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Title:
ATTITUDE CONTROL METHOD FOR FINAL SUBSTAGE ORBITAL APPLICATION SUBSYSTEM
Document Type and Number:
WIPO Patent Application WO/2020/103290
Kind Code:
A1
Abstract:
An attitude control method for a final substage orbital application subsystem, comprising: when the final substage orbital application subsystem is in a rate damping phase, an attitude controller utilizes a minus B-dot magnetic control law, and uses a three-axis magnetorquer as an execution mechanism to exert a control magnetic torque in order to damp the angular velocity of the final substage orbital application subsystem in the pitch axis, roll axis, and yaw axis, performing despinning processing on the final substage orbital application subsystem; and when the final substage orbital application subsystem is in a steady-state control phase, the attitude controller, in a pitch loop, utilizes a PD control law having dead time compensation, and uses a bias momentum wheel and the three-axis magnetorquer as execution mechanisms to exert a control magnetic torque in order to complete pitch loop attitude control, and roll/yaw loops are designed using a sliding mode controller. The present method solves the problem of sun pointing in final substage orbital application subsystems, while also eliminating the impact of dead time, and raising the accuracy of attitude control in final substage orbital application subsystems.

Inventors:
ZENG ZHANKUI (CN)
ZHENG QI (CN)
ZOU XU (CN)
JIANG LILI (CN)
QING ZHINENG (CN)
WU JUNJIE (CN)
WEI RAN (CN)
JIANG WEI (CN)
WAN YUZHU (CN)
Application Number:
PCT/CN2018/124508
Publication Date:
May 28, 2020
Filing Date:
December 27, 2018
Export Citation:
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Assignee:
SHANGHAI ASES SPACEFLIGHT TECH LIMITED COMPANY (CN)
International Classes:
B64G1/28; B64G1/36
Foreign References:
CN103112602A2013-05-22
CN106915477A2017-07-04
CN104527994A2015-04-22
EP0603869A11994-06-29
JPH0789499A1995-04-04
Attorney, Agent or Firm:
SHANGHAI IPOWER LAW OFFICE (CN)
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