Design Of Flapping Wing Micro Air Vehicle And Study On Testing Experiment

Flapping Wing Micro Air Vehicle(FWMAV)is a new concept aircraft that takes insects and birds as bionic research objects.Due to the advantages of small size,light-weight,high-visual concealment and low noise in flight,FWMAVs have vital important applications and bright prospect in military and civil areas.For the design of FWMAV,the drive mechanism and bionic wings have always been the research core and difficulties.Based on the above two aspects,this paper have been done these research as follows:At first,from the aspect of bionics,the basic motion parameters and patterns of MAVs were determined by the description of mechanisms of insects,flapping motions and flight patterns wing-tip trajectory and scale law principles,which provided the basic theory and guide principle for the design of FWMAVs.Then,the multiple flapping motion mechanism was the research object;a flapping model with composite mechanism of crank rocker and eccentric ball was established;motion principle,simulation optimization and aerodynamic calculation were also conducted.The result showed that: by using only one power source,the mechanism can realize the flapping and twist motion of wing;the wing-tip can form “8” figure motion trajectory.By calculating aerodynamic theory and analyzing the distribution of aerodynamic forces in the process of whole flapping motion,the validity of the designed model could be verified in theory.Next,based on the flapping mechanism,the design of aircraft was conducted.By the method of scale principle and aerodynamic theory calculation,the power source could be selected.Moreover,the generality of scale principle was verified.We focused on the design of flapping wing stiffness,analyzed the influence of width and thickness on the stiffness of wing veins by using three-dimension software evaluating and finite element modal analysis,provided an innovative access to design wings of different stiffness in theory;complete assembly of flapping wing aircraft and power testing and so on.At last,complete the construction of the wind tunnel system and the aerodynamic test.In the process of the construction of the wind tunnel system,the design of the force measuring device is the key part,by checking statics theory and experimental calibration,the force device was completed;In test,the vibration test of the frame structure proved the transmission stability of the flapping wing mechanism;A new design method is provided for the stiffness design of the bionic wing of aircraft through the aerodynamic test of the wings with different stiffness;Finally,by comparing the simple flapping mechanism,it is proved that the composite flapping mechanism has high aerodynamic performance.