Fatigue Analysis of an Aircraft Wing Spar Kansas State University

Format:

Conference/Event

Author/Creator:

Lease, Kevin, author.

Conference Name:

General, Corporate & Regional Aviation Meeting & Exposition (1999-04-20 : Wichita, Kansas, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1999

Summary:

During full body fatigue testing, an aircraft wing spar initiated a crack from a rivet hole and crack growth data was obtained unique to the test spectrum loading. Fatigue testing of the 7050-T73511 spar material was used to obtain crack growth rate data and variable amplitude fatigue crack growth tests were performed on specimens fabricated from the spar material. Calculated results were in excellent agreement with these experimental results. A layered analysis of the adhesively bonded spar showed that the stress intensity in the lower cap was approximately constant, independent of crack length. When the constant stress intensity is used in a variable amplitude fatigue crack growth analysis, there is good correlation between the predicted and observed crack growth rates

Notes:

Vendor supplied data

Publisher Number:

1999-01-1561

Access Restriction:

Restricted for use by site license