TRANSITION FITTING FOR HIGH STRENGTH COMPOSITE
Assignee
BOEING COMPANY
Filed
Jun 7, 1984
Granted
Oct 16, 1990
Location
SEATTLE WA US
Abstract
A transition fitting (16) for a high strength composite article (10) comprised of a matrixed skin (12) supported by and bonded to a core (14) to locate the same in an intended structural disposition subjecting the composite and fitting at or about a juncture thereof to bending and/or shear loads, comprising a profiled web (22) disposed within the composite article and a shank for fixturing the article, wherein the web includes a longitudinal aspect projecting into the core from the juncture to a tip of the web (26), a lateral aspect projecting across the core bounding the juncture, and a transverse aspect extending through the core; wherein the transverse aspect of the web tapers inwardly along the longitudinal direction of the web toward the tip and is dimensioned to provide load distribution to transfer structural loads from the composite to the fitting along a longitudinal force gradient having a minimum force value at the tip and a maximum force value at the shank, and yet further wherein the lateral aspect is dimensioned to yield a web surface area selected to provide force balancing for maintaining loads transferred to the web along the gradient below the interfacial shear limits at the junctures of the fitting, the core and the skin.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 1, 1985
Rescinded
May 5, 1989
Duration
4 years
Inventor
- 1JOHN S. PERRY
Record Details
- Patent number
- US 4962904
- Application
- 06618566
- Aerospace match
- No
- Dataset source
- 35 USC §181 SO records