US 12,291,341 B2
Compact electric propulsion unit comprising a statically determinate engine mount, and aircraft comprising at least one such electric propulsion unit
Rémi Amargier, Toulouse (FR); and Kotaro Fukasaku, Toulouse (FR)
Assigned to Airbus Operations SAS, Toulouse (FR)
Filed by Airbus Operations SAS, Toulouse (FR)
Filed on Mar. 2, 2023, as Appl. No. 18/177,352.
Claims priority of application No. 2202124 (FR), filed on Mar. 11, 2022.
Prior Publication US 2023/0286664 A1, Sep. 14, 2023
Int. Cl. B64D 27/40 (2024.01); B64D 27/30 (2024.01)
CPC B64D 27/40 (2024.01) [B64D 27/30 (2024.01); B64D 27/406 (2024.01)] 15 Claims
OG exemplary drawing
 
1. A propulsion unit for an aircraft, the propulsion unit comprising:
a structure secured to the aircraft,
an electric motor,
a propeller driven in rotation by the electric motor and configured to generate thrusting forces which sustain flight,
a rigid casing configured to transmit the thrusting forces generated by the propeller, and
an engine mount connecting the rigid casing and the structure,
the propeller, which has an axis of rotation, defining a longitudinal direction parallel to the axis of rotation, a vertical longitudinal plane passing through the axis of rotation and which is vertical and a longitudinal and horizontal direction perpendicular to the vertical longitudinal plane,
wherein the engine mount comprises:
first and second transverse link rods positioned on each side of the vertical longitudinal plane and each having a first end connected by, at least, a first joint to the structure and a second end connected by, at least, a second joint to the rigid casing, each of the first and second joints having an axis of pivoting parallel to the axis of rotation,
first and second thrust rods positioned on each side of the vertical longitudinal plane and having a first end connected by a first thrust rod connection to the structure and a second end connected by a second thrust rod connection to the rigid casing, for each of the first and second thrust rods, the first and second thrust rod connections being separated from one another in the longitudinal direction, and,
a longitudinal end stop configured to limit a movement of the rigid casing with respect to the structure in at least the longitudinal direction.