Stress-relieving joint between materials with differing coefficients of thermal expansion
AssigneeRohr, Inc.
InventorMichael Sean Pretty
Life of this patent
Estimating the term…
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.
Claims12
A joint comprising:
- a composite bond panel having a first coefficient of thermal expansion;
- a 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 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.
2-4. (canceled)
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;
- and
- a first plurality of fasteners coupling the aluminum hinge beam to the composite bond panel.
13-14. (canceled)
Dependencies are inferred from the claim text.