Satellite attitude maneuvering method based on subsection control

A technology of satellite attitude and segmental control, applied in the field of satellite attitude maneuvering
CN106945849AActive Publication Date: 2017-07-14SHANGHAI AEROSPACE CONTROL TECH INST
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Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Applications(China)
Current Assignee / Owner
SHANGHAI AEROSPACE CONTROL TECH INST
Publication Date
2017-07-14

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Abstract

The invention discloses a satellite attitude maneuvering method based on subsection control. The method comprises the following steps that attitudes of a satellite in the attitude maneuvering process are determined; acceleration, constant velocity and deceleration maneuvering control is conducted on the direction of a satellite rolling axis; the direction of the satellite rolling axis is stably controlled; maneuvering control is conducted on the directions of a satellite pitch axis and a satellite yaw axis; and the satellite rolling axis, the satellite pitch axis and the satellite yaw axis are switched into a homeostatic state control mode. According to the method, by means of symmetry of acceleration and deceleration of the maneuvering process, the attitude maneuvering of the satellite can be autonomously divided into the processes of acceleration, constant velocity, deceleration, fast steadiness and homeostatic control, the processes are controlled correspondingly, and the maneuvering process is automatically interlocked.
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Description

technical field

[0001] The invention relates to a satellite attitude maneuvering method, in particular to a satellite attitude maneuvering method based on segment control. Background technique

[0002] With the improvement of satellite user requirements, in order to shorten the revisit period, many satellites require the attitude control system not only to achieve high-precision and high-stability control, but also to have the ability to quickly maneuver the attitude, expand the observation range, and improve the effective utilization of the payload.

[0003] There is no relevant technical record in the prior art to solve the problem of satellite rapid maneuvering attitude control. SUMMARY OF THE INVENTION

[0004] The purpose of the present invention is to provide a satellite attitude maneuver method based on segmented control, the method utilizes the symmetry of acceleration and deceleration in the maneuvering process, and can autonomously divide the satellite attitude m...

Claims

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