Prediction of creep effects in aircraft structures.
Part 2 /
C.W. Alesch, B. Klein, and W. Robe.

Description

Main Author

Alesch, C. W.

Related Names

Robe, W., author.
Klein, B., author.
United States. Air Force.
Air Force Flight Dynamics Laboratory (U.S.)
General Dynamics Corporation. Convair Division

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962.

Subjects

Airframes.
Materials > Materials / Creep.
Metals > Metals / Creep.

Summary

The method presented in WADD TR 60-411 Part I for predicting deformations in aircraft structures undergoing creep is reviewed. A simplified version of the original method is presented. Box beam tests were used to investigate the simplified method. The outcome of these tests indicated the accuracy of the method in predicting deformations in aircraft structures undergoing creep was in the same order of accuracy as that usually experienced in redundant analysis procedures. The power law for expressing creep relations is found redundant in solution. Its usefulness appears chiefly in the display of creep test data. Current creep prediction methods appear as linearizing approximations for creep-relations with the result that inaccuracies in predicting very long and very short creep life restrict their usefulness. An approach to creep prediction based on creep-rupture history for establishment of creep laws is proposed. Relationships between tension - and creep - test data are examined experimentally with respect to single and repetitive load applications. A general approach to creep prediction in all metallic materials appears improbable.

Note

"February 1962."

Physical Description

xiii, 218 pages : illustrations ; 28 cm

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