PARALLEL HYBRID-ELECTRIC AIRCRAFT ENGINE

Abstract

A parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer neede

Claims

1. A parallel hybrid-electric aircraft engine for providing power to a propeller-driven aircraft, comprising: means for provide power for takeoff and climb in parallel with an electric motor; means for thrust; means for transferring power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure; means for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor, single directionally connected to said means for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure; means for transmit rotary power to the propeller shaft and to switch to a generator to provide power for accessories and to recharge the batteries, rigidly connected to said means for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor, and rigidly connected to said means for thrust; and means for transferring rotary motion to the sprag clutch, rigidly connected to said means for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure, and rigidly connected to said means for provide power for takeoff and climb in parallel with an electric motor.

2. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for provide power for takeoff and climb in parallel with an electric motor comprises a gasoline or diesel internal combustion engine.

3. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for thrust comprises a variable pitch propeller.

4. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure comprises an over-running sprag clutch.

5. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor comprises a ribbed flexible belt.

6. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for transmit rotary power to the propeller shaft and to switch to a generator to provide power for accessories and to recharge the batteries comprises an out-runner electric motor.

7. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for transferring rotary motion to the sprag clutch comprises an engine output shaft.

8. A parallel hybrid-electric aircraft engine for providing power to a propeller-driven aircraft, comprising: a gasoline or diesel internal combustion engine, for provide power for takeoff and climb in parallel with an electric motor; a variable pitch propeller, for thrust; an over-running sprag clutch, for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure; a ribbed flexible belt, for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor, single directionally connected to said sprag clutch; an out-runner electric motor, for transmit rotary power to the propeller shaft and to switch to a generator to provide power for accessories and to recharge the batteries, rigidly connected to said flexible belt, and rigidly connected to said propeller; and an engine output shaft, for transferring rotary motion to the sprag clutch, rigidly connected to said sprag clutch, and rigidly connected to said internal combustion engine.

9. A parallel hybrid-electric aircraft engine for providing power to a propeller-driven aircraft, comprising: a gasoline or diesel internal combustion engine, for provide power for takeoff and climb in parallel with an electric motor; a variable pitch propeller, for thrust; an over-running sprag clutch, for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure; a ribbed flexible belt, for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor, single directionally connected to said sprag clutch; an out-runner electric motor, for transmitting rotary power to the propeller shaft and to switch to a generator to provide power for accessories and to recharge the batteries, rigidly connected to said flexible belt, and rigidly connected to said propeller; and an engine output shaft, for transferring rotary motion to the sprag clutch, rigidly connected to said sprag clutch, and rigidly connected to said internal combustion engine.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0013] A complete understanding of the present invention may be obtained by reference to the accompanying drawings, when considered in conjunction with the subsequent, detailed description, in which:

[0014] FIG. 1 is a front perspective view of a parallel hybrid-electric aircraft engine;

[0015] FIG. 2 is a lower perspective view of a parallel hybrid-electric aircraft engine;

[0016] FIG. 3 is a left view of a parallel hybrid-electric aircraft engine;

[0017] FIG. 4 is a front view of a parallel hybrid-electric aircraft engine;

[0018] FIG. 5 is a top view of a parallel hybrid-electric aircraft engine; and

[0019] FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine.

[0020] For purposes of clarity and brevity, like elements and components will bear the same designations and numbering throughout the Figures.

DESCRIPTION OF THE PREFERRED EMBODIMENT

[0021] FIG. 1 is a perspective view of a hybrid-electric aircraft engine consisting of an internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50 and propeller 20. FIG. 2 is a lower perspective view of parallel hybrid electric engine showing the internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50 and propeller 20. FIG. 3 is a left side view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20. FIG. 4 is a front view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50, engine output shaft 60 and propeller 20. FIG. 5 is a top view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20. FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20.

[0022] Since other modifications and changes varied to fit particular operating requirements and environments will be apparent to those skilled in the art, the invention is not considered limited to the example chosen for purposes of disclosure, and covers all changes and modifications which do not constitute departures from the true spirit and scope of this invention.

[0023] Having thus described the invention, what is desired to be protected by Letters Patent is presented in the subsequently appended claims.