Design and analysis of spatial inclined crank rocker based flutter wing configuration

In order to improve the kinematic symmetry of the kinematic branch chains on both sides of the flutter structure and then enhance the stability of the fluttering flight of the flutter vehicle, a spatial diagonal crank rocker flutter structure is designed in this paper. Firstly, the kinematic model of the space inclined crank rocker mechanism was established by the kinematic analysis, and then the kinematic analysis of the model was carried out. The simulation model of the flutter mechanism was established in the multi-body dynamics software ADAMS to verify the theoretical analysis. The results show that the upper limit angle of the designed flutter mechanism is 29.99°and the lower limit angle is -29.99°, which are consistent with the flight parameters of the selected bird, so it has good aerodynamic performance. Moreover, the kinematic parameters obtained from the simulation are consistent with the theoretical calculation, which verifies the correctness of the theoretical calculation.