CPC B64C 29/0033 (2013.01) [A61L 9/122 (2013.01); B64C 21/06 (2013.01); B64C 27/28 (2013.01); B64C 29/00 (2013.01); B64D 27/14 (2013.01); B64D 27/24 (2013.01); H02J 7/0042 (2013.01); H02J 50/10 (2016.02); H02P 9/04 (2013.01); A61L 2209/133 (2013.01); B64C 3/385 (2013.01); B64C 29/0008 (2013.01); B64D 2027/026 (2013.01); B64D 2221/00 (2013.01); Y02T 50/60 (2013.01)] | 18 Claims |
1. A propulsion system of an aircraft comprising:
at least one unducted fan and at least one ducted fan, the at least one unducted fan and the at least one ducted fan being powered by an electric power source and rotatable between a vertical thrust position and a forward thrust position; and
a controller configured to distribute electrical power between the at least one unducted fan and the at least one ducted fan,
wherein, during a first mode when the at least one unducted fan and the at least one ducted fan are in the vertical thrust position, the controller is configured to distribute the electrical power between each of the at least one unducted fan and each of the at least one ducted fan such that the at least one unducted fan is a primary source of thrust, and
wherein, during a second mode when the at least one unducted fan and the at least one ducted fan are in the forward thrust position, the controller is configured to distribute the electrical power between each of the at least one unducted fan and each of the at least one ducted fan such that the at least one ducted fan is the primary source of thrust.
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