Aircraft

• US 7,011,274 B1
• Filed: 10/06/1997
• Issued: 03/14/2006
• Est. Priority Date: 10/01/1997
• Status: Expired due to Fees

• Current Assignee: Pierre Eugene Georges Hardoin
• Original Assignee: Pierre Eugene Georges Hardoin
• Inventors: Hardoin, Pierre
• Primary Examiner(s): Carone, Michael J.
• Assistant Examiner(s): Sukman, Gabriel S.
• Application Number:
  US09/647,626
• Time in Patent Office: 3,081 Days
• Field of Search: 244/17.23, 244/12.4, 244/53.R, 244/52
• US Class Current: 244/17.23
• CPC Class Codes: B64D 35/00 Transmitting power from power plants to propellers or rotors; Arrangements of transmissions

Abstract

The invention concerns a land and flying vehicle with its tubular frame, 2 main rotors with blades and adjustable pitch-propellers, with its drive propelled by the force of a hydraulic turbine located at the end of its driving shaft. Said force is propelled by a very high pressure pump driven by an internal combustion engine or jet engine. Streamlined pusher propellers (already patented) located on the side are driven by hydraulic turbines located at the shaft end of rotating propellers from 0° to 180°, once they are extended.

Drawings describe the revolutionary design and unable the installation of said system on some current helicopter. By said method the present drive assembly, gimbal joints, gear boxes, are replaced with turbine drives with smooth and lightweight start. Said method can be adapted on running vehicles, including trains, whereof the designs and applications are reserved.

Claims

1. An aircraft comprising:

a hydraulic drive propelled by 2 composed separated forces including an engine, and a very high pressure pump driven by the engine,

a central chassis having tubes, the chassis defining a rectangular form for 3 persons including the pilot in the center, above the engine, and 2 passengers on each side of the pilot for rapid exit, the chassis having a central axle, a first welded triangular girder fixed on the central axle, a second welded triangular girder fixed on the central axle, the second girder being behind the first girder, the first and second girders including strengthening crosspieces;

first and second lift rotors;

a first vertical shaft coupled to drive the first lift rotor;

a first hydraulic turbine coupled to drive the first vertical shaft, the first hydraulic turbine being in fluid communication with the pump;

a first support fixed at an end of the first girder, the first support holding the first hydraulic turbine;

a second vertical shaft coupled to drive the second lift rotor;

a second hydraulic turbine coupled to drive the second vertical shaft, the second hydraulic turbine being in fluid communication with the pump;

a second support fixed at an end of the second girder, the second support holding the second hydraulic turbine, wherein each lift rotor has 4 blades of 20 feet diameter, each blade being more stable and wider at a pivoting connection, each blade having a tip downward 50 degrees curve to avoid gushing outwards, each blade having an air passage, thereby avoiding vibration of the 4 blades of the lift rotor;

a source of compressed air, and a mechanism that couples the source of compressed air to the very high pressure pump in the event of failure of the engine.

2. An aircraft in accordance with claim 1 further including

a body with a non-return flap integrated in the first hydraulic turbine.

3. An aircraft in accordance with claim 1 wherein

the first lift rotor is configurated to articulate in response to the action of a control stick.

4. An aircraft in accordance with claim 3 further

including a cone for guiding the vertical shaft.

5. An aircraft in accordance with claim 1 further including

a pressure manifold;

a first valve coupled to the pressure manifold; and

a second valve coupled to the pressure manifold, in parallel with the first valve, wherein the first hydraulic turbine is in fluid communication with the pump via the pressure manifold and the first valve to regulate revolutions of the first turbine, and the second hydraulic turbine is in fluid communication with the pump via the pressure manifold and the second valve to regulate revolutions of the second turbine.

6. An aircraft in accordance with claim 1 further including

a retractable faired propeller for very precise movement of the aircraft is hovering;

and

a manifold with an outlet, having a pre-adjusted output rate, in communication with the pump and the retractable faired propeller.

7. An aircraft in accordance with claim 6 wherein the retractable faired propeller is configurated to rotate 180 degrees thus enabling forward or backward movement of the aircraft.

8. An aircraft in accordance with claim 6 further including

a second retractable faired propeller that can be moved jointly or separately relative to the first retractable faired propeller.

9. An aircraft in accordance with claim 1 further including

a pressure manifold wherein the first hydraulic turbine is in fluid communication with the pump via the pressure manifold.

10. An aircraft in accordance with claim 1 further including

a clutch between the engine and the hydraulic pump.