HOT CYCLE ROTOR/WING COMPOSITE RESEARCH AIRCRAFT

Abstract
A preliminary design study of a hot cycle rotor/wing composite research aircraft is described. The hot cycle rotor/wing uses a single lightweight lifting surface which functions as both a rotor for takeoff and a fixed wing for horizontal flight. The rotary/wing is essentially an equilateral delta wing with short feathering blades at the three corners. The rotor is powered by a tip-jet hot cycle drive, and the turbojet exhaust is diverted from the rotor to provide forward propulsion. The hot cycle rotor/wing provides the advantages of hovering efficiency, low downwash velocity, and helicopter-like flying qualities for vertical and low-speed flight, in addition to the high- speed capability and cruise efficiency of the jet airplane. Its simplicity and light weight are made possible through the combined use of the all-pneumatic hot cycle drive system and the dual-purpose rotor/wing lift system. This eliminates the need for heavy and complex mechanical drive components and anti-torque tail rotor; it permits flight as a helicopter and as an airplane without recourse to duplicate lifting systems or to folding, tilting, or retracting of lift systems to effect conversion.

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