US 12,134,463 B2
Aircraft comprising a main landing gear compartment with a body which is produced in a single piece
Matthieu Plet, Toulouse (FR); Laurent Dubreuil, Colomiers (FR); Alain Prudent, Colomiers (FR); Xavier Matheis, Toulouse (FR); Gilles Andrieu, Colomiers (FR); and Damien Desgaches, Colomiers (FR)
Assigned to AIRBUS OPERATIONS SAS, Toulouse (FR)
Filed by Airbus Operations SAS, Toulouse (FR); and Airbus Atlantic SAS, Rochefort (FR)
Filed on Sep. 9, 2022, as Appl. No. 17/941,075.
Claims priority of application No. 2109585 (FR), filed on Sep. 13, 2021.
Prior Publication US 2023/0079075 A1, Mar. 16, 2023
Int. Cl. B64C 25/14 (2006.01); B64C 25/04 (2006.01)
CPC B64C 25/14 (2013.01) [B64C 25/04 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An aircraft comprising a fuselage with a longitudinal direction as well as a vertical median plane, and comprising, from the front to the rear,
a central wing spar,
a main landing gear compartment,
a section of the fuselage,
the main landing gear compartment comprising
a rear transverse wall connected to the section of fuselage which is positioned at the rear of the main landing gear compartment,
a base wall which is connected to the central wing spar,
the rear transverse wall and the base wall forming a sealed barrier between a first, pressurized area and a second, non-pressurized area,
the aircraft comprising a ventral beam which passes through the main landing gear compartment;
wherein the main landing gear compartment comprises:
a body, produced in a single piece from composite material, separating the first, pressurized area and the second, non-pressurized area, said body comprising
a first part corresponding to the base wall,
a second part corresponding to the rear transverse wall,
an inner face which is oriented towards the second, non-pressurized area, and
an outer face which is oriented towards the first, pressurized area;
at least two longitudinal beams made of composite material, at least in part oriented parallel to the longitudinal direction and connected to the body; and
bolster beams which assure a continuity of the ventral beam, the bolster beams being positioned in-line with the longitudinal beams, and being connected to the ventral beam, to the section of fuselage, as well as to the body.