Abstract
FWMAVs (Flapping Wing Micro Air Vehicles) turn to be a flexible multibody system when the inertia and flexibility of flapping wing are considered. The flight dynamic stability considering the oscillation of body in forward flight are still an open question. In this study, based on a method coupled CFD (Computational fluid dynamics), CSD (Computational structural dynamics) and equations of longitudinal motion for FWMAVs, the periodic derivatives of forces and moment during whole flapping course can be computed. The dynamic stability is analysed by Floquet method specially for the cyclic-motion equilibrium. Results show that the FWMAV in forward flight is stable and character of eigenvalue is similar to that of fixed-wing vehicles. However, the effect of pitch rate damping is different from its role played for the fixed wing vehicle. As the pitch rate damping increases, the system turns to be unstable. These results can inform designs of FWMAV from the perspective of dynamic stability.
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