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Path planning based flexible spacecraft attitude adaptive control method

A flexible spacecraft, adaptive control technology, applied in the direction of attitude control, space navigation aircraft, aircraft, etc., can solve the problem of not considering the dynamic robustness of high frequency and unmodeled, and achieve the reduction of overcoming flexible accessories Effects of vibration, excitation of vibration reduction, enhanced adaptability and robustness

Active Publication Date: 2018-03-16
NANJING UNIV OF SCI & TECH
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Problems solved by technology

Some scholars have proposed an attitude control strategy that applies the characteristic model adaptive control to the feedback linearization control, which considers the model characteristics of the strong coupling of high-speed spacecraft, but does not consider the robustness of high-frequency unmodeled dynamics

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  • Path planning based flexible spacecraft attitude adaptive control method
  • Path planning based flexible spacecraft attitude adaptive control method
  • Path planning based flexible spacecraft attitude adaptive control method

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Embodiment Construction

[0021] The solutions of the present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0022] The present invention first analyzes the flexible spacecraft dynamics model of the MIMO nonlinear strong coupling system, and provides the overall structure of its attitude control system; The maneuvering path planning method softens the command signal to reduce the high-frequency components in the command signal; then, using the MIMO feature modeling theory, an adaptive tracking control method based on the golden section is designed; finally, the input expected value is passed through SMPPa attitude planning The softened control signal is input to the designed golden section adaptive tracking control method to control the flexible spacecraft to complete the attitude control of the spacecraft; and the online identification of the gradient descent method is used for the parameter identification of the characteristic model ...

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Abstract

The invention relates to a path planning based flexible spacecraft attitude adaptive control method. First softening operation on an expected angle of a spacecraft is performed based on an SMPPa attitude maneuvering path planning method; on-line parameter identification is performed by utilizing a gradient descent method based on a flexible spacecraft mathematical model based on the feature modeltheory, and a three-axis model feature parameter is determined; a control moment is determined according to the determined flexible spacecraft mathematical model and the feature parameter thereof, theflexible spacecraft attitude is controlled through the control moment, and finally the steps are repeated until the angle reaches the expected spacecraft angle. According to the path planning based flexible spacecraft attitude adaptive control method, the influence of flexible accessory vibration on control performances is restrained, attitude control steady accuracy and dynamic characteristics are improved, and the path planning based flexible spacecraft attitude adaptive control method is suitable for the flexible spacecraft having three-axis coupling nonlinear characteristics.

Description

technical field [0001] The invention relates to a flexible spacecraft attitude control technology, in particular to an adaptive control method for a flexible spacecraft attitude based on path planning. Background technique [0002] With the rapid development and wide application of space technology, people's requirements for satellite data communication transmission capabilities have further increased. In order to meet this requirement, most modern satellites are equipped with a wide variety of flexible accessories such as large-area solar panels. At the same time, in order to adapt to the diverse requirements of space missions, modern spacecraft usually need to have the ability of fast attitude tracking or large-angle attitude maneuvering. However, for the flexible spacecraft, which is a multi-input, multi-output and uncertain nonlinear strong coupling system, the research mainly focuses on the dynamic modeling of the flexible spacecraft, the design of the controller and t...

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Application Information

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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 吴益飞芦梦兰高熠关妍陈庆伟郭健郭毓金立伟刘小壮周梦兰范成旺陈鑫
Owner NANJING UNIV OF SCI & TECH
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