Load transfer apparatus for transferring loads in an aircraft structure

Patent metadata

Field	Value
Publication number	US-2016272297-A1
Application number	US-201615072399-A
Country	US
Kind code	A1
Filing date	Mar 17, 2016
Priority date	Mar 17, 2015
Publication date	Sep 22, 2016
Grant date	—

Abstract

An aircraft wing comprising a load transfer apparatus arranged to transfer transverse shear loads from a first component such as a wing skin to a second, adjacent component such as a wing skin. The apparatus comprises a master interlock, and a plurality of slave interlocks. Each master interlock comprises a master male member received in a master female member to form the master interlock. Each of the plurality of slave interlocks comprises a slave male member received in a corresponding female member to form the slave interlocks. The master male and female members are sufficiently stiff that the master male member and the master female member are fixed, whereas the slave male and/or female members are less stiff than the master male and female members such that the slave male and/or female members are able to tolerate some movement, in the transverse direction.

First claim

1 . An aircraft wing comprising a load transfer apparatus arranged to transfer transverse shear loads from a first wing skin to a second, adjacent, wing skin, the apparatus comprising a master interlock, and a plurality of slave interlocks,
the master interlock comprising a master male member associated with the first or second wing skin, received in a master female member associated with the other of the first or second wing skin, to form the master interlock, and each of the plurality of slave interlocks comprising a slave male member associated with the first or second wing skin, received in a corresponding female member associated with the other of the first or second wing skin, to form the slave interlocks, wherein the master male and female members are sufficiently stiff that the master male member and the master female member are fixed relative to their respective first and second wing skin, whereas each slave male member is less stiff than the master male member such that the slave male members are able to tolerate some movement, in the transverse direction, thereby enabling both the slave interlocks and the master interlock to transfer some of the transverse shear loads between the wing skins even when there is play in the master interlock.

2 . A wing according to claim 1 , wherein the master and slave male members are all associated with the first wing skin, and the master and slave female members are all associated with the second wing skin.

3 . A wing according to claim 1 wherein the female slave members are sufficiently stiff that they are fixed to their respective wing skin.

4 . A wing according to claim 1 , wherein the slave members each comprise a necked region configured to reduce the stiffness of the slave members relative to the master male member.

5 . A wing according to claim 1 , wherein the male members each comprise a tapered region for insertion in a corresponding tapered region of the respective female member.

6 . A wing according to claim 5 , wherein each male member comprises two opposing transverse tapering surfaces that are configured, in the interlock, to abut two corresponding transverse tapering surfaces of the respective female member.

7 . A wing according to claim 1 , wherein the load transfer apparatus comprises a plurality of the master interlocks and a multiplicity of the slave interlocks.

8 . An aircraft comprising the aircraft wing of claim 1 .

9 . An aircraft according to claim 8 , wherein the wing comprises an inner wing and a wing tip device at the tip of the inner wing, the wing tip device being configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced.

10 . An aircraft according to claim 9 , wherein the first or second wing skin is on the wing tip device, and the other of the first and second wing skin is on the inner wing.

11 . An aircraft according to claim 8 , wherein the wing skins are wing skins on the lower surface of the wing.

12 . A load transfer apparatus for use as the load transfer apparatus in claim 1 , the apparatus comprising a master interlock, and a plurality of slave interlocks,
the master interlock comprising a master male member for associating with a first or second wing skin, and a master female member for receiving the master male member and for being associated with the other of the first or second wing skin, to form the master interlock, and each of the plurality of slave interlocks comprising a slave male member for associating with the first or second wing skin, and a corresponding female member for receiving the slave male member and for being associated with the other of the first or second wing skin, to form the slave interlocks, wherein the master male and female members are sufficiently stiff that the master male member and the master female member are fixable relative to their respective first and second wing skin, whereas each slave male member is less stiff than the master male member such that the slave male members are able to tolerate some movement, in the transverse direction, thereby enabling both the slave interlocks and the master interlock to transfer some of the transverse shear loads between the wing skins even when there is play in the master interlock.

13 . A method of designing a load transfer apparatus for transferring transverse shear loads from a first wing skin to a second, adjacent, wing skin, the apparatus comprising a master interlock, and a plurality of slave interlocks,
the master interlock comprising a master male member for associating with the first or second wing skin, and a master female member for receiving the master male member and for being associated with the other of the first or second wing skin, to form the master interlock, and each of the plurality of slave interlocks comprising a slave male member for associating with the first or second wing skin, and a corresponding female member for receiving the slave male member and for being associated with the other of the first or second wing skin, to form the slave interlocks, wherein the master male and female members are sufficiently stiff that the master male member and the master female member are fixable relative to their respective first and second wing skin, and wherein the method comprises the step of:
designing each slave male member to be less stiff than the master male member, the stiffness being selected such that the slave male members are able to tolerate some movement, in the transverse direction, thereby enabling both the slave interlocks and the master interlock to transfer some of the transverse shear loads between the wing skins even when there is play in the master interlock.

Assignees

• Airbus Operations Ltd

Inventors

• Thompson Robert Ian

Classifications

• B64C3/26 Primary

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/56 Primary

  Folding or collapsing to reduce overall dimensions of aircraft · CPC title

• F16B5/0012

  a tongue on the edge of one sheet, plate or panel co-operating with a groove in the edge of another sheet, plate or panel · CPC title