US 12,071,250 B2
Electric architecture for hybrid propulsion
Philippe Delbosc, Blagnac (FR); Anne Lienhardt, Moissy-Cramayel (FR); Clement Dupays, Moissy-Cramayel (FR); Christophe Viguier, Moissy-Cramayel (FR); and Sonia Dhokkar, Blagnac (FR)
Assigned to SAFRAN, Paris (FR); SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN ELECTRICAL & POWER, Blagnac (FR)
Appl. No. 17/282,549
Filed by SAFRAN, Paris (FR); SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN ELECTRICAL & POWER, Blagnac (FR)
PCT Filed Oct. 1, 2019, PCT No. PCT/FR2019/052322
§ 371(c)(1), (2) Date Apr. 2, 2021,
PCT Pub. No. WO2020/070438, PCT Pub. Date Apr. 9, 2020.
Claims priority of application No. 1859208 (FR), filed on Oct. 4, 2018.
Prior Publication US 2021/0347491 A1, Nov. 11, 2021
Int. Cl. B64D 27/24 (2024.01); B64D 27/02 (2006.01); H02J 1/14 (2006.01); H02J 7/34 (2006.01)
CPC B64D 27/24 (2013.01) [H02J 1/14 (2013.01); H02J 7/345 (2013.01); B64D 27/026 (2024.01); H02J 2310/44 (2020.01)] 14 Claims
OG exemplary drawing
 
1. An aircraft with hybrid thermal/electrical propulsion comprising:
a turbomachine,
a first electrical source,
a second electrical source equipped with electrical energy storage means,
a non-propulsion electrical distribution network,
a low-voltage electrical distribution network,
a propulsion electrical distribution network, the three electrical distribution networks being electrically supplied by the first and second electrical sources and electrically interconnected by static converters,
a main electrical system mounted in the body of the aircraft, and
for the turbomachine of the aircraft, a local electrical system mounted in the turbomachine.