Stress-relieving joint between materials with differing coefficients of thermal expansion

Patent metadata

Field	Value
Publication number	US-9499275-B2
Application number	US-201414516362-A
Country	US
Kind code	B2
Filing date	Oct 16, 2014
Priority date	Oct 16, 2014
Publication date	Nov 22, 2016
Grant date	Nov 22, 2016

Abstract

A composite component may be coupled to an aluminum component with a plurality of fasteners. An expansion strap may be located between the composite component and the aluminum component. The expansion strap may have a coefficient of thermal expansion which is greater than the coefficient of thermal expansion of the composite component, and less than the coefficient of thermal expansion of the aluminum component. A first set of fasteners may be inserted through the composite component, the expansion strap, and the aluminum component. A second set of fasteners may be inserted through the composite component and the expansion strap. The expansion strap may decrease stress in the composite component at the fastener locations.

First claim

I claim:

1. A joint comprising:
a composite bond panel having a first coefficient of thermal expansion;
a titanium expansion strap in contact with the composite bond panel, the titanium expansion strap having a second coefficient of thermal expansion, wherein the second coefficient of thermal expansion is greater than the first coefficient of thermal expansion;
an aluminum hinge beam in contact with the titanium expansion strap, the aluminum hinge beam having a third coefficient of thermal expansion, wherein the third coefficient of thermal expansion is greater than the second coefficient of thermal expansion; and
a first plurality of fasteners coupling the composite bond panel, the titanium expansion strap, and the aluminum hinge beam together, wherein the titanium expansion strap is located between the composite bond panel and the aluminum hinge beam, and wherein the first plurality of fasteners pass through the composite bond panel, the titanium expansion strap, and the aluminum hinge beam.

2. The joint of claim 1 , further comprising a second plurality of fasteners, wherein the second plurality of fasteners couple the composite bond panel to the titanium expansion strap, and wherein the second plurality of fasteners pass through the composite bond panel and the titanium expansion strap.

3. The joint of claim 1 , wherein the composite bond panel comprises a nacelle component for an aircraft.

4. The joint of claim 1 , wherein the first plurality of fasteners comprise at least one of a bolt or a rivet.

5. The joint of claim 1 , wherein the titanium expansion strap is configured to decrease a bearing load on the composite bond panel.

6. An aircraft nacelle comprising:
an aluminum hinge beam;
a composite bond panel;
a titanium expansion strap located between the aluminum hinge beam and the composite bond panel, wherein the titanium expansion strap is in contact with the aluminum hinge beam and the composite bond panel; and
a first plurality of fasteners coupling the composite bond panel, the titanium expansion strap, and the aluminum hinge beam together, wherein the titanium expansion strap is located between the composite bond panel and the aluminum hinge beam, and wherein the first plurality of fasteners pass through the composite bond panel, the titanium expansion strap, and the aluminum hinge beam.

7. The aircraft nacelle of claim 6 , wherein a coefficient of thermal expansion of the titanium expansion strap is greater than a coefficient of thermal expansion of the composite bond panel and less than a coefficient of thermal expansion of the aluminum hinge beam.

8. The aircraft nacelle of claim 6 , further comprising a second plurality of fasteners coupling the composite bond panel to the titanium expansion strap.

9. The aircraft nacelle of claim 6 , wherein the titanium expansion strap is configured to reduce a bearing load on the composite bond panel.

10. The aircraft nacelle of claim 6 , wherein the composite bond panel is configured to withstand a bearing load from the aluminum hinge beam at a temperature of at least 300° C.

Assignees

• Rohr Inc

Inventors

• Pretty Michael Sean

Classifications

• B64D29/02

  associated with wings · CPC title

• B64D29/06 Primary

  Attaching of nacelles, fairings or cowlings · CPC title

• B29C66/524

  Joining profiled elements · CPC title

• B29C66/1122

  Single lap to lap joints, i.e. overlap joints (B29C66/45, B29C66/472, B29C66/52272 take precedence) · CPC title

• B29C66/721

  Fibre-reinforced materials (B29C66/729 takes precedence) · CPC title