U.S. patents available from 1976 to present.
U.S. patent applications available from 2005 to present.

Paddle wheel rotorcraft

Patent 5265827 Issued on November 30, 1993. Estimated Expiration Date: Icon_subject September 16, 2012. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.

Patent References

1754977

2123916

2413460

2507657

2580428

Lift augmenting device for aircraft
Patent #: 4194707
Issued on: 03/25/1980
Inventor: Sharpe

Propulsive lifting rotors
Patent #: 4210299
Issued on: 07/01/1980
Inventor: Chabonat

Cyclorotor composite aircraft
Patent #: 4482110
Issued on: 11/13/1984
Inventor: Crimmins, Jr.

Rotor for developing sustaining and propelling forces in a fluid, steering process, and aircraft equipped with such rotor Patent #: 5100080
Issued on: 03/31/1992
Inventor: Servanty

Inventor

Assignee

Application

No. 946266 filed on 09/16/1992

US Classes:

244/20, Feathering244/9, Airplane and paddle wheel sustained244/70Paddle wheel

Examiners

Primary: Barefoot, Galen L.

Attorney, Agent or Firm

Foreign Patent References

  • 480750 GB. 02/13/2012

International Class

B64C 029/00

Abstract

An aircraft having vertical takeoff and landing capability having at least first and second laterally extending paddle wheels rotatable on a central axis generally perpendicular to the longitudinal axis of the aircraft and between its nose and tail. Each of the paddle wheels has a plurality of blades pivoted by a system of linear actuators to a determined optimum blade pitch angle. One paddle wheel is positioned adjacent the port side of the aircraft and the other paddle wheel is positioned adjacent the starboard side. The pilot is able to operate the aircraft in all regimes of flight by differentially adjusting the pivot angle of each of the blades. In one embodiment utilizing only a pair of paddle wheels, differential operation of the blades provides lift, thrust, roll, and yaw control of the aircraft, while an aircraft pitch control rotor rotatable about a vertical axis distant from the paddle wheels is provided for controlling pitch of the aircraft. In another embodiment of the invention, the aircraft is provided with both forward and aft pairs of paddle wheels such that differential operation of the blades of the forward and aft paddle wheels provides pitch control of the aircraft without need of a separate pitch control rotor, while also providing lift, thrust, roll, and yaw control.

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