Hybrid electric power helicopter

• US 9,248,908 B1
• Filed: 06/12/2013
• Issued: 02/02/2016
• Est. Priority Date: 06/12/2013
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Luyks, Leo J.
• Primary Examiner(s): Eldred, J. Woodrow
• Application Number:
  US13/916,283
• Time in Patent Office: 965 Days
• Field of Search: 244/17.11, 244/17.23, 244/17.25, 244/53.R, 244/60, 244/17.13, 244/76.R, 903/903, 903/905, 903/906
• US Class Current: 1/1
• CPC Class Codes: B64C 2027/8209 Electrically driven tail rotors
• CPC Class Codes: B64C 27/04 Helicopters
• CPC Class Codes: B64C 27/12 Rotor drives
• CPC Class Codes: B64C 27/52 Tilting of rotor bodily relative to fuselage of see-saw type construction B64C27/43
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 903/903 having energy storing means, e.g. battery, capacitor

Abstract

A helicopter has a propulsion system that includes a diesel engine driven electric generator, battery storage, power inverters for converting AC current to DC current and converting DC current to AC current, and an electric motor powered main rotor and an electric motor powered tail rotor. The propulsion system is integrated with electric controls of the main rotor electric motor and the tail rotor electric motor to provide additional system efficiencies. The design of the helicopter allows a single engine helicopter to be just as safe as a twin engine design helicopter while consuming less fuel. The helicopter design also includes a main rotor tilt system which tilts the rotation axis of the main rotor forward during high-speed flight to improve the aerodynamic efficiency of the helicopter airframe and rotary wing.

Claims

1. A method to enhance fuel efficiency of a rotary wing aircraft, the method comprising:

providing the aircraft with a main rotor electric motor and operatively connecting the main rotor electric motor to a main rotor of the aircraft, whereby running the main rotor electric motor rotates the main rotor of the aircraft;

providing the aircraft with an engine;

providing the aircraft with a generator, operatively connecting the generator to the engine and operatively connecting the generator to the main rotor electric motor, whereby running the engine in turn operates the generator and the operating generator supplies electric power to the main rotor electric motor to run the main rotor electric motor and rotate the main rotor;

providing the aircraft with a battery, operatively connecting the battery to the generator and operatively connecting the battery to the main rotor electric motor;

providing the aircraft with a flight control system, the flight control system controlling the engine to run at idle during takeoff and the flight control system controlling the main rotor electric motor to use battery power to power the takoff of the aircraft;

following takeoff of the aircraft, the flight control system controlling the engine to increase speed above idle and operate the generator to recharge the battery during flight of the aircraft; and

,

the flight control system controlling the engine to return to idle and the flight control system controlling the main rotor electric motor to use battery power to land the aircraft.

2. The method of claim 1, further comprising:

providing the aircraft with a tail rotor electric motor and operatively connecting the tail rotor electric motor to a tail rotor of the aircraft, whereby running the tail rotor electric motor rotates the tail rotor of the aircraft; and

,

operatively connecting the generator to the tail rotor electric motor, whereby the operating generator supplies electric power to the tail rotor electric motor to run the tail rotor electric motor and rotate the tail rotor.

3. The method of claim 1, further comprising:

directly connecting the main rotor electric motor to the main rotor of the aircraft.

4. The method of claim 2, further comprising:

directly connecting the tail rotor electric motor to the tail rotor of the aircraft.

5. The method of claim 1, further comprising:

directly connecting the engine to the generator.

6. The method of claim 1, further comprising:

operatively connecting the battery to the tail rotor electric motor.

7. The method of claim 1, further comprising:

providing the aircraft with an inverter, operatively connecting the inverter with the generator and operatively connecting the inverter with the battery.

8. The method of claim 6, further comprising:

providing the aircraft with a second inverter, operatively connecting the second inverter to the battery and operatively connecting the second inverter to the main rotor electric motor.