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Prediction Of Creep Effects In Aircraft Structures

Report Number: WADD TR 60-411 Part 2
Author(s): C. W. Alesch, B. Klein, and W. Robe
Corporate Author: Convair, A Division of General Dynamics Corporation Engineering Department
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1962-02
Pages: 218
Contract: AF 33(616)-6567
Project: 1367
Task: 14002
AD Number: AD0277163

Abstract:
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 methhtem n methods appear as linearizing approximations for creeprelations 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.

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