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Finite-time adaptive fault-tolerant control method for rigid spacecraft based on enhanced bipower reaching law and fast terminal sliding mode surface

A sliding mode technology for aerospace vehicles and terminals, applied in adaptive control, attitude control, general control systems, etc.

Active Publication Date: 2018-09-04
ZHEJIANG UNIV OF TECH
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Problems solved by technology

[0005] In order to solve the nonlinear problems in the existing attitude kinematics and dynamics of the aircraft and realize the external disturbance suppression control, and reduce the chattering problem existing in the sliding mode control, the present invention provides a method based on the enhanced double power reaching law A finite-time adaptive fault-tolerant control method for rigid aerospace vehicles with fast terminal sliding surface, and a finite-time uniformly ultimately bounded control method for the system in the presence of uncertainties and disturbances

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  • Finite-time adaptive fault-tolerant control method for rigid spacecraft based on enhanced bipower reaching law and fast terminal sliding mode surface
  • Finite-time adaptive fault-tolerant control method for rigid spacecraft based on enhanced bipower reaching law and fast terminal sliding mode surface
  • Finite-time adaptive fault-tolerant control method for rigid spacecraft based on enhanced bipower reaching law and fast terminal sliding mode surface

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Embodiment Construction

[0078] The present invention will be further described below in conjunction with the accompanying drawings.

[0079] refer to Figure 1 to Figure 6 , a finite-time adaptive fault-tolerant control method for rigid aerospace vehicles based on enhanced double-power reaching law and fast terminal sliding surface, including the following steps:

[0080] Step 1, establish the kinematics and dynamics model of the aircraft attitude fault-tolerant control system, initialize the system state and control parameters, the process is as follows:

[0081] 1.1 The expression form of the dynamic model of the aircraft attitude control system is:

[0082]

[0083] in, are the angular velocity and angular acceleration of the aircraft; Ω∈R n is the angular velocity of the reaction flywheel; × is the operation symbol, the operation symbol × applied to a=[a 1 ,a 2 ,a 3 ] T got a × =[0,-a 3 ,a 2 ;a 3 ,0,-a 1 ;-a 2 ,a 1 ,0]; J∈R 3×3 is the rotational inertia matrix of the aircraft...

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Abstract

The invention relates to a finite-time adaptive fault-tolerant control method for a rigid spacecraft based on an enhanced bipower reaching law and a fast terminal sliding mode surface. In order to solve a problem of low attitude stability under the fault of an aircraft actuator with centralization uncertainty, the invention designs an adaptive fast terminal sliding-mode composite control scheme bycombining adaptive control based on a sliding mode control method with the enhanced bipower reaching law. On the one hand, an uncertain and disturbed upper bound is estimated and compensated by usingthe adaptive technique; and on the other hand, on the basis of the quickness and high robustness of the fast terminal sliding mode, finite-time attitude stability of the aircraft system is realized.With the control method, buffeting of the sliding surface and control torque is reduced; and a finite-time boundary control method of the system is realized under the conditions of uncertainty and interference existence in the system.

Description

technical field [0001] The invention relates to a finite-time self-adaptive fault-tolerant control method for a rigid aerospace vehicle based on an enhanced double-power reaching law and a fast terminal sliding surface, especially under the condition of an aircraft actuator fault with external disturbance and uncertainty of the rotational inertia matrix attitude control method. Background technique [0002] The attitude control system is one of the important subsystems of the spacecraft. Its reliability and normal operation will directly determine whether the spacecraft can normally complete the scheduled space mission. However, factors such as the harsh space environment and the aging of components lead to the inevitable failure of spacecraft components. If the failure of the spacecraft cannot be detected, located, isolated and handled accordingly in a timely and correct manner, the attitude control performance will be significantly reduced or the system stability will be ...

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Application Information

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IPC IPC(8): G05B13/04G05D1/08
CPCG05B13/042G05D1/0825
Inventor 陈强陶玫玲何熊熊
Owner ZHEJIANG UNIV OF TECH
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