Spacecraft rapid maneuvering attitude tracking adaptive robust control method

An adaptive robust and control method technology, applied in attitude control and other directions, can solve the problems of general effect, poor robustness, and few applications, and achieve the effect of solving contradictions and enhancing robustness

Pending Publication Date: 2020-06-26
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0003] Most of the traditional attitude tracking control is PID control or improved PID control, optimal control, variable structure control method, robust control, etc. The design of PID controller is simple but the effect is general; the optimal control can achieve the optimal

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  • Spacecraft rapid maneuvering attitude tracking adaptive robust control method
  • Spacecraft rapid maneuvering attitude tracking adaptive robust control method
  • Spacecraft rapid maneuvering attitude tracking adaptive robust control method

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Embodiment Construction

[0078] The invention can be used in a spacecraft attitude tracking control system. The invention mainly solves the problem of high-precision robust tracking control under the condition of given spacecraft fast maneuvering expected attitude path.

[0079] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0080] (1) Satellite attitude tracking attitude error and angular velocity error ω e ∈ R 3

[0081] consider figure 1 As shown in the satellite attitude tracking attitude error calculation, let ω∈R 3 , respectively represent the rotational angular velocity and attitude quaternion of the satellite system B relative to the inertial system I, ω d ∈ R 3 Denotes the desired angular velocity vector in the desired coordinate system, The attitude quaternion representing the desired coordinate system relative to the inertial coordinate system. q e , ω e Defined in the spacecraft body coordinate system.

[008...

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Abstract

The invention provides a spacecraft rapid maneuvering attitude tracking adaptive robust control method, which adopts a tracking differentiator to calculate the transition process of reference input and give the differential of the reference input, and solves the contradiction between the overshoot and rapidity of the system by arranging a proper reference signal transition process. The design of the controller is based on a cooperative control method, the problem of intrinsic discontinuity of sliding mode variable structure control is solved, the optimization of performance indexes is achieved, the cooperative control method combines the advantages of sliding mode control and optimal control, and meanwhile the buffeting phenomenon generated by discontinuity in sliding mode variable structure control is improved. Furthermore, based on self-adaptive control, the problem of spacecraft rotational inertia uncertainty and the problem of interference suppression are solved, and spacecraft rapid maneuvering attitude tracking self-adaptive robust high-precision control under the interference condition is achieved.

Description

technical field [0001] The invention relates to a fast maneuvering attitude tracking control method for a spacecraft, and belongs to the technical field of adaptive robust control of a nonlinear control system. Background technique [0002] At present, complex space missions require the spacecraft to have attitude maneuvering and attitude tracking capabilities to ensure that the attitude and command requirements can be achieved after a series of controls. Moreover, with the development of space missions, high-resolution remote sensing satellites have attracted the attention of various countries and fields around the world because of their extremely high spatial resolution in both full-spectrum and multi-spectral bands. With the continuous improvement of user requirements for high-resolution remote sensing satellites, while pursuing high spatial resolution, higher requirements are put forward for the satellite's rapid response capability, earth observation efficiency, and ima...

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Application Information

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IPC IPC(8): G05D1/08
CPCY02T90/00
Inventor 黄静孙俊黄庭轩谭龙玉张敏
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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