Hybrid contingency power drive system
AssigneeSikorsky Aircraft Corporation
InventorPeter James Waltner
Life of this patent
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Abstract
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.
Claims14
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;
- and
- a 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.
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;
- and
- causing 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 rotor
- wherein 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.
Dependencies are inferred from the claim text.