Abstract
Life estimates for aircraft structural components, which are subjected to repeated loads of varying amplitudes and frequencies, must be based on some cumulative damage hypothesis. Such a hypothesis enables the calculation of the endurance of the component under a more or less complicated load spectrum from the normal S-N curve.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
Bibliography
Miner, M. A.: J. appl. Mech. 12, A 159-A 164 (1946).
Schijve, J. and F. A. Jacobs: NLL (Nat. aeronaut. Res. Inst.) Rep. (Amsterdam) M 1982 (1955).
Hartman, A. and G. C. Dtjijn: NLL (Nat. aeronaut. Res. Inst.) Rep. (Amsterdam) M 1857 (1952).
Hartman, A.: NLL (Nat. aeronaut. Res. Inst.) Rep. (Amsterdam) M 1923 (1953).
Schijve, J. and F. A. Jacobs: NLL (Nat. aeronaut. Res. Inst.) Rep. (Amsterdam) M 1970 and M 1974 (1954/1955) (Restricted).
Peterson, R. E.: Stress Concentration Design Factors, New York 1953.
Lepson, C. L., G. C. Noll and L. S. Clock: Stress and Strength of Manufactured Parts, New York 1950.
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 1956 Springer-Verlag OHG., Berlin · Gottingen · Heidelberg
About this paper
Cite this paper
Plantema, F.J. (1956). Some investigations on cumulative damage. In: Weibull, W., Odqvist, F.K.G. (eds) Colloquium on Fatigue / Colloque de Fatigue / Kolloquium über Ermüdungsfestigkeit. IUTAM Symposia. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-99854-6_24
Download citation
DOI: https://doi.org/10.1007/978-3-642-99854-6_24
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-99856-0
Online ISBN: 978-3-642-99854-6
eBook Packages: Springer Book Archive