Journal of Bionic Engineering ›› 2021, Vol. 18 ›› Issue (3): 649-661.doi: 10.1007/s42235-021-0043-x
Liftoff of a New Hovering Oscillating-wing Micro Aerial Vehicle
Xiangcong Zhou1, Deyuan Zhang1,2, Zhiyong Huang1, Xiaogang Song1, Hao Liu2,3,4, Lin Feng1,2*
- 1. Institute of Bionic and Micro-Nano Systems, School of Mechanical Engineering and Automation,
Beihang University, Beijing 100191, China
2. Beijing Advanced Innovation Center for Biomedical Engineering, Beihang University, Beijing 100191, China
3. Graduate School of Engineering, Chiba University, Chiba 263-8522, Japan
4. Shanghai Jiao Tong University and Chiba University International Cooperative Research Center, Shanghai 200240, China
Liftoff of a New Hovering Oscillating-wing Micro Aerial Vehicle
Xiangcong Zhou1, Deyuan Zhang1,2, Zhiyong Huang1, Xiaogang Song1, Hao Liu2,3,4, Lin Feng1,2*
- 1. Institute of Bionic and Micro-Nano Systems, School of Mechanical Engineering and Automation,
Beihang University, Beijing 100191, China
2. Beijing Advanced Innovation Center for Biomedical Engineering, Beihang University, Beijing 100191, China
3. Graduate School of Engineering, Chiba University, Chiba 263-8522, Japan
4. Shanghai Jiao Tong University and Chiba University International Cooperative Research Center, Shanghai 200240, China
摘要： Hovering ability forms the basis for space operations of Micro Aerial Vehicles (MAVs). The problem of uneven load puts high demands on the wing design. In this paper, a new hovering-mode for MAVs, inspired by flapping flight in bees and hummingbirds but using high-aspect-ratio and low-stress wings, is proposed. Different from the flapping actuations that occur at the wing roots, the two wings are driven back and forth in a straight line. To simplify the design and control the angle of attack, passive wing rotation is employed. The numerical results and analysis show that the maximum stress of the oscillating wing is approximately 1/6 of that of the flapping wing when the lift of the oscillating wing is twice that of the flapping wing. A theoretical aerodynamic model of the kinematics of the vehicle’s driving mechanism was developed to fulfill its design. Force measurements indicate that the vehicle generates a sufficiently high cycle-averaged vertical thrust (71 g) for liftoff at a maximum frequency of 5.56 Hz, thereby validating the proposed aerodynamic model. Moreover, liftoff performance is presented to visually demonstrate the vertical take-off capabilities and hovering potential of the aeromechanical solution.