Abstract
Control characteristics of a buoyant quad-rotor research aircraft are predicted by considering such a vehicle configuration based on preliminary design. Concepts for controlling the vehicle with or without its external sling load are evaluated by using a flight dynamics simulation of the aircraft. Results are presented which show the vehicle response to control inputs, wind disturbances, and systems failure while hovering over a point on the ground. Typical control power and trim characteristics of the vehicle are also discussed.
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