The significance of cladding for fatigue of aluminium alloys in aircraft structures

Report (1976)

Authors

J. Schijve

F.A. Jacobs

P.J. Tromp

Corrosion Cracks Crack propagation Cladding Crack initiation Protective coatings Gust loads Fatigue tests Airframe materials S-N diagrams Cyclic loads Flight-simulation Aluminiajm alloys Perforated plates Metal coatings Aluminium coatings

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Published Date

05-09-1976

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Source:

NLR-TR 76065 U

Abstract

Flight-simulation tests were carried out on sheet specimens notched "by an open hole (Kt = 2.66). The material was 2024-T3 in three conditions; Alclad, bare and chemically milled. The crack initiation period and the crack propagation period were considerably shorter for the Alclad material. The significance of the cladding, both for constant-amplitude loading and variable-amplitude loading, is analysed. Information from the literature is summarized. Practical aspects for aircraft application are indicated.

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