, a gyroscope combination, a reaction flywheel, a magnetorquer, a valve line box, a comprehensive electronic management unit, a concomitant star GNSS receiver, a primary star GNSS receiver, a GPS guide star analog module, a BD guide star analog module, a radio frequency modulation module, a navigation simulator upper computer, an orbital dynamics module, an attitude dynamics module, a signal acquisition module, and an electrical signal source module, wherein the attitude and orbit control computer is connected with the star sensor and the gyroscope combination through a universal serial bus. The system has the advantages of being high in real-time performance, high in data stability, good in adaptability and the like, and the problem of loop formation control closed loop testing of physical products on stars is solved.

Description

technical field [0001] The invention relates to a space vehicle ground test technology, in particular to a double-star formation control closed-loop test system and method under the whole star condition. Background technique [0002] With the development of aerospace technology, satellite formation flight technology has been more and more widely used. Through the in-orbit formation flight of two or more satellites and inter-satellite cooperation, the functions that cannot be realized by a single satellite can be realized. According to the formation flight mission The requirements are different. In order to ensure the implementation of on-orbit missions, formation configuration control generally includes three types of satellite formation configuration initialization, configuration maintenance, and configuration reconfiguration control. The first prerequisite for formation configuration control is to obtain formation configuration Parameters, generally by installing GNSS rece...

AI Technical Summary

Problems solved by technology

[0003] Aiming at the defects in the prior art, the object of the present invention is to provide a double-satellite formation control closed-loop test system and method under the condition of the entire satellite, which has the

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