Patent ID: 11964752
Assignee: THE BOEING COMPANY
Field: Transport (Mechanical engineering)
Classification: CPC B  G | IPC B  G

Claim 14:
15. A method for reducing noise from a landing gear of an aircraft, the method comprising the steps of:
providing one or more acoustically treated landing gear doors, each acoustically treated landing gear door comprising:
a landing gear door having an acoustic treatment assembly integrated on an inner mold line of an interior side of the landing gear door, and extending within an interior cavity of the landing gear door, the acoustic treatment assembly comprising:
a core structure comprising:
a first side and a second side;
a plurality of core cells extending between the first side and the second side; and
a drainage system having a plurality of drainage paths interconnected between the plurality of core cells, the plurality of drainage paths coupled to one or more drainage exits located at one or more perimeter portions of the landing gear door;

an acoustic facesheet coupled atop the first side of the core structure, wherein a placard is printed on a portion of the acoustic facesheet using one of, a laser drilling process, and a sintering process, and wherein the placard has an exterior placard surface displaying markings that are legible, while maintaining a controlled porosity; and
a nonporous backsheet directly coupled between the second side of the core structure and a portion of the interior cavity of the landing gear door;

attaching the one or more acoustically treated landing gear doors to a fuselage of the aircraft;
opening the one or more acoustically treated landing gear doors during a takeoff phase, or a landing phase, of the aircraft, and deploying the landing gear of the aircraft; and
reducing the noise created by acoustic waves emanating from the landing gear, by absorbing the acoustic waves through the acoustic facesheet and the core structure of the acoustic treatment assembly, and reflecting the acoustic waves off the nonporous backsheet of the acoustic treatment assembly.