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.
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
.
DOI: 10.1007/s12204-013-1401-6
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