Aircraft electromechanical actuation system fault detection method based on extended state observer

A technology of electromechanical actuation and extended state, applied in test/monitoring control systems, general control systems, control/regulating systems, etc., to solve problems such as fault detection uncertainty

Active Publication Date: 2021-04-09
江苏航空职业技术学院
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Problems solved by technology

[0004] Aiming at the strong nonlinear factors and unknown input disturbances existing in the system, the uncertainty and complexity of fault detection, the technical problem to be solved by the pre...

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  • Aircraft electromechanical actuation system fault detection method based on extended state observer
  • Aircraft electromechanical actuation system fault detection method based on extended state observer
  • Aircraft electromechanical actuation system fault detection method based on extended state observer

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Embodiment Construction

[0056] The present invention will be specifically described below through exemplary embodiments. It is to be understood, however, that structures and features of one embodiment may be beneficially incorporated in other embodiments without further recitation.

[0057] The aircraft electromechanical actuation system fault detection method based on the extended state observer of the present invention comprises the following steps:

[0058] A. The establishment of the nonlinear model of the aircraft electromechanical actuation system: based on the actuation mechanism and structural characteristics of the aircraft electromechanical actuation system, the nonlinear factors of the system and the input unknown disturbance are transformed into a dynamic model of the system; specifically, considering the system There are two kinds of nonlinear interferences: friction and flux linkage change. In addition, considering the unknown interference of the system load input, based on the mechanis...

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Abstract

The invention discloses an aircraft electromechanical actuation system fault detection method based on an extended state observer. The method comprises the following steps: A, establishing a nonlinear model of the aircraft electromechanical actuation system: converting nonlinear factors and input unknown interference of the system into a dynamic model of the system based on actuation mechanics and structural characteristics of the aircraft electromechanical actuation system; and B, designing a fault detection method based on the threshold of the extended state observer: the extended state observer generating an estimated value of the composite interference to realize estimation of the composite interference and detection of a fault error so as to ensure the boundness of the interference observation error. The method has the advantages that estimation of composite disturbance including input disturbance and nonlinear factors can be generated, faults in the system can be effectively detected, the adopted fault detection method has high robustness for nonlinear influences and unknown interference of the system, the faults of the system can be accurately detected, and the false alarm rate is reduced in time.

Description

technical field [0001] The invention relates to a fault detection design of an aircraft electromechanical actuation system with strong nonlinearity and unknown interference, in particular to a fault detection method for an aircraft electromechanical actuation system based on an extended state observer. Background technique [0002] Aircraft electromechanical actuation system is a new type of actuation system that has gradually been widely used in civil aircraft with the development of multi-electric aircraft and the maturity of fly-by-wire flight control technology. The characteristic of maintenance is one of the typical characteristics and development direction of the application of power transmission to new civil airliners. The aircraft electromechanical actuation system has been used as the key technology of the new actuation system, and it has been applied to the trimming and actuation of the horizontal stabilizer of Boeing 787. The spoiler actuation of A380 has a great ...

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Application Information

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IPC IPC(8): G05B23/02
CPCG05B23/0262G05B2219/24065
Inventor 杨珍书沈宝国毛奇杨文杰
Owner 江苏航空职业技术学院
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