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Satellite attitude maneuvering method based on subsection control

A technology of satellite attitude and segmental control, applied in the field of satellite attitude maneuvering

Active Publication Date: 2017-07-14
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

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

Method used

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  • Satellite attitude maneuvering method based on subsection control
  • Satellite attitude maneuvering method based on subsection control
  • Satellite attitude maneuvering method based on subsection control

Examples

Experimental program
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Embodiment Construction

[0051] The present invention will be further elaborated below by describing a preferred specific embodiment in detail with reference to the accompanying drawings.

[0052] like figure 1 As shown, a method for maneuvering satellite attitude based on segmented control, the method comprises the following steps:

[0053] Determine the attitude of the satellite during the attitude maneuver;

[0054] Carry out acceleration, constant speed, and deceleration maneuver control on the direction of the satellite's rolling axis;

[0055] Stabilize the direction of the satellite roll axis;

[0056] Carry out maneuver control on the pitch axis and yaw axis direction of the satellite respectively;

[0057] Switches the satellite's roll, pitch and yaw axes to steady state control.

[0058] The above-mentioned attitude determination in the process of satellite attitude maneuvering specifically includes:

[0059] The satellite uses the inertial angular velocity of the star to perform quaterni...

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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.

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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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24B64G1/10
CPCB64G1/10B64G1/24B64G1/245
Inventor 钟超王文妍石晓涵秦捷陈撼
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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