CPC B64C 29/0033 (2013.01) [B60L 50/64 (2019.02); B60L 53/00 (2019.02); B64C 13/48 (2013.01); B64C 27/82 (2013.01); B64C 39/12 (2013.01); B64D 27/02 (2013.01); B64D 27/24 (2013.01); B64D 27/26 (2013.01); B64D 31/06 (2013.01); G05D 1/101 (2013.01); B60L 2200/10 (2013.01); B64C 2027/8209 (2013.01); B64D 2027/026 (2013.01); B64D 2027/264 (2013.01)] | 12 Claims |
1. A hybrid power system, including:
a first power source that includes an internal combustion engine;
a second power source that includes a battery; and
a power controller, wherein:
the hybrid power system is included in a vertical takeoff and landing (VTOL) vehicle that flies in a transitional mode that occurs: (1) after a hovering mode and before a forward flight mode during a vertical takeoff or (2) after the forward flight mode and before the hovering mode during a vertical landing; and
the power controller selects one or more of the first power source and the second power source to power a rotor included VTOL vehicle, including by:
receiving a current draw associated with the VTOL vehicle;
receiving one or more flight state variables associated with a flight computer that indicate whether the VTOL vehicle is in the hovering mode, the forward flight mode, or the transitional mode;
during the vertical landing, the power controller performs a power source switch so that the second power source provides power to the rotor, including by supplementing power provided to the rotor by the first power source, independent of the current draw and in response to the one or more flight state variables associated with the flight computer being in the transitional mode that occurs after the forward flight mode and before the hovering mode during the vertical landing; and
during the vertical takeoff, the power controller selects, based at least in part on the current draw, one or more of the first power source and the second power source to power to the rotor.
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