Autogyro aircraft
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United States of America Patent
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Aug 13, 1996
Issued Date -
N/A
app pub date -
Apr 11, 1994
filing date -
Dec 12, 1990
priority date (Note) -
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Abstract
An autogyro has a teetering semi-rigid rotary wing with rigid rotor blades. The angle of attack (blade pitch) of the rotor blades is fully adjustable in flight continuously over an operational range, and varies along the blade length. A prerotator rotates the rotor blades up to takeoff speed at minimum drag, no lift and optimum engine efficiency. Engine power is disconnected from the rotor blades and their angle of attack is changed for optimum lift to facilitate smooth vertical takeoff. Rotor blade pitch is likewise adjusted during vertical landing. In flight, rotor blade angle of attack is varied to adjust autorotation, lift and drag at any flight airspeed. On the ground, the rotary wing is braked to prevent rotation. The autogyro may roll, pitch, or yaw, with complete independence of blade pitch with respect to all other relative motions. The pedals have disproportionate forward and backward motions. The autogyro has retractable gear capable of fail-safe gear-up landing.
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