US 12,291,340 B2
Propulsion unit with propeller and electric motor comprising an adapted primary structure, and aircraft having at least one such propulsion unit
Pascal Pome, Toulouse (FR); Nicolas Jolivet, Toulouse (FR); Rémi Amargier, Toulouse (FR); Lionel Czapla, Toulouse (FR); Franck Alvarez, Toulouse (FR); Kotaro Fukasaku, Toulouse (FR); Benoît Penven, Toulouse (FR); Delphine Jalbert, Blagnac (FR); Laurent Lafont, Blagnac (FR); Milan Tasic, Toulouse (FR); Frédéric Goupil, Toulouse (FR); Jean-Victor Lapeyre, Marignane (FR); and Emmanuel Mermoz, Marignane (FR)
Assigned to AIRBUS OPERATIONS SAS, Toulouse (FR); and AIRBUS SAS, Blagnac (FR)
Filed by Airbus Operations SAS, Toulouse (FR); and Airbus SAS, Blagnac (FR)
Filed on Jun. 27, 2022, as Appl. No. 17/849,895.
Claims priority of application No. 2106993 (FR), filed on Jun. 29, 2021.
Prior Publication US 2022/0411084 A1, Dec. 29, 2022
Int. Cl. B64D 27/40 (2024.01); B64D 27/30 (2024.01)
CPC B64D 27/40 (2024.01) [B64D 27/30 (2024.01); B64D 27/402 (2024.01)] 16 Claims
OG exemplary drawing
 
1. A propulsion unit comprising:
at least one electric motor,
a propeller exhibiting an axis of rotation,
at least one intermediate element interposed between the motor and the propeller and configured to transmit at least thrust loads generated by the propeller, and
a primary structure supporting the propulsion unit,
wherein the propulsion unit comprises at least one interface comprising:
a first load path, configured to transmit loads that act mainly perpendicular to the axis of rotation of the propeller, linking the intermediate element or one of the intermediate elements to a support linked rigidly to or incorporated in the primary structure, and
a second load path, configured to transmit loads that act mainly parallel to the axis of rotation of the propeller, linking the intermediate element or one of the intermediate elements to the support linked rigidly to or incorporated in the primary structure,
wherein the second load path comprises at least two connecting rods which converge toward the axis of rotation of the propeller and each of which forms an angle of between 20° and 70° with the axis of rotation of the propeller.