Research/Patents/US 4962904
US 4962904

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Rescinded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

Browse by Assignee

BOEING COMPANY
Back to patent indexSource: USPTO 35 USC §181 secrecy order records