H∞ Parameter Identification and H2 Feedback Control Synthesizing for Inflight Aircraft Icing

doi:10.1007/s12204-013-1401-6

上海交通大学学报（英文版） ›› 2013, Vol. 18 ›› Issue (3): 317-325.doi: 10.1007/s12204-013-1401-6

H∞ Parameter Identification and H2 Feedback Control Synthesizing for Inflight Aircraft Icing

YING Si-bin1* (应思斌), GE Tong1 (葛彤), AI Jian-liang2 (艾剑良)

(1. School of Naval Architecture, Ocean and Civil Engineering, Shanghai Jiaotong University, Shanghai 200240, China; 2. Department of Mechanics & Engineering Science, Fudan University, Shanghai 200433, China)

出版日期:2013-06-28 发布日期:2013-08-12
通讯作者: YING Si-bin (应思斌) E-mail:yingsibin@163.com

H∞ Parameter Identification and H2 Feedback Control Synthesizing for Inflight Aircraft Icing

YING Si-bin1* (应思斌), GE Tong1 (葛彤), AI Jian-liang2 (艾剑良)

(1. School of Naval Architecture, Ocean and Civil Engineering, Shanghai Jiaotong University, Shanghai 200240, China; 2. Department of Mechanics & Engineering Science, Fudan University, Shanghai 200433, China)

Online:2013-06-28 Published:2013-08-12
Contact: YING Si-bin (应思斌) E-mail:yingsibin@163.com

摘要/Abstract

摘要： Aircraft icing accident happens frequently. Researchers try to find new ways to solve this problem. The study is facing the direction of intelligent inspection and control system. Previous studies focused on the principle of aircraft icing and its effects on flight performance. The onboard icing detection equipment can only give the qualitative icing information, but cannot effectively describe how serious the consequences would be. If the icing detection equipment fails, it will cause a serious threat to flight safety. This paper reviews the smart icing system and its fundamental principle. Then based on H∞ theory, an aircraft icing parameter identification method is introduced, and its feasibility is verified by simulation results. Moreover, this method can work normally under noise interference and measurement error. Icing parameter identification method can also test part of aircraft’s stability or control derivatives which would be changed obviously after aircraft icing. Classified by neural networks, the stability or control derivatives’ variation can be mapped to ice parameters’ variation that reflects the severity of aircraft icing. Then H2 state feedback control is designed originally to suppress the impact of noise interference, so aircraft can keep steady after it is iced. Seeing from simulation result of the whole system, it is clear that the system can effectively detect icing parameters and by using feedback control system, it can ensure the safety of aircraft in the flight envelope.

关键词: aircraft icing, parameter identification, H-infinity, feedback control

Abstract: Aircraft icing accident happens frequently. Researchers try to find new ways to solve this problem. The study is facing the direction of intelligent inspection and control system. Previous studies focused on the principle of aircraft icing and its effects on flight performance. The onboard icing detection equipment can only give the qualitative icing information, but cannot effectively describe how serious the consequences would be. If the icing detection equipment fails, it will cause a serious threat to flight safety. This paper reviews the smart icing system and its fundamental principle. Then based on H∞ theory, an aircraft icing parameter identification method is introduced, and its feasibility is verified by simulation results. Moreover, this method can work normally under noise interference and measurement error. Icing parameter identification method can also test part of aircraft’s stability or control derivatives which would be changed obviously after aircraft icing. Classified by neural networks, the stability or control derivatives’ variation can be mapped to ice parameters’ variation that reflects the severity of aircraft icing. Then H2 state feedback control is designed originally to suppress the impact of noise interference, so aircraft can keep steady after it is iced. Seeing from simulation result of the whole system, it is clear that the system can effectively detect icing parameters and by using feedback control system, it can ensure the safety of aircraft in the flight envelope.

Key words: aircraft icing, parameter identification, H-infinity, feedback control

中图分类号:

V 212.1

YING Si-bin1* (应思斌), GE Tong1 (葛彤), AI Jian-liang2 (艾剑良). H∞ Parameter Identification and H2 Feedback Control Synthesizing for Inflight Aircraft Icing[J]. 上海交通大学学报（英文版）, 2013, 18(3): 317-325.

YING Si-bin1* (应思斌), GE Tong1 (葛彤), AI Jian-liang2 (艾剑良). H∞ Parameter Identification and H2 Feedback Control Synthesizing for Inflight Aircraft Icing[J]. Journal of shanghai Jiaotong University (Science), 2013, 18(3): 317-325.

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H∞ Parameter Identification and H2 Feedback Control Synthesizing for Inflight Aircraft Icing

H∞ Parameter Identification and H2 Feedback Control Synthesizing for Inflight Aircraft Icing

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