CPC B64D 27/24 (2013.01) [B64D 27/14 (2013.01); B64D 31/00 (2013.01); F02C 6/00 (2013.01); H02K 7/1823 (2013.01); B64D 27/026 (2024.01)] | 17 Claims |
1. A hybrid-electric aircraft system, comprising:
first and second hybrid-electric engines, each of which comprises a gas turbine engine and an electric motor to drive operations of the first and second hybrid-electric engines;
a supplemental power unit (SPU) configured as a thermal engine paired with a generator and to generate electrical power; and
a control system,
wherein the first hybrid-electric engine is operable under control of the control system and the second hybrid-electric engine is operable with the gas turbine engine of the second hybrid-electric engine shut off under control of the control system with electrical power generated by the SPU diverted to the electric motor of the second hybrid-electric engine, and
wherein each of the first and second hybrid-electric engines comprises a full authority digital engine control (FADEC) and the SPU comprises an SPU controller which is configured to independently operate the SPU independently from the control system and which is directly communicative with the FADEC of each of the first and second hybrid-electric engines.
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