Attitude control method of flexible spacecraft

A technology of attitude control and attitude angle, which is applied in the field of spacecraft, can solve the problem of inapplicability of large-angle maneuvering of spacecraft attitude, and achieve the effect of avoiding excessive control gain and having robustness

Active Publication Date: 2019-01-25
BEIHANG UNIV
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Problems solved by technology

The variable parameter model obtained after this process is only suitable for discussing the situation where the attitude angle is near the balance point, and it is not suitable for the large-angle maneuver of the spacecraft attitude

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  • Attitude control method of flexible spacecraft

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Embodiment Construction

[0021] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0022] In order to overcome the above-mentioned problems in the prior art, the embodiment of the present invention provides an attitude control method for a flexible spacecraft. The quantity satisfies: N={x(0)∈R n |x(0)=Uv, U≠0, v T v≤1}, where N is the definition space of the initial state quantity, x(0) represents the initial state quantity, R...

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Abstract

An embodiment of the invention provides an attitude control method of a flexible spacecraft. The attitude control method comprises the steps of: regarding a vector portion of an error attitude quaternion at a current moment as variable parameters of a variable gain controller, and combining a control gain restriction condition to obtain control gain at the current moment; regarding the error attitude quaternion, an error attitude angular speed and a control moment at the current moment as input parameters of a dimensionality reduction observer, and acquiring estimated values of modal coordinates of a flexible attachment at the current moment and estimated values of parameter variables; and regarding the vector portion of the error attitude quaternion at the current moment, the control gain, an error attitude angular speed, the estimated values of the modal coordinates and the estimated values of the parameter variables as input of the variable gain controller, and outputting a controlmoment at a next moment. The attitude control method enables a system which is externally disturbed to complete high-precision attitude maneuvering tasks, and achieves the purpose of limiting the control gain through introducing additional linear matrix inequality constraints.

Description

technical field [0001] The invention relates to the technical field of spacecraft, and more particularly, to an attitude control method of a flexible spacecraft. Background technique [0002] The attitude maneuver control technology of spacecraft is one of the key technologies for spacecraft in-orbit applications. It is the basic link for tasks such as cooperative target rendezvous and docking, non-cooperative target tracking and flying around, and cluster spacecraft attitude coordination. [0003] The attitude control method for rigid spacecraft can solve the large-angle attitude maneuver problem of rigid spacecraft, but for spacecraft with flexible attachments, if the influence of the flexible mode is not considered, the system may be unstable. Although adding patches such as piezoelectric ceramics (PZT) on the sailboard can achieve active vibration suppression for flexible accessories, but due to the introduction of new additional structures, the overall vibration modal p...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/0808G05D1/0816G05D1/0825
Inventor 师鹏雷冰瑶刘思帆程琦翔赵育善
Owner BEIHANG UNIV
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