本研究探索一种通过变翼型实现扑旋翼-扑翼飞行模式转换和逆转换、从而兼具垂直起降、悬停和高效巡航飞行性能的仿生MAV。开展形状记忆合金驱动的可变翼型扑旋翼研究，在满足扑旋翼-扑翼飞行模式转换要求的变翼型和结构动态耦合特性等约束条件下优化超轻型扑旋翼构型和结构；分析变翼型扑旋翼的气动伺服弹性耦合特性，揭示变翼型改变扑旋翼自推进旋转速度对扑旋翼-扑翼飞行模式转换的增效机理；建立仿生MAV的刚-弹多体模态耦合及多场流固耦合飞行动力学模型，分析飞行模式转换过程中的飞行速度、姿态、变翼型及尾翼偏转过程对飞行稳定性的影响，确定可实现MAV稳定飞行模式转换和逆转换的必要飞行条件以及变翼型和尾翼偏角变化的最优过程方案。研究将为新概念高飞行性能仿生MAV的探索及可操控实用型MAV的研发奠定基础。

This research project is aimed at developing a novel bionic micro aerial vehicle (MAV) capable of vertical take-off and landing and hovering（VTOLH）in flapping wing rotor (FWR) mode and high efficiency forward flight in flapping wing (FW) mode through FWR-FW mode transition. The research will take theoretical study, numerical simulation and experimental approach and start from developing a morphing wing of large deformation actuated using shape memory alloys (SMA) to achieve exchange of the airfoil leading edge with trailing edge. The relationship will be established between the SMA characteristic parameters and dynamic behavior of the morphing FWR. Under multi constraints including specified wing airfoil shape and structural dynamic characteristics of the morphing wing, an ultra-light FWR of minimum weight will be optimized. Based on the FWR analysis with aeroservoelastic coupling effect, the study will reveal the mechanism of FWR self-propelling rotation speed change and FWR-FW mode transition enhancement by the wing morphing. Subsequently a flight dynamic model will be created for MAV with strong multi-physics fluid-elastic body coupling effect and validated by experiment. Taking a MAV model as example, the influence of the flight speed, attitude, FWR morphing scheme and multi-physics coupling effect on the flight stability during the FWR-FW flight mode transition will be analyzed. The study will lead to evaluation of the necessary flight condition, morphing wing and tail-plane actuation optimal scheme to realize a stable FWR-FW flight mode transition and reversed transition. The research will pave a theoretical base to develop a controllable high performance bionic MAV. It will also add scientific value to the new research field and provide an alternative route to solve the key problem for flight mode transition between rotor and fixed wing aircraft.