THE STRUCTURAL RELIABILITY OF AIRFRAMES

Abstract

The theory of reliability estimation developed in previous reports (WADD TR61-53, ML-TDR-64-300) has been applied to three types of aircraft, a civilian transport, a heavy bomber and a fighter designed by current procedures, for which operational records, multiple structural tests and records of service experience are available. Failure rates for critical ultimate load conditions have been evaluated on the basis of data obtained from various sources and compared with service experience. Lives associated with equal risk of ultimate load failure and fatigue failure (or initial structural fatigue damage) have also been computed. The obtained numerical values which reflect current design practices can serve as the basis for a rational comparative reliability analysis of new designs involving new materials and different design criteria and missions psectra and profiles.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1964
Accession Number
AD0615654

Entities

People

  • A. M. Freudenthal
  • A. O. Payne

Organizations

  • Columbia University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Airframes
  • Bomber Aircraft
  • Design Criteria
  • Fatigue Life
  • Fighter Aircraft
  • Gust Loads
  • Load Distribution
  • Materials
  • Materials Laboratories
  • Military Aircraft
  • Normal Distribution
  • Probability Distributions
  • Standards
  • Transport Aircraft
  • United States

Readers

  • Calculus or Mathematical Analysis
  • Instructional Design and Training Evaluation.
  • Tribology (the study of the boundary interaction between sliding surfaces, lubrication, wear and friction).