Flight control system executor deadlock trouble real-time detection method

A flight control system, real-time detection technology, applied in the direction of electrical testing/monitoring, etc., can solve problems such as failure to propose, actuator stuck, etc., and achieve the effect of reducing energy consumption, simplifying hardware structure, and reducing space requirements

Inactive Publication Date: 2008-08-13
DALIAN MARITIME UNIVERSITY
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Problems solved by technology

In the document "Y. Zhang and J. Jiang, Active fault-tolerant control system against partial actuator failures, IEE Proceedings-Control Theory Applications, Vol.149, No, 1, January 2002, pp.95-104", the author proposed A method can handle partial failure faults in a continuous parameter manner, but no effective method has been proposed for the stuck actuator case

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  • Flight control system executor deadlock trouble real-time detection method
  • Flight control system executor deadlock trouble real-time detection method
  • Flight control system executor deadlock trouble real-time detection method

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Embodiment Construction

[0024] The present invention is described in further detail below in conjunction with accompanying drawing:

[0025] The invention provides a detection method for actuator stuck fault based on a multi-model observer, and Fig. 1 shows the structure of the fault detection system. A set of observers is designed to generate the residual signal, and the design of each observer is based on the model of the system under a specific fault; the fault diagnosis is made by determining the best model of the current system, that is, the method is in p Find the model that best matches the current system among the models. For this purpose, the ideal goal of the observer design is to produce a residual signal vector r i (t), i=1,...,p, satisfy the following conditions: when the i-th model matches the current system fault, r i (t)=0, while for all j≠i, r j (t)≠0. In order to eliminate the influence of external disturbances on the residual signal, this paper adopts the UIO (UnknownInput Obse...

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Abstract

A real-time detection method for executor blocking fault in a flight control system pertains to flight control system field. The invented method uses a multi-model structure to build a set of observers UIOs each of which is based on a system model for describing a specific executor fault, UIOs are used for generating residual error signals depending on faults, UIO of a model matching with the system generates a residual error signal close to zero, and each UIO of a model mismatching with the system generates a big residual error signal driven by the mismatch signal. Aiming at unknown model parameter caused by that the executor blocking position can not be predicted, fault detection is implemented by using a model with a model of an uncertain parameter to online approach the executor blocking parameter by self-adaptation adjustment, to make the UIO model to match with the system status.

Description

technical field [0001] The invention relates to the technical field of flight control systems, in particular to a real-time detection method for actuator stuck faults in the flight control system. Background technique [0002] The reliable operation of the flight control system is the premise of the flight safety of the aircraft. In order to make the flight control system have fault tolerance in case of failure, modern aircraft usually adopt hardware redundancy, that is, multiple sets of hardware devices such as controllers, sensors and actuators are repeated in parallel. The disadvantage of hardware redundancy is Due to space and load limitations on small aircraft, especially unmanned aerial vehicles, it is necessary and promising to use fault diagnosis technology based on analytical analysis or artificial intelligence methods. When the flight control system adopts fault-tolerant control technology, the rapid detection and accurate location of faults provide a good foundat...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
Inventor 王丹胡晓静黄加亮李小强牛小兵
Owner DALIAN MARITIME UNIVERSITY
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