Dong Zehong, Da Xingya, Li Yinghui, Li Zhe, Xie Like
China Aerodynamics Research and Development Center, High Speed Aerodynamics Institute, Mianyang, 621000, China.
Aviation Engineering School, Air Force Engineering University, Xi'an, 710038, China.
Sci Rep. 2024 Mar 4;14(1):1388. doi: 10.1038/s41598-023-50038-y.
Aircraft icing deteriorates aerodynamic performance and reduces stall angle of attack, the fast convergence rate of tracking error is required to stabilize the aircraft when aircraft icing occurs. The state-of-the-art control methods for icing aircraft mostly assume that the icing of aircraft is instantaneous. Aiming at these issues, a fixed-time angle of attack-constrained control strategy is designed considering dynamic icing process. In order to explore the variation of aerodynamic coefficients in the process of dynamic icing, an ice wind tunnel experiment is implemented, and the relationship between lift coefficient, drag coefficient and pitching moment coefficient with angle of attack and icing intensity is obtained by fitting method. In order to prevent the stalling problem caused by the decrease of the stalling angle of attack in the process of dynamic icing, a method to determine the stalling angle of attack based on deep neural network is proposed. Considering the asymmetric and time-varying angle of attack constraint, a fixed-time convergent angle of attack-constrained robust control method is designed. The ice wind tunnel experiment shows the process of dynamic icing of the airfoil, and the simulation results verify the effectiveness of the proposed control method.
飞机结冰会降低空气动力学性能并减小失速迎角，在飞机结冰时需要快速收敛的跟踪误差来稳定飞机。目前最先进的结冰飞机控制方法大多假设飞机结冰是瞬间完成的。针对这些问题，考虑动态结冰过程设计了一种固定时间的迎角约束控制策略。为了探究动态结冰过程中空气动力学系数的变化，进行了冰风洞实验，并通过拟合方法得到了升力系数、阻力系数和俯仰力矩系数与迎角和结冰强度之间的关系。为了防止动态结冰过程中因失速迎角减小而导致的失速问题，提出了一种基于深度神经网络确定失速迎角的方法。考虑到不对称且时变的迎角约束，设计了一种固定时间收敛的迎角约束鲁棒控制方法。冰风洞实验展示了翼型的动态结冰过程，仿真结果验证了所提控制方法的有效性。
