Design, flight dynamic analysis and hover control of a vertical take-off and landing micro air vehicle

Abstract

A ducted fan Vertical Takeoff and Landing (VTOL) Micro Air Vehicle (MAV) is developed. The vehicle is equipped with a wing that can be rotated in the pitch direction (variable incidence). This feature is expected to suppress the altitude loss during transition and to reduce the gust effect in hover. The selected I would also address my thankfulness to the member of the MAV development

Computational investigation on aerodynamic and stability characteristics of a vertical take-off and landing micro air vehicle

“…for the left are added to the VTOL MAV. The number of blade-layers and the setting angle of the stators are determined during the conceptual design phase [8]. Based on the empirical calculation conducted in the conceptual design phase, this configuration is expected to be able to generate sufficient rolling moment to counteract the propeller torque.…”

“…The winged-ducted propeller is the most suitable configuration to satisfy the Design Requirement and Objective (DRO). The VTOL MAV is capable of VTOL and hover, flying for medium duration and range, pack-able and easy to operate[8]. The ducted propeller configuration offers advantages such as high static thrust and high propulsive efficiency, able to generate additional lift from the duct and the wing, low noise and high safety level.…”