US 12,012,214 B2
Hybrid propulsion system for vertical take-off and landing aircraft
Romain Jean Gilbert Thiriet, Moissy-Cramayel (FR); and Stéphane Meyer Beddok, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/609,060
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed May 5, 2020, PCT No. PCT/FR2020/050747
§ 371(c)(1), (2) Date Nov. 5, 2021,
PCT Pub. No. WO2020/225510, PCT Pub. Date Nov. 12, 2020.
Claims priority of application No. 1904715 (FR), filed on May 6, 2019.
Prior Publication US 2022/0185489 A1, Jun. 16, 2022
Int. Cl. B64D 27/02 (2006.01); B60L 50/40 (2019.01); B60L 50/50 (2019.01); B64C 29/00 (2006.01); B64D 27/04 (2006.01); B64D 27/10 (2006.01); B64D 27/24 (2024.01)
CPC B64D 27/02 (2013.01) [B60L 50/40 (2019.02); B60L 50/50 (2019.02); B64C 29/00 (2013.01); B64D 27/04 (2013.01); B64D 27/10 (2013.01); B64D 27/24 (2013.01); B60L 2200/10 (2013.01); B60L 2210/30 (2013.01); B60L 2210/40 (2013.01); B64D 27/026 (2024.01); B64D 2221/00 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A hybrid propulsion system for a vertical take-off and landing aircraft comprising:
two energy branches, each having a combustion engine driving an electricity generator and at least one electrical energy storage assembly associated with each electricity generator,
a plurality of electric motors actuating a same plurality of rotors providing together the propulsion and/or the lift of the hybrid VTOL aircraft, and
an electrical power and distribution unit supplying power to the plurality of electric motors from the electricity generators and/or from the electrical energy storage assemblies according to a pre-established flight phase,
wherein the two energy branches have an asymmetric configuration and each supply power selectively, by means of the electrical power and distribution unit, all or part of the plurality of electric motors and in that the electricity generators of the combustion engines have between them a power ratio comprised between 1.2 and 1.4 so as to allow the more powerful to supply alone the electrical power required for the aircraft in all flight conditions, wherein an additional electrical energy storage assembly supplies a determined power corresponding to the power delivered by one of the electricity generators and is configured to reactivate one of the electricity generators.