The research and development efforts outlined in this paper address the aerodynamic design of micro air vehicles that are capable of vertical takeoff and landing, as well as hovering. The effect of a propulsive slipstream on a wing's quasi-steady aerodynamics is investigated as an early step toward improving existing vertical takeoff and landing designs and control algorithms. Wind-tunnel testing was conducted on a propulsion system with contrarotating propellers, a wing, and the combined wing and propulsion system. Aerodynamic coefficient definitions are discussed with regard to vertical takeoff and landing micro air vehicles, and modified definitions are presented.

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This paper presents the simulation and validation of models for transition between forward flight and hover for a micro air vehicle (MAV). A dynamical simulation environment is developed, based on measured aerodynamic properties of a fixed-wing tail-sitter MAV with vertical take-off and landing (VTOL) capabilities. The simulator is validated against recorded flight data of transition from forward flight to hover using the physical platform. Specifically, the flight transition maneuver in the vertical plane (vertical-to-horizontal and horizontal-to-vertical) is studied in detail. The development and evaluation of a VTOL MAV called Mini-Vertigo 2 (MV2) is presented. A non-linear longitudinal dynamic model of MV2 flight is derived, and semi-empirical aerodynamic formulas for thrust, lift, drag and pitching moment based on wind tunnel testing are applied to the dynamic model. Nonlinearities during transition to/from hover are addressed, and (using the developed dynamic model) a numerical vehicle dynamic simulator is presented. The MV2 autopilot is discussed and flight test data are presented. Flight data from pitch-up maneuvers was compared to results of simulations. This comparison enables the future application of the simulation system throughout the flight envelope. This work presents a significant extension of [1].

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