ROTORCRAFT

WIPO Patent Application WO2003091099

A3

An ultralight coaxial dual rotor helicopter (10) having a substantially L shaped frame (12). Attached to the back of the frame (12) is a vertical shaft engine (18), and a pair of yaw paddles (30 and 32) for controlling yaw of the craft (10). The drive shaft (22) connects to a belt drive (24) at the top of the frame (12), which transmits the engine power to a transmission (24) and coaxial drive gear for driving the rotors (16). Crank actuators are provided for tilting the rotor axis to control the pitch and roll of the craft. A pilot seat (34) and ballast tank (48) are attached to the front of the frame (12). The ballast tank (48) may be filled with a volume of water to balance the craft for the weight of the pilot. The fuel tank (56) is located behind the pilot seat (34) on the centerline of the helicopter, such that as fuel is used and the weight of fuel in the tank (56) changes, the balance of the craft will not be affected. A simplified electronic control system controls all functions of the helicopter in response to pilot input.

WO/2016/048785	PROPELLER DIVERTER DUCT
WO/2015/058363	METHOD AND DEVICE FOR DRIVING ROTOR
WO/1993/003961	SHROUD GEOMETRY FOR UNMANNED AERIAL VEHICLES

PHELPS ARTHUR E III (US)
NORRIS ELWOOD G (US)
ROCK EUGENE F (US)
WALLACE EMITT (US)

PCT/US2003/012730

November 25, 2004

April 25, 2003

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AIRSCOOTER CORP (US)
PHELPS ARTHUR E III (US)
NORRIS ELWOOD G (US)
ROCK EUGENE F (US)
WALLACE EMITT (US)

B64C27/10; B64C27/52; B64C31/028; (IPC1-7): B64C27/82

US4531692A	1985-07-30
US6182923B1	2001-02-06
US6293492B1	2001-09-25
US5791592A	1998-08-11
US5370341A	1994-12-06
US6460802B1	2002-10-08
US20020109044A1	2002-08-15

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