Accession Number:

ADA025365

Title:

Further Development of Reliability Analysis Application to Structural Fatigue Evaluation

Descriptive Note:

Final rept. 15 Feb 1974-15 Oct 1975

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WA

Personal Author(s):

Report Date:

1976-01-01

Pagination or Media Count:

102.0

Abstract:

Three parameter symmetric distributions have been investigated for application as a fatigue life distribution model. Maximum likelihood ML estimator, and simulation procedures for maximum variance unbiased estimates and confidence bounds have been developed for analysis of censored data. A technique for testing the hypothesis of two censored samples having a common parent population is also presented. The effect on airplane structural reliability resulting from differing levels of fatigue performance from nominally identical structures is discussed, and a preflaw model was developed and incorporated in a reliability analysis method. Parametric studies were conducted using the reliability method to obtain qualitative information on the impact and interaction in terms of structural reliabliity, of several variables such as preflaws, loads environment, material, structural configuration, and designed residual strength.

Subject Categories:

  • Aircraft
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE