Abstract
Aircraft icing can result in degradation of the aerodynamic characteristics and reduction of the control effectiveness, which would pose serious threats to flight safety. Reconfigurable flight control and envelope protection of iced aircraft have become an effective solution to ensure flight safety in icing encounters. In this study, the dynamic model of the iced aircraft was established, and high precision numerical simulation method and wind tunnel virtual flight experiment were applied to obtain the icing aerodynamic database. Furthermore, the reconfigurable flight control law was designed by using the adaptive neural networks based dynamic inversion (ANN-DI) control method. Simulation results demonstrate that the control method behaves well tracking performance and strong robustness in the presence of modeling errors and control surface damage. After that, an icing envelope protection system was designed based on control limiting strategy and the ANN-DI control was applied to calculate the control surface deflection limits based on the limit values of the key flight safety parameters. Finally, the designed icing envelope protection system has been verified through simulation in two autopilot modes under icing conditions. The simulation results obtained here show that the system could keep the key flight safety parameters such as the flight speed, the angle of attack (AOA), the side slip angle, and bank angle within the flight safe region under icing conditions. The method proposed in this study is expected to provide flight safety measures for in-flight icing.
Highlights
Aircraft icing has been shown to be one of the most common external environmental causal factors that affect flight safety and even lead to catastrophic accidents [1]
In order to ensure good handling and stability characteristics when encountering icing during flight, and protect the aircraft states within the changing safe envelope, we developed the adaptive neural networks based dynamic inversion (ANN-dynamic inversion (DI)) method applied to reconfigurable flight control and envelope protection under icing conditions
APPLICATION TO RECONFIGURABLE FLIGHT CONTROL Based on ANN-DI control method mentioned above, the reconfigurable flight controller has been designed to compensate the undesirable effects of control surface failures and other adverse effects of damage conditions and we will discuss the results in the following content details
Summary
Aircraft icing has been shown to be one of the most common external environmental causal factors that affect flight safety and even lead to catastrophic accidents [1]. In order to ensure good handling and stability characteristics when encountering icing during flight, and protect the aircraft states within the changing safe envelope, we developed the ANN-DI method applied to reconfigurable flight control and envelope protection under icing conditions. Numerical simulation and wind tunnel based virtual flight test method are used to obtain the aerodynamic parameters of aircraft caused by ice accretion. Through the wind tunnel virtual flight test verification, we can obtain a set of reliable icing aerodynamic effect database and flight envelope limits of some key parameters like AOA. The control goal is to make the state variables x track the given desired trajectory xc
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