Hybrid drive powered lift platform

• US 20060213710A1
• Filed: 03/25/2005
• Published: 09/28/2006
• Est. Priority Date: 03/25/2005
• Status: Active Grant

• Current Assignee: Aeroflex Incorporated (Cobham PLC)
• Original Assignee: Aeroflex Incorporated (Cobham PLC)
• Inventors: De Roche, Mark Stephen
• Granted Patent: US 7,231,997 B2
• Time in Patent Office: Days
• US Class Current: 180/116
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: B64C 39/028 Micro-sized aircraft
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports

Abstract

An air-based thrust recovery system for use in a powered lift platform utilizing fixed-pitch propellers is provided. The system utilizes an air compressor coupled to the drive motor of the platform and an on-board, high pressure tank for air storage. The fixed-pitch propellers are coupled to the primary drive system with over-running clutches, thus allowing the thrust recovery system to rotate the propellers faster than if driven solely by the primary drive system. Preferably the propellers are surrounded by air ducts. The thrust recovery system uses individually, or in combination, cold air jets mounted at the tips of the propellers, a circulation control system which blows out the leading or trailing edge of the propellers, and one or more perforated tubing segments surrounding at least a portion of the platform'"'"'s air ducts.

Claims

1. A lift platform comprising:

a primary drive system, comprising;

an engine;

a transmission coupled to said engine;

a first fixed-pitch propeller coupled to said transmission;

a first over-running clutch interposed between said transmission and said first fixed-pitch propeller;

a second fixed-pitch propeller coupled to said transmission; and

a second over-running clutch interposed between said transmission and said second fixed-pitch propeller; and

an auxiliary drive system, comprising;

an air compressor coupled to said engine;

an air storage tank coupled to said air compressor;

a thrust recovery system coupled to said air storage tank; and

at least one valve for controlling air flow from said air storage tank to said thrust recovery system.

2. The lift platform of claim 1, wherein said first and second over-running clutches are combined into a single clutch unit.

3. The lift platform of claim 1, wherein said thrust recovery system further comprises a first plurality of tip jets positioned at a first plurality of propeller tips corresponding to said first fixed-pitch propeller and a second plurality of tip jets positioned at a second plurality of propeller tips corresponding to said second fixed-pitch propeller.

4. The lift platform of claim 3, wherein said at least one valve comprises a single valve controlling air flow to both said first and second pluralities of tip jets.

5. The lift platform of claim 3, wherein said at least one valve comprises a first valve controlling air flow to said first plurality of tip jets and a second valve controlling air flow to said second plurality of tip jets.

6. The lift platform of claim 3, further comprising a first air duct surrounding said first fixed-pitch propeller and a second air duct surrounding said second fixed-pitch propeller.

7. The lift platform of claim 3, wherein said engine is a turbine engine.

8. The lift platform of claim 3, wherein said thrust recovery system further comprises a first plurality of holes positioned within each trailing edge of each propeller blade of said first fixed-pitch propeller and a second plurality of holes positioned within each trailing edge of each propeller blade of said second fixed-pitch propeller.

9. The lift platform of claim 8, wherein said first and second pluralities of holes are between 0.020 and 0.30 inches in diameter.

10. The lift platform of claim 8, wherein said first and second pluralities of holes are positioned within a region of 15 to 25 percent axial chord upstream of each trailing edge.

11. The lift platform of claim 3, wherein said thrust recovery system further comprises a first plurality of holes positioned within each leading edge of each propeller blade of said first fixed-pitch propeller and a second plurality of holes positioned within each leading edge of each propeller blade of said second fixed-pitch propeller.

12. The lift platform of claim 8, wherein said at least one valve comprises a single valve controlling air flow to said first and second pluralities of holes and to said first and second pluralities of tip jets.

13. The lift platform of claim 8, wherein said at least one valve comprises a first valve controlling air flow to said first plurality of holes and to said first plurality of tip jets, and a second valve controlling air flow to said second plurality of holes and to said second plurality of tip jets.

14. The lift platform of claim 8, wherein said at least one valve comprises a first valve controlling air flow to both said first and second pluralities of tip jets and a second valve controlling air flow to both said first and second pluralities of holes.

15. The lift platform of claim 8, wherein said at least one valve comprises a first valve controlling air flow to said first plurality of tip jets, a second valve controlling air flow to said second plurality of tip jets, a third valve controlling air flow to said first plurality of holes and a fourth valve controlling air flow to said second plurality of holes.

16. The lift platform of claim 8, further comprising a first air duct surrounding said first fixed-pitch propeller and a second air duct surrounding said second fixed-pitch propeller.

17. The lift platform of claim 8, wherein said engine is a turbine engine.

18. The lift platform of claim 1, further comprising:

a first air duct surrounding said first fixed-pitch propeller;

a second air duct surrounding said second fixed-pitch propeller; and

wherein said thrust recovery system further comprises means for selectively blowing air over said first air duct and means for selectively blowing air over said second air duct.

19. The lift platform of claim 18, wherein said means for selectively blowing air over said first air duct comprises a first perforated tubing encircling at least a portion of said first air duct and wherein said means for selectively blowing air over said second air duct comprises a second perforated tubing encircling at least a portion of said second air duct.

20. The lift platform of claim 18, wherein said means for selectively blowing air over said first air duct comprises a first multi-segmented perforated tubing encircling at least a portion of said first air duct and wherein said means for selectively blowing air over said second air duct comprises a second multi-segmented perforated tubing encircling at least a portion of said second air duct and wherein said at least one valve comprises multiple valves controlling air flow to each segment of said first multi-segmented perforated tubing and each segment of said second multi-segmented perforated tubing.

21. The lift platform of claim 18, wherein said means for selectively blowing air over said first air duct comprises a first perforated tubing encircling at least a portion of said first air duct, and wherein said means for selectively blowing air over said second air duct comprises a second perforated tubing encircling at least a portion of said second air duct, and wherein said thrust recovery system further comprises a first plurality of tip jets positioned at a first plurality of propeller tips corresponding to said first fixed-pitch propeller and a second plurality of tip jets positioned at a second plurality of propeller tips corresponding to said second fixed-pitch propeller.

22. The lift platform of claim 18, wherein said means for selectively blowing air over said first air duct comprises a first perforated tubing encircling at least a portion of said first air duct, and wherein said means for selectively blowing air over said second air duct comprises a second perforated tubing encircling at least a portion of said second air duct, and wherein said thrust recovery system further comprises:

a first plurality of tip jets positioned at a first plurality of propeller tips corresponding to said first fixed-pitch propeller and a second plurality of tip jets positioned at a second plurality of propeller tips corresponding to said second fixed-pitch propeller; and

a first plurality of holes positioned within each trailing edge of each propeller blade of said first fixed-pitch propeller and a second plurality of holes positioned within each trailing edge of each propeller blade of said second fixed-pitch propeller.