Aircraft structure arrangement

Patent metadata

Field	Value
Publication number	US-9499250-B2
Application number	US-201314083541-A
Country	US
Kind code	B2
Filing date	Nov 19, 2013
Priority date	Nov 20, 2012
Publication date	Nov 22, 2016
Grant date	Nov 22, 2016

Abstract

An aircraft structure arrangement which is in particular suitable to form a part of a secondary structure of an aircraft comprises a first longitudinal profile and a first frame profile. The aircraft structure arrangement further comprises a mounting bracket which is directly attached to both, the first longitudinal profile and the first frame profile. The mounting bracket further is connectable to a component of a primary structure of the aircraft so as to fasten the first longitudinal profile and the first frame profile to the primary structure of the aircraft.

First claim

The invention claimed is:

1. An aircraft structure arrangement forming a part of a secondary structure of an aircraft and which comprises:
a first longitudinal profile,
a first frame profile, and
a mounting bracket,

wherein the mounting bracket is directly attached to both the first longitudinal profile and the first frame profile, and wherein the mounting bracket further is connectable to a component of a primary structure of the aircraft so as to fasten the first longitudinal profile and the first frame profile to the primary structure of the aircraft, wherein the mounting bracket comprises a plurality of attachment portions, each attachment portion serving to attach the mounting bracket to a respective longitudinal profile or frame profile, wherein the number of attachment portions formed on the mounting bracket is adapted to the number of longitudinal and frame profiles attached to the mounting bracket, further comprising at least one of
a second frame profile, wherein the mounting bracket is directly attached to the second frame profile, and
a second longitudinal profile, wherein the mounting bracket is directly attached to the second longitudinal profile.

2. The aircraft structure arrangement according to claim 1 , wherein the mounting bracket comprises a base portion and a connection portion, the connection portion extending from a plane defined by the base portion and comprising a fastening device for fastening the mounting bracket to the component of the primary structure of the aircraft.

3. The aircraft structure arrangement according to claim 1 , further comprising a connecting element for connecting the mounting bracket to the component of the primary structure of the aircraft, the connecting element being connected to a connection portion of the mounting bracket.

4. The aircraft structure arrangement according to claim 1 , wherein at least one of
each attachment portion extends from the base portion of the mounting bracket in a direction of the respective longitudinal and frame profile attached to the attachment portion, and
an orientation of the attachment portion relative to the base portion of the mounting bracket is adjusted to an orientation of the respective longitudinal and frame profile attached to the attachment portion relative to the base portion of the mounting bracket.

5. The aircraft structure arrangement according to claim 1 , wherein at least one attachment device is provided in the region of each attachment portion of the mounting bracket, the attachment device extending through a bore formed in the respective longitudinal and frame profile attached to the attachment portion.

6. A method of mounting an aircraft structure arrangement to form a part of a secondary structure of an aircraft, the method comprising:
providing a first longitudinal profile,
providing a first frame profile,
directly attaching a mounting bracket to both, the first longitudinal profile and the first frame profile, and
connecting the mounting bracket to a component of a primary structure of the aircraft so as to fasten the first longitudinal profile and the first frame profile to the primary structure of the aircraft, wherein each longitudinal or frame profile is attached to a respective attachment portion of the mounting bracket, wherein the number of attachment portions formed on the mounting bracket is adapted to the number of longitudinal and frame profiles attached to the mounting bracket, further comprising at least one of:
providing a second frame profile, and directly attaching the mounting bracket to the second frame profile, and
providing a second longitudinal profile, and directly attaching the mounting bracket to the second longitudinal profile.

7. The method according to claim 6 , wherein at least one of:
the mounting bracket is fastened to the component of the primary structure of the aircraft via of a fastening device, the fastening device being formed on a connection portion of the mounting bracket extending from a plane defined by a base portion of the mounting bracket, and
the mounting bracket is fastened to the component of the primary structure of the aircraft by means of a connecting element, the connecting element being connected to the connection portion of the mounting bracket.

8. The method arrangement according to claim 6 , wherein at least one of
each longitudinal and frame profile is attached to a respective attachment portion of the mounting bracket, wherein the attachment portion extends from the base portion of the mounting bracket in a direction of the respective longitudinal and frame profile attached to the attachment portion, and
each longitudinal and frame profile is attached to a respective attachment portion of the mounting bracket, wherein an orientation of the attachment portion relative to the base portion of the mounting bracket is adjusted to an orientation of the respective longitudinal and frame profile attached to the attachment portion, relative to the base portion of the mounting bracket.

9. The method according to claim 6 , wherein each longitudinal and frame profile is attached to a respective attachment portion of the mounting bracket by means of at least one attachment device provided in the region of the attachment portion, the attachment device extending though a bore formed in the respective longitudinal and frame profile attached to the attachment portion.

10. An aircraft structure system comprising a plurality of aircraft structure arrangements according to claim 1 .

Assignees

• Airbus Operations Gmbh

Inventors

• Engmann Joern
• Neumann Juergen
• Penski Gerhard

Classifications

• B64C1/06 Primary

  Frames; Stringers; Longerons {; Fuselage sections} · CPC title

• B64C1/066 Primary

  Interior liners · CPC title

• Y02T50/46

  Cross-Sectional Technologies · mapped topic

• Y10T29/49622

  Vehicular structural member making · CPC title

• Y02T50/40

  Weight reduction · CPC title