HYBRID ASSEMBLY FOR AN AIRCRAFT

• US 20130227950A1
• Filed: 03/05/2013
• Published: 09/05/2013
• Est. Priority Date: 03/05/2012
• Status: Active Grant

• Current Assignee: Embry-Riddle Aeronautical University Incorporated
• Original Assignee: Embry-Riddle Aeronautical University Incorporated
• Inventors: Anderson, Richard, Costello, Lori, Eastlake, Charles, Greiner, Glenn P.
• Granted Patent: US 9,102,326 B2
• Time in Patent Office: Days
• US Class Current: 60/718
• CPC Class Codes: B60W 20/40 Controlling the engagement or disengagement of prime movers, e.g. for transition between prime movers power-up or power-down of the driveline B60W30/192
• 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: B64D 35/08 characterised by the transmission being driven by a plurality of power plants
• CPC Class Codes: F01B 21/00 Combinations of two or more machines or engines F01B23/00 takes precedence; combinations of two or more pumps F04; fluid gearing F16H
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 903/902 Prime movers comprising electrical and internal combustion motors

Abstract

A propeller driven aircraft powered by either an internal combustion engine or an electric motor. The parallel system hybrid aircraft can takeoff with the internal combustion engine and climb to a cruising altitude. The internal combustion engine then can be turned off and the electric motor turned on to power the aircraft'"'"'s propeller. The aircraft is capable of alternating operation between the electric motor and internal combustion engine as often as required at altitude. The aircraft can be landed using either the internal combustion engine or the electric motor. The transition of power from the internal combustion engine to the electric motor and back is performed through a hybrid clutch and pulley assembly that interconnects the internal combustion engine propeller flange to the propeller driveshaft. The electric motor is connected to the hybrid assembly through belts and sheaves. The electric motor throttle is controlled in the cockpit.

Claims

1. A hybrid aircraft propulsion system comprising:

a driveshaft;

an internal combustion engine mounted on the driveshaft to power an aircraft propeller;

an electrical motor that operates the aircraft propeller independently of the internal combustion engine;

a hybrid assembly interconnecting the internal combustion engine and electric motor to the driveshaft such that the electric motor and internal combustion engine operate in parallel to power the propeller independently.

2. The hybrid aircraft propulsion system of claim 1 wherein the hybrid assembly comprises a belt housing including at least one drive belt mounted on a plurality of sheaves to connect the electric motor to the driveshaft.

3. The hybrid aircraft propulsion system of claim 1 wherein the electric motor is mounted to the internal combustion engine using a plurality of turnbuckles.

4. The hybrid aircraft propulsion system of claim 1 further comprising a motor controller to control operation of the electric motor.

5. The hybrid aircraft propulsion system of claim 4 further comprising a plurality of battery modules to provide voltage to the motor controller to power the electric motor.

6. The hybrid aircraft propulsion system of claim 1 further comprising a linear potentiometer integrated into a cockpit control panel to regulate a speed of the electric motor.

7. The hybrid aircraft propulsion system of claim 1 wherein the hybrid assembly is mounted on the driveshaft of the internal combustion engine.

8. The hybrid aircraft propulsion system of claim 7 wherein the hybrid assembly further comprises a plurality of sheaves connecting the shafts of the internal combustion engine and the electric motor by at least one belt mounted on the plurality of sheaves.

9. The hybrid aircraft propulsion system of claim 8 wherein the hybrid clutch is attached to a first sheave of the hybrid assembly that is mounted on the driveshaft to transmit power to the propeller.

10. The hybrid aircraft propulsion system of claim 9 wherein the electric motor is connected by an electric motor shaft to a second sheave of the hybrid assembly.

11. The hybrid aircraft propulsion system of claim 8 further comprising a pulley system to translate power from the driveshaft to the propeller when the propeller is not positioned inline with the driveshaft.

12. The hybrid aircraft propulsion system of claim 9 further comprising a spline connecting the driveshaft to the first sheave of the hybrid assembly.

13. A hybrid aircraft propulsion system comprising:

a driveshaft;

an internal combustion engine mounted on the driveshaft to power the aircraft propulsion system;

a hybrid assembly attached to a propeller flange of the internal combustion engine; and

a propeller mounted to the hybrid assembly; and

an electrical motor mounted to the internal combustion engine, the electric motor providing power to the aircraft propulsion system independently of the internal combustion engine.

14. The hybrid aircraft propulsion system of claim 13 wherein the hybrid assembly comprises a belt housing including at least one drive belt mounted on a plurality of sheaves to connect the electric motor to the driveshaft.

15. The hybrid aircraft propulsion system of claim 13 wherein the hybrid assembly further comprises a plurality of sheaves connecting the shafts of the internal combustion engine and the electric motor by at least one belt mounted on the plurality of sheaves.

16. The hybrid aircraft propulsion system of claim 15 wherein the hybrid clutch is attached to a first sheave of the hybrid assembly that is mounted on the driveshaft to transmit power to the propeller.

17. The hybrid aircraft propulsion system of claim 13 further comprising a plurality of batteries to provide voltage to a motor controller to power the electric motor.

18. A method for in flight operation of a propeller-driven hybrid aircraft propulsion system, the hybrid aircraft propulsion system having an internal combustion engine mounted on a driveshaft, an electric motor, and a hybrid assembly interconnecting the internal combustion engine and electric motor to the driveshaft, the method comprising:

activating an electrical system of the electric motor;

energizing a battery management system to control operation of the electric motor;

decreasing internal combustion engine throttle power level;

increasing an electric motor throttle power level;

turning off the internal combustion engine; and

adjusting the electric motor throttle power level to maintain a speed and a cruising altitude of the aircraft.

19. The method for in flight operation of a propeller-driven hybrid aircraft propulsion system of claim 18 further comprises transitioning from operation with power supplied by the electric motor to power generated by the internal combustion engine.

20. The method for in flight operation of a propeller-driven hybrid aircraft propulsion system of claim 19 wherein transitioning comprises:

decreasing the electric motor throttle power level;

restarting the internal combustion engine;

increasing the internal combustion engine throttle power level; and

turning off the electric motor and battery management system.

21. The method for in flight operation of a propeller-driven hybrid aircraft propulsion system of claim 20 further comprising switching between operation with power supplied by the electric motor and power generated by the internal combustion engine dependent upon the energy supplied from a battery module.

22. The method for in flight operation of a propeller-driven hybrid aircraft propulsion system of claim 21 further comprising using either the internal combustion engine or the electric motor for a descent and a landing portion of a flight.