Fracture control procedures for aircraft structural integrity /
Howard A. Wood.

Description

Main Author

Wood, Howard A.

Related Names

Air Force Flight Dynamics Laboratory (U.S.)

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971.

Subjects

Fracture mechanics.
Brittleness.
Metals > Metals / Cracking.
Titanium alloys.
Aluminum alloys.
Quality control.
Airframes.

Summary

The report reviews the application of applied fracture mechanics in the design, analysis and qualification of aircraft structural systems. Recent service experiences are cited. Current trends in high strength materials application are reviewed with particular emphasis on the manner in which fracture toughness and structural efficiency may affect the material selection process. General fracture control procedures are reviewed in depth with specific reference to the impact of inspectability, structural arrangement and material on proposed analysis requirements for safe crack growth. The relative impact on allowable design stress is indicated by example. Design criteria, material and analysis requirements for implementation of fracture control procedures are reviewed together with limitation in current available data techniques. A summary of items which require further study and attention is presented.

Note

AD0731565 (from http://www.dtic.mil).
"July 1971."

Physical Description

ix, 76 pages : illustrations, figures, tables ; 28 cm.

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