Dynamic-actuator aircraft attitude distributed type fault-tolerant control system

Abstract

The invention discloses a dynamic-actuator aircraft attitude distributed type fault-tolerant control system. The system comprises an actuator fault detection and identification unit, an auxiliary system based on an observer and an inversion fault-tolerant control algorithm based on order filtering. According to the distributed type fault-tolerant control system, the actuator fault detection and identification unit is used for obtaining fault information of actuators in real time, the self-adaptive sliding-mode observer is obtained according to an attitude angular speed ring, the observer has strong robustness, an undetermined or interference upper bound does not need to be known, and control surface damage fault information an interference information are both hidden in the observer; a fault-tolerant controller is obtained based on an observer model. Robustness fault-tolerant control over various faults of different types under the multi-fault condition is achieved, the fault-tolerant control system is applied to near-space vehicle attitude stable control and tracking control under the condition of faults of the actuators and the control surface, flying attitude robustness fault-tolerant control is achieved, and good control performance and effect are achieved.

Description

technical field [0001] The invention belongs to the technical field of near-Earth aircraft, and in particular relates to a distributed fault-tolerant control system for the dynamic actuator attitude of the aircraft. Background technique [0002] As a new aerospace vehicle, the failures of near-space vehicles (NSVs) are mainly caused by failures of actuators, control surfaces, sensors and structures. In order to improve the safety and reliability of NSV, NSV has reasonably divided the traditional aileron, rudder and elevator in the aerodynamic layout design, which can greatly improve the reliability and safety of the system, and also make the attitude control system become an overdrive system. [0003] Fault detection and identification (FDI) technology based on state or parameter estimation is the most commonly used method for fault-tolerant control of flight control systems. It is a model-based method. At present, various mainstream FDI methods include observer method and ...

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Problems solved by technology

[0006] The purpose of the embodiments of the present invention is to provide a dynamic aircraft attitude decentralized fault-tolerant control system for actuators, which aims to solve the problem that the existing fault detection and identification technology does not consider the dynamics of actuators, which will cause problems on the Hard-In-Loop Problems that cause errors in the estimation of faults or parameters

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