# US 7,607,614 B2 · Transition shim between structure for fastening a wing to a fuselage of an aircraft, and aircraft having such a shim

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- Number: US 7,607,614 B2
- Document ID: US7607614B2
- Status: Granted
- Kind: B2
- Application number: 11/114,659
- Filed: 2005-04-26
- Published: 2005-11-10
- Granted: 2009-10-27
- Earliest claimed: 2004-05-04
- Assignees: Airbus France
- Inventors: François Rouyre
- Web page: https://patentgrep.com/patent/US7607614B2

## CPC

- B64C 7/00: Structures or fairings not otherwise provided for
- B64D 29/06: Attaching of nacelles, fairings or cowlings
- B64C: AEROPLANES; HELICOPTERS
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT

## Abstract

A shim adapted for positioning on the upper surface of at least one wing of an aircraft. The shim restores an aerodynamic profile of the wing at the position of a zone of transition between structure fastening the wing to the fuselage of the aircraft and the upper surface of the aircraft. The shim enables a seal to run from the fastening structure to the upper surface of the wing, in eliminating the zones at which the seal may break open. An aircraft provided with such a shim is also disclosed.

## Claims

### Claim 1

An aircraft comprising:
a fuselage;
an airfoil comprising two wings fixed on either side of the fuselage, each wing being operably coupled to the fuselage by a fastening structure, the fastening structure forming a reinforcement at least one of an upper surface or a lower surface of the wing;
a ventral fairing fixed to a lower part of the fuselage, the ventral fairing comprising a base and two panels extending radially relative to the base and rising laterally along the fuselage, each panel being provided with structure defining an opening for receiving a wing therethrough;
a seal fixed to a periphery of each opening, the seal being at least partially positioned between an internal wall of the opening and the wing, wherein the seal is subjected to a difference in height along a transition zone defined between the fastening structure and the wing;
wherein the aircraft includes, on at least one wing, a transition shim positioned in the transition zone between the fastening structure and the wing, a thickness of the shim decreasing from an edge of the fastening structure to the wing corresponding to the difference in height along the transition zone, thereby defining a slope of the shim, and wherein a profile of the shim restores an aerodynamic profile of the wing in the transition zone.

### Claim 2 (depends on 1)

An aircraft according to claim 1, wherein the slope is configured such that a rate of compression of at a first part of the seal between the fastening structure and the internal wall of the opening and at a second part of the seal between the wing and the internal wall of the opening is uniform.

### Claim 3 (depends on 1)

The aircraft according to claim 1, wherein the shim is positioned on an upper surface of the wing.

### Claim 4 (depends on 1)

The aircraft according to claim 1, wherein the shim is positioned on a lower surface of the wing.

### Claim 5 (depends on 1)

The aircraft according to claim 1, wherein the shim comprises an expanded plastic material.

### Claim 6 (depends on 1)

The aircraft according to claim 1, wherein the shim is adhered to the wing.

### Claim 7 (depends on 1)

The aircraft according to claim 1, wherein the shim is fitted with rounded ridges.

### Claim 8 (depends on 1)

The aircraft according to claim 1, wherein at least a portion of an external surface of the shim is coated with sealant.

### Claim 9 (depends on 1)

The aircraft according to claim 1, wherein an external contour of the shim is adapted to fit an external contour of the fastening structure at a zone of contact between said shim and said fastening structure.