ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Nonlinear stability region of icing aircraft during landing phase based on normal form method
Received date: 2016-08-25
Revised date: 2016-10-25
Online published: 2016-11-03
Supported by
National Natural Science Foundation of China (61374145); National Basic Research Program of China (2015CB755805)
Icing can cause flight envelope shrink and thus poses a great threat to flight safety; therefore, research on nonlinear stability region of an aircraft after icing is significantly important for the design of flight envelope protection system and the improvement flight safety. A transport is taken as an object of this study. Taking the nonlinear aerodynamic characteristics into account, the longitudinal nonlinear dynamic model with stability augmentation control is obtained. Based on the theory of manifold and normal form, the longitudinal nonlinear stability boundary and its analytic expression are obtained. Via dynamic simulation, the stability boundary based on normal form is justified to be feasible and accurate. Finally, icing factor impacting on aircraft stability region and the mechanism for accidents of an icing aircraft is studied at the landing phase. Results show that mild icing condition can cause the shrink of nonlinear stability region, while severe icing condition can change the aircraft stability. When icing of an aircraft is not detected, regular manipulation can result in flight accident as the aircraft state can be out of the icing nonlinear stability region. The results can provide some reference for flight envelope protection under icing condition.
Key words： aircraft icing; stability region; nonlinear; normal form theory; transport aircraft
ZHENG Wuji , LI Yinghui , QU Liang , XU Haojun , YUAN Guoqiang . Nonlinear stability region of icing aircraft during landing phase based on normal form method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(2) : 520714 -520724 . DOI: 10.7527/S1000-6893.2016.0279
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