Design and Research of Flapping-Wing Aircraft Based on Linear Module Actuator

In order to improve the stability of the flapping wing aircraft, this paper designs a connecting rod driving mechanism for it based on linear module actuator, and the reciprocating motion of the module drives the symmetrical flapping of both wings through the linkage. Firstly, the kinematic model of the driving mechanism is established, following this the kinematic analysis of the driving mechanism is carried out, and then the fluttering mechanism is simulated and verified by using ADAMS-View, which theoretically determines the rationality of the mechanism. The findings indicate that the driving mechanism's upper flutter angle measures 22.37 degrees, while the lower flutter angle measures -16.69 degrees. The ADAMS simulation results align with the theoretical calculation results, thereby confirming the accuracy of the theoretical study.