Hybrid electric power drive system for a rotorcraft
A hybrid power drive system for an aircraft that comprises a rotor and a first power drive sub-system. The first power drive sub-system includes at least one engine in connection with the rotor and provides a first power to the rotor. The hybrid power drive system also includes a second power drive sub-system connected in parallel to the first power drive sub-system, which supplements with a second power the first power delivered to the rotor during operation of the aircraft. In addition, an electric power source provides a third power to the second power drive sub-system.
1. A hybrid power drive system for an aircraft, comprising:
a rotor;
a first power drive sub-system including at least one engine in connection with the rotor and configured to provide a first power to the rotor;
a second power drive sub-system connected in parallel to the first power drive sub-system and configured to supplement, with a second power, the first power delivered to the rotor during operation of the aircraft, a motor output shaft of the second power drive sub-system being in direct mechanical communication with the first power drive sub-system at a main rotor shaft; and
an electric power source configured to provide a third power to the second power drive sub-system,
wherein the second power drive sub-system includes an electric motor in electric communication with a rechargeable energy source and a non-rechargeable energy source.
2. The hybrid power drive system of claim 1 , wherein the rechargeable energy source is selected from a list, wherein the list includes at least one of a battery, a capacitor, and a flywheel energy storage sub-system.
3. The hybrid power drive system according to claim 1 , wherein the rechargeable energy source is configured to provide power to the rotor during a transient high power demand condition.
4. The hybrid power drive system of claim 1 , wherein the non-rechargeable energy source is selected from a list, wherein the list includes an auxiliary power unit, supplemental power unit, and a hybrid electric engine.
5. The hybrid power drive system according to claim 1 , wherein the non-rechargeable energy source is configured to provide longer duration supplemental rotational power to the rotor during an increased power demand on the engine.
6. The hybrid power drive system according to claim 1 , wherein the first power is a main power, the first power drive sub-system is a main power drive sub-system, the second power is a supplemental rotational power, and the second power drive sub-system is an auxiliary power drive sub-system.
7. A method for controlling a hybrid power drive system of an aircraft, comprising:
receiving a signal indicative of a power demand on a rotor;
connecting in parallel a first power drive sub-system and a second power drive sub-system, a motor output shaft of the second power drive sub-system being in direct mechanical communication with the first power drive sub-system at a main rotor shaft;
connecting an electric power source to the second power drive sub-system;
supplying a second power from the second power drive sub-system to the first power drive sub-system to provide power to the rotor; and
supplying energy to the electric motor from a rechargeable energy source and a non-rechargeable energy source.
8. The method of claim 7 , wherein the connecting of the first power drive sub-system to the second power drive sub-system further comprises connecting an electric motor to the first power drive sub-system.
9. The method according to claim 7 , further comprising:
connecting the electric motor to the first power drive sub-system via at least one of a main rotor shaft, a gearbox, and an engine power shaft.
10. The method according to claim 7 , wherein the first power is a main power, the first power drive sub-system is a main power drive sub-system, the second power is a contingency power, and the second power drive sub-system is an auxiliary power drive sub-system.