US 12,103,693 B2
System for managing energy for an aircraft with a hybrid power source comprising at least one rechargeable electricity source and one electricity generating source
Clément Dinel, Toulouse (FR); and Marion Marduel, Toulouse (FR)
Assigned to ASCENDANCE FLIGHT TECHNOLOGIES, Toulouse (FR)
Appl. No. 18/290,149
Filed by ASCENDANCE FLIGHT TECHNOLOGIES, Toulouse (FR)
PCT Filed May 10, 2022, PCT No. PCT/FR2022/050892
§ 371(c)(1), (2) Date Nov. 9, 2023,
PCT Pub. No. WO2022/238653, PCT Pub. Date Nov. 17, 2022.
Claims priority of application No. 2104948 (FR), filed on May 10, 2021.
Prior Publication US 2024/0262521 A1, Aug. 8, 2024
Int. Cl. B64D 31/18 (2024.01); B60L 50/61 (2019.01); B64D 27/33 (2024.01)
CPC B64D 31/18 (2024.01) [B60L 50/61 (2019.02); B64D 27/33 (2024.01); B60L 2200/10 (2013.01); B64D 2221/00 (2013.01)] 6 Claims
OG exemplary drawing
 
1. An energy management system for an aircraft with a hybrid power source comprising at least one rechargeable electricity source and at least one electricity generating source, the energy management system comprising:
a detector configured to determine, on the one hand, status data indicating a status of elements of a power consumption electrical circuit of an aircraft controlled by the energy management system, and on the other hand power data relating to (i) an instantaneous electrical power demanded by the aircraft and/or (ii) a charging status of rechargeable electricity sources of the aircraft,
an automaton configured to receive the power data from the detector and to determine a control status of the power sources, the automaton comprising at least three statuses in the group comprising:
a buffer status in which a demanded instantaneous electrical power is lower than a capacity of the at least one electricity generating source and is supplied thereby,
a charging status in which the demanded instantaneous electrical power is lower than the capacity of the at least one electricity generating source and is entirely supplied by the at least one electricity generating source, and wherein the one or more electricity generating source produces a surplus of power used to recharge the at least one rechargeable electricity source,
a turbo status in which the demanded instantaneous electrical power is higher than the capacity of the at least one electricity generating source, and wherein the at least one rechargeable electricity source supplies a complement required to reach the demanded instantaneous electrical power,
an adapter configured to receive the status data and to determine a backup electrical configuration when the status data indicate a failure,
a controller configured to receive status information of the automaton and to determine an electrical control for the at least one rechargeable electricity source and the at least one electricity generating source according to the demanded instantaneous electrical power,
a switch configured to emit controls to the switches of the power consumption electrical circuit of the aircraft controlled by the energy management system to implement a nominal electrical configuration, or, in case of reception of a backup electrical configuration of the adapter, the backup electrical configuration,
the controller being configured to receive the backup electrical configuration of the adapter when a failure is detected, and to control an extinction of one or more element of the power consumption electrical circuit of the aircraft controlled by the energy management system according to the backup electrical configuration.