The Design And Experiment Of Micro Flapping Wing Rotor

Because of its high maneuverability and excellent concealment,micro aerial vehicle(MAV)has irreplaceable advantages in the field of personnel search and rescue and intelligence investigation.Nowadays,MAV has become a hot spot in the field of aircraft design.Micro-flapping wing rotor is a special micro air vehicle,whose vertical takeoff or hovering can be achieved by the motion of the wing,which is a combination of wing flutter and wing rotation.The study of micro-flapping wing rotor is a promising directions for developing high efficiency and high maneuverability MAVThis paper designs a linear motor drive mechanism for flapping wing rotorcraft,which takes the advantages of flapping wing rotorcraft for high efficiency and high lift,in combination with the simplicity of the linear drive mechanism and the high mechanical efficiency.In view of the fact that the traditional flat wing has a poor lift performance,two new airfoils are designed and tested.The main work of the paper is as follow:1.The development of MAV are studied.The driving technology of flapping wing vehicle and linear drive technology are mainly studied.Meanwhile,the development status of micro flapping wing rotor aircraft is investigated.2.The driving schemes of MAV are summarized in this section.A drive mechanism which uses linear motor as power output is designed.The dynamic model of the linear motor drive mechanism is established and the simulation of virtual prototype is carried out.The comparison of simulation results and physical test data shows that: the output of the linear motor drive mechanism meet the design requirements.3.The flight mechanism and high lift mechanism of insects and birds are analyzed.According to the scale ratio formula of bionics,a traditional flat wing is preliminary designed.In order to minimize the difference between the first order bending frequency and the first order torsional frequency of the flat wing,the structural optimization design of the flat wings is carried out.Based on the investigation of the new wings,two new types of flapping wing structures,elastic-hinge-wing and bow wing,are proposed.4.The prototype of flat wing,elastic-hinge-wing,bow wing and linear motor drive mechanism are fabricated.The lift test system which can synchronous record the motion picture of flapping wing rotorcraft is built.Lift tests were carried out on three kinds of wings by using the test system.Aerodynamic and inertial force tests were carried out on the flapping wing rotor with flat wings and elastic-hinge-wing respectively.The aerodynamic forces of two airfoils are calculated by the panel method,and the error between the theoretical and experimental results is not more than 10%.The results show that the elastic-hinge-wing has high lift characteristics at low frequency,and it is more suitable for low speed flight of microflapping wing rotor in complex environment.