Diagnosis of Aircraft Control Surface Fault Based on Semi-physical Simulation

Authors

Yunlong Li, 1. School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China; ;
Xia Jie, 1. School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China; ;2. Science and Technology on Aircraft Control Laboratory, Beihang University, Beijing 100191, China;
Zifang Shi, 1. School of Automation Science and Electrical Engineering, Beihang University, Beijing 100191, China; ;

Abstract

Abstract: The aircraft control surface defaults of rudders were mainly divided into jam fault and damage fault. On the basis of the relationship between motor toque and hinge moment, a new method of using the motor voltage was proposed to detect the control surface'faults of rudder. And the method could detect the damage degree of the faults. Torque motor was used to play the role of hinge moment. And the new method was simulated by Semi-Physical system which is consisted of dSPACE system, PC and simulated rudder actuator. The results show that, the damage faults and jam faults can be detected in 0.5s between 1.5s. And also it can detect the damage degree. According to the above, this method has good practical value.

Recommended Citation

Li, Yunlong; Jie, Xia; and Shi, Zifang (2020) "Diagnosis of Aircraft Control Surface Fault Based on Semi-physical Simulation," Journal of System Simulation: Vol. 27: Iss. 8, Article 38.
Available at: https://dc-china-simulation.researchcommons.org/journal/vol27/iss8/38

First Page

1914

Revised Date

2015-06-24

DOI Link

https://doi.org/

Last Page

1921

CLC

V267

Recommended Citation

Li Yunlong, Xia Jie, Shi Zifang. Diagnosis of Aircraft Control Surface Fault Based on Semi-physical Simulation[J]. Journal of System Simulation, 2015, 27(8): 1914-1921.