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Self-adaptive compensation control method for continuous intermittent faults of actuator in non-minimum phase air vehicle control system

A non-minimum phase, self-adaptive compensation technology, applied in the direction of self-adaptive control, general control system, control/regulation system, etc., can solve problems such as sudden change, irrespective of system dynamic structural characteristics, difficult to effectively compensate, etc.

Active Publication Date: 2019-05-28
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

In addition, the existing actuator fault compensation technology often does not consider the sudden change of the dynamic structural characteristics of the system caused by the actuator fault.
This makes it difficult for existing methods to effectively compensate for the impact of continuous and intermittent actuator failures on the aircraft control system

Method used

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  • Self-adaptive compensation control method for continuous intermittent faults of actuator in non-minimum phase air vehicle control system
  • Self-adaptive compensation control method for continuous intermittent faults of actuator in non-minimum phase air vehicle control system
  • Self-adaptive compensation control method for continuous intermittent faults of actuator in non-minimum phase air vehicle control system

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Embodiment Construction

[0101] A kind of non-minimum phase aircraft control system actuator adaptive compensation control method of continuous intermittent failure of the present invention is suitable for solving the following problems: The actuator faults are all unknown, that is: which actuator fails is unknown, and the time, number and size of the actuator faults are also unknown; 2) Uncertain actuator faults may cause Uncertain phase variation occurs in the structural characteristics of the aircraft control system, that is, the minimum phase and non-minimum phase characteristics of the system will change with the change of the actuator failure mode; 3) The uncertain actuator failure will continue intermittently occurs and the actuator fault signal does not match the control input signal. The actuator faults include faults generated by actuators such as elevators, rudders, and ailerons. The aircraft control system can be considered as a time-varying system when the actuators of the aircraft contr...

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Abstract

The invention discloses a self-adaptive compensation control method for continuous intermittent faults of an actuator in a non-minimum phase air vehicle control system. The method includes the following steps that 1, based on an existing aircraft control system model, an aircraft control system model is reconstructed equivalently when the actuator has the continuous intermittent faults; 2, based on a time-varying input-output model, a parameterized aircraft control system model is constructed; 3, an LQ optimal control framework based on control separation is established; 4, a state space modelof a virtual parametric error control system is constructed; 5. a nominal LQ optimal controller is established; 6, a robust self-adaptive parameter updating law is designed and an error control system based on parameter estimation is established; 7, a robust self-adaptive LQ controller based on control separation is designed. When the actuator has the continuous intermittent faults, the flight control system effectively ensure the desired closed-loop stability and output tracking performance to achieve the safe flight of an aircraft.

Description

technical field [0001] The invention belongs to the technical field of aircraft automatic control, especially for a kind of aircraft control system with non-minimum phase characteristics, adopts LQ control technology and self-adaptive control technology based on control separation, and relates to a non-minimum phase aircraft control system actuator continuous Adaptive Compensation Control Method for Intermittent Faults. Background technique [0002] With the development and progress of aerospace technology, new types of aerospace vehicles have emerged one after another. Due to the structural characteristics of the new aerospace vehicle itself and its complex working environment, the dynamic model of its system has the characteristics of multi-variable, strong coupling, fast time-varying, and strong nonlinearity. Especially when the system components fail, the system will have a large parameter or structure uncertainty, which will cause a sudden change in the dynamic structu...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 文利燕陶钢姜斌杨少华董敏叶慧
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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