Rotor system for winged aircraft

• US 4,979,698 A
• Filed: 07/11/1989
• Issued: 12/25/1990
• Est. Priority Date: 07/07/1988
• Status: Expired due to Fees

• Current Assignee: Paul Lederman
• Original Assignee: Paul Lederman
• Inventors: Lederman, Paul
• Primary Examiner(s): Barefoot, Galen
• Application Number:
  US07/378,273
• Time in Patent Office: 532 Days
• Field of Search: 244/7 R, 244/7 A, 244/7 B, 244/8, 244/17.11, 244/17.13, 244/36, 244/2, 244/56, 244/66, D12/335, D12/336, D12/326, D12/327, D12/328, 416/142, 416/143, 416/148
• US Class Current: 244/7.00R
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage

Abstract

A rotor system for a rotor convertible fixed winged aircraft comprising a rotatable rotor shaft mounted on one of the wings of the aircraft, the shaft tiltable between a substantially vertical position and a substantially horizontal position, a rotor mounted to the shaft and including at least one blade, the blade having an adjustable blade angle relative to the shaft, apparatus for tilting the shaft between the vertical and horizontal positions, controls responsive to the tilting of the shaft for automatically adjusting the blade angle of a blade to an autogyro blade angle when the shaft is in the vertical position and to a substantially feathered blade angle when the shaft is in the horizontal position.

Claims

1. On a fixed winged, jet propelled aircraft, a rotor system for contributing to lift during takeoff and flight comprising:

a rotatable rotor shaft mounted on one of said wings, said shaft tiltable between a substantially vertical position and a substantially horizontal position;

a rotor mounted to said shaft, and including at least one blade, said blade having an adjustable blade angle relative to said shaft;

means for tilting said shaft between said vertical and horizontal positions;

means, responsive to the tilting of said shaft for automatically adjusting the blade angle of said blade to an autogyro blade angle when said shaft is in said vertical position to lend autogyro lift during takeoff and landing, and to a substantially feathered blade angle when said shaft is in said horizontal position to minimize drag and add aerodynamic lift during wingborne flight.

2. The rotor system of claim 1 wherein said shaft is mounted near the center of lift of said wing.

3. The rotor system of claim 1 further including means for differentially adjusting said blade angle independent of the tilting of said shaft to override said means for automatically adjusting.

4. The rotor system of claim 3 further including means for rotating said shaft before takeoff to energize said rotor.

5. The rotor system of claim 1 further including means for inhibiting rotation of said shaft when said shaft is in said horizontal position.

6. The rotor system of claim 1 wherein said winged aircraft includes substantially horizontal wings having winglets attached to their distal ends, said winglets being angled upward from said wings.

7. The rotor system of claim 6 wherein said shaft is mounted on said winglet.

8. The rotor system of claim 7 wherein said rotor includes at least two blades, each blade being shorter than the wing on which it is mounted.

9. The rotor system of claim 1 wherein said means for tilting includes a tilt driver and a tilt gear.

10. The rotor system of claim 1 wherein said means for automatically adjusting includes tilt indicator means and pitch adjuster means responsive to said tilt indicator means.

11. The rotor system of claim 4 wherein the means for rotating includes an electric motor.

12. The rotor system of claim 4 wherein the means for rotating includes pneumatic means.

13. The rotor system of claim 5 wherein the means for inhibiting includes indexed brake means associated with said shaft.

21. The rotor system of claim 1 installed upon an aircraft having more than one fuselage linked by a wing structure providing lift, wherein the fuselages and the wing structure house payload space.

14. On a fixed winged, jet propelled aircraft, a rotor system for contributing to lift during takeoff and flight comprising:

one rotatable rotor shaft mounted on each of said wings, said shafts tiltable during flight between a substantially vertical position and a substantially horizontal position;

a rotor, including at least one blade, mounted on each of said shafts, each said blade having a pitch relative to said wing;

means for synchronously tilting said shafts between said vertical and horizontal positions;

means for inhibiting rotation of said rotors when said shafts are in said horizontal position; and

means responsive to the tilting of said shafts, for automatically adjusting the pitch of each said blade so that said blades lend lift when said shafts are in said vertical position during takeoff and landing, and said blades are substantially feathered when said shafts are in said horizontal position during wingborne flight to attain aerodynamic lift.

15. The rotor system of claim 14 further including means for differentially adjusting the pitch of said blades independent of the tilting of said shaft to override said means for automatically adjusting.

16. The rotor system of claim 14 wherein said rotor shafts counter rotate to provide improved balance.

17. The rotor system of claim 16 wherein the outboard blades of said rotors advance in the direction of travel.

18. The rotor system of claim 14 wherein said means for synchronously tilting includes a tilt synchronizer for synchronizing the tilting of said shafts, and a tilt driver and tilt gear associated with each said rotor, said tilt drivers responsive to said tilt synchronizer.

19. The rotor system of claim 14 wherein said means for inhibiting includes indexed braking means, for inhibiting the rotation of said shafts, associated with each said shaft.

20. The rotor system of claim 14 wherein said means for automatically adjusting includes tilt indicator means and pitch adjustor means responsive to said tilt indicator means.