折叠机翼变体飞机非对称变形控制效率分析

折叠机翼变体飞机变形量大,变形引起的气动参数变化显著,提出一种将非对称变形作为操纵输入的控制方案,研究非对称变形的控制效率和有效区间。首先建立能够完整描述变形过程的非线性动力学方程和气动力模型;然后基于非对称变形控制方法建立一种非对称变形操纵模型;最后通过与常规操纵面效率对比和仿真的动态响应总结出非对称变形操纵的最大变形操纵有效区间。结果表明:在较低飞行速度下非对称变形操纵效率高,非对称变形操纵能够在基准折叠角度90°附近提供最高的滚转操纵效率。

The Control Efficiency Analysis of Asymmetry Transmutation forFolding Wing Morphing Aircraft

Folding wing morphing aircraft can alter their shape largely which causes the aerodynamic parameters change significantly. So the aerodynamic effects caused by the asymmetric morphing can be used for aircraft maneuver control as an assist to the conventional control, which can enhance maneuvering flight ability. The purpose of this paper is studying the asymmetric morphing control efficiency of a folding wing morphing aircraft. Firstly, the nonlinear dynamic equations and aerodynamic model that can depict the full morphing process are derived. Then, an asymmetric morphing control model is proposed based on the asymmetric morphing control method. Finally, by comparing with the efficiency of conventional control and the dynamic response of simulation, we find the maximum effective interval of the asymmetric morphing control. The results show that the efficiency of asymmetric morphing control is higher at lower flight speeds, and the asymmetric morphing control can provide the highest roll handling efficiency near the reference folding angle of 90°.