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A hybrid power drive system for an aircraft comprises a rotor that receives power and a first power drive sub-system including at least one engine in connection with the rotor is configured to provide a first power to the rotor. Further, the hybrid power drive system also includes a second power dri

A hybrid power drive system for an aircraft comprises a rotor that receives power and a first power drive sub-system including at least one engine in connection with the rotor is configured to provide a first power to the rotor. Further, the hybrid power drive system also includes a second power drive sub-system connected in parallel to the first power drive sub-system. The second power drive sub-system is configured to provide a second power to the rotor a second power drive sub-system connected in parallel to the first power drive sub-system and configured to provide a second power to the rotor when the first power provided by the first power drive sub-system is less than a power demand of the rotor.

대표청구항 ▼

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

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 provide a second power to the rotor when the first power provided by the first power drive sub-system is less than a power demand of the rotor; anda controller operable to supply power from the second power drive sub-system to the first power drive sub-system to power to the rotor in response to a signal indicative of the power demand of the rotor. 2. The hybrid power drive system of claim 1, wherein the second power drive sub-system includes an electric motor in electric communication with an electric power source of the hybrid power drive system. 3. The hybrid power drive system of claim 1, wherein an electric motor is in mechanical communication with the first power drive sub-system at a rotor shaft. 4. The hybrid power drive system of claim 1, wherein an electric motor is in mechanical communication with the first power drive system at a first gearbox. 5. The hybrid power drive system of claim 1, wherein an electric motor is mechanical communication with the first power drive sub-system at an engine power shaft. 6. The hybrid power drive system of claim 1, wherein an electric power source comprises a rechargeable energy source selected from a list, wherein the list includes at least one of a battery, a capacitor, and a flywheel energy storage sub-system. 7. The hybrid power drive system of claim 1, further comprising a controller configured to receive a power demand signal indicative of the power demand. 8. The hybrid power drive system of 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 contingency power, and the second power drive sub-system is an auxiliary power drive sub-system. 9. The hybrid power drive system of claim 1, wherein the first power is less than the power demand of the rotor when the first power drive sub-system fails due to an emergency condition. 10. The hybrid power drive system of claim 1, wherein the emergency condition is a failure of the engine. 11. The hybrid power drive system of claim 1, wherein the first power is less than the power demand of the rotor when the engine increases the power demand in accordance with a drooped rotor state. 12. 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; andcausing the supply of second power from the second power drive sub-system to the first power drive sub-system to provide power to the rotor when the first power provided by the first power drive sub-system is less than the power demand of the rotorwherein a controller in communication with a flight control computer causes the supply of second power from the second power drive sub-system to the first power drive sub-system to provide power to the rotor in response to receiving the signal indicative of the power demand on the rotor. 13. The method of claim 12, 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. 14. The method of claim 12, wherein the receiving of the signal indicative of the power demand on the rotor is due to an emergency condition, and wherein the emergency condition is one ofa failure of the engine andwhen the engine increases the power demand in accordance with a drooped rotor state.