Evaluation of flapping wing propulsion based on a new experimentally validated aeroelastic model

To evaluate the propulsion system capabilities of a flapping micro air vehicle (fmav), a newaeroelastic model of a typical flexible fmav is developed, utilizing the eulerbernoulli torsion beamand quasi steady aerodynamic model. the new model accounts for all existing complex interactionsbetween the mass, inertia, elastic properties, aerodynamic loading, flapping amplitude and frequency ofthe fmav, as well as the effects of several geometric and design parameters. to validate the proposedtheoretical model, a typical fmav, as well as an instrumented test stand for the online measurementof forces, flapping angle and power consumption, has been constructed. the experimental results areinitially utilized to validate the flight dynamic model, and several appropriate conclusions are drawn.the model is subsequently used to demonstrate the flapping propulsion characteristics of the fmav viasimulation. using dimensionless parameters, a set of new aeroelastic coordinates are introduced. in thisreduced design space, new generalized performance curves have been deduced. the results indicate thatby proper adjustment of the wing stiffness parameter, as a function of reduced frequency, the fmav willattain its optimum propulsive efficiency. this fact raises additional ideas of utilizing intelligent variablestiffness materials and/or an active morphing technology for the sustained flight of fmavs.