Aircraft galley fitting assembly
AssigneeB/E Aerospace, Inc.
InventorsJeriel Binas Cunanan, Kevin Hedwhig Panaligan Generoso
Life of this patent
Estimating the term…
Abstract
An aircraft galley fitting assembly for attaching an aircraft galley structure to an aircraft structure, the fitting assembly comprising: a fitting panel arranged to be fixed to the aircraft structure and the aircraft galley structure; and a damping panel configured to be located between the fitting panel and the aircraft galley structure when assembled, wherein the damping panel comprises a plurality of convex protrusions extending from a first side of the damping panel.
Claims17
An aircraft galley fitting assembly for attaching an aircraft galley structure to an aircraft structure, the fitting assembly comprising:
- a fitting panel configured to be fixed to the aircraft structure and the aircraft galley structure, the fitting panel comprising one or more through-holes;
- and
- a damping panel configured to be located between the fitting panel and the aircraft galley structure when assembled, wherein the damping panel comprises a plurality of convex protrusions extending from a first side of the damping panel, wherein the damping panel comprises one or more through-holes configured to align with the one or more through-holes in the fitting panel to allow the fitting panel and the damping panel to be fixed to the aircraft structure using one or more fixings.
A method of attaching an aircraft galley structure to a portion of an aircraft structure;
- the method comprising:
- providing a fitting panel to attach the aircraft structure and the aircraft galley structure, the fitting comprising one or more through-holes;
- and
- providing a damping panel between the fitting panel and the aircraft galley structure, wherein the damping panel comprises a plurality of convex protrusions extending from a first side of the damping panel,
- wherein the damping panel comprises one or more through-holes configured to align with the one or more through-holes in the fitting panel to allow the fitting panel and the damping panel to be fixed to the aircraft structure using one or more fixings.
Dependencies are inferred from the claim text.