A fault-tolerant control method for distributed flight control system facing wing damage

doi:10.23919/JSEE.2021.000089

Journal of Systems Engineering and Electronics ›› 2021, Vol. 32 ›› Issue (5): 1041-1052.doi: 10.23919/JSEE.2021.000089

• New Developments on FDD and FTC Techniques • Previous Articles Next Articles

A fault-tolerant control method for distributed flight control system facing wing damage

Yuwei CUI^1,^2,*(), Aijun LI¹(), Xianfeng MENG²()

¹ School of Automation, Northwestern Polytechnical University, Xi’an 710072, China
² Aviation Industry Corporation of China Xi’an Flight Automatic Control Research Institute, Xi’an 710065, China

Received:2020-12-28 Online:2021-10-18 Published:2021-11-04
Contact: Yuwei CUI E-mail:cuiyuwei0505@mail.nwpu.edu.cn;liaijun@nwpu.edu.cn;xfmeng@facri.com
About author:|CUI Yuwei was born in 1986. He received his B.S. and M.S. degrees in control theory and control engineering from Northwestern Polytechnical University in 2009 and 2012, respectively. He is currently pursuing his Ph.D. degree at Northwestern Polytechnical University. His research interests include aircraft flight control system, fault diagnosis, and fault-tolerant control. E-mail: cuiyuwei0505@mail.nwpu.edu.cn||LI Aijun was born in 1973. He received his B.S., M.S., and Ph.D. degrees in aircraft design from Northwestern Polytechnical University in 1995, 2000, and 2005, respectively. Currently he is a professor and doctoral supervisor at Northwestern Polytechnical University. His research interests include aircraft flight control and intelligent control. E-mail: liaijun@nwpu.edu.cn||MENG Xianfeng was born in 1990. He received his B.S. and M.S. degrees in guidance, navigation, and control from Nanjing University of Aeronautics and Astronautics in 2012 and 2016, respectively. He is currently with Xi’an Flight Automatic Control Research Institute, Aviation Industry Corporation of China. His research interests include modeling of control systems and fault diagnosis. E-mail: xfmeng@facri.com
Supported by:
This work was supported by the Defense Industrial Technology Development Program (JCKY2016205C013)

Abstract

Abstract:

With the strong battlefield application environment of the next generation fighter, based on the design of distributed vehicle management system, a fault diagnosis and fault-tolerant control (FTC) method for wing surface damage is proposed in this paper. Aiming at three kinds of wing damage modes, this paper proposes a diagnosis method based on the fault decision tree and forms a fault decision tree for wing damage from the aspects of sample database construction, feature parameter extraction, and fault decision tree construction. Based on the fault diagnosis results, the longitudinal control law based on dynamic inverse and the lateral-directional robust control laws based on linear quadratic regulator (LQR) are proposed. From the simulation examples, the fault diagnosis algorithm based on the decision tree can complete the judgment of three wing surface damage modes within 2 ms, and the FTC law can make the fighter quickly return to a stable flight state after a short transient of 1 s, which achieves the fault-tolerant goal.

Key words: flight control, fault diagnosis, distributed system, dynamic inverse, linear quadratic regulator (LQR)

Yuwei CUI, Aijun LI, Xianfeng MENG. A fault-tolerant control method for distributed flight control system facing wing damage[J]. Journal of Systems Engineering and Electronics, 2021, 32(5): 1041-1052.

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References 21

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Main parameter	Value
Length/mm	2426
Wingspan/mm	2 000
Wing area/m²	0.72
Weight/kg	21
Maximum thrust/kg	20

Configuration number	Detailed parameter
No.1	No damage
No.2	50% right wing damage
No.3	50% vertical tail damage
No.4	95% vertical tail damage

Condition point	Height/km	Velocity/km·h^?1
No.1	0.40	90.0
No.2	0.40	100.8
No.3	0.40	115.2
No.4	0.50	100.8
No.5	0.50	115.2
No.6	0.50	126.0
No.7	0.50	144.0
No.8	0.50	162.0

Roll angle command/(°)	Height command/m
Roll angle command/(°)	0	5	30
0	Sample 1	Sample 2	Sample 3
5	Sample 4	Sample 5	Sample 6
10	Sample 7	Sample 8	Sample 9
30	Sample 10	Sample 11	Sample 12

Control law parameter	Parameter value
Ke_theta	0.0130
Ke_thetac	?0.0868
Ke_wz	0.0347
Ke_v	0.0120
Ke_alf	?4.2259
Ke_vc	3.3852

A fault-tolerant control method for distributed flight control system facing wing damage

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References 21

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Control law parameter	Parameter value
Ka_beta	0.5111
Ka_wx	?0.2587
Ka_wy	?0.0791
Ka_bank	?0.3208
Kr_beta	0.0390
Kr_wx	0.0654
Kr_wy	?0.2319
Kr_bank	0.0764

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