IN aircraft construction, until about fifteen years ago, the customary static method of stressing generally also provided for an adequate fatigue strength. This does not now apply for various reasons (e.g. increased flight speeds, use of high-strength materials with changed fatigue properties). It is, therefore, necessary to establish design rules which take account of more recent knowledge; which variables are to be specially considered, and what their importance is in a particular case, becomes clear from fatigue tests which, to a considerable extent, cater for the peculiar loading conditions of flight (service endurance tests or programme-loading tests). The principle of these tests was established in the DVL (1938 to 1941) and it is now in general use in automobile design for determining the relation between fatigue strength and endurance (life function) as in many cases of service failures a very good agreement with these tests can be observed.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    The Problem of Fatigue Strength in Aircraft Structures


    Subtitle :

    A Survey with Recommendations for Design Rules based on Recent Research


    Contributors:

    Published in:

    Publication date :

    1956-07-01


    Size :

    7 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



    Problem of fatigue strength in aircraft structures

    Gassner, E. | Engineering Index Backfile | 1956


    Fatigue in aircraft structures

    Barrois, W. | Engineering Index Backfile | 1955


    Fatigue of aircraft structures

    Walker, P.B. | Engineering Index Backfile | 1949


    Fatigue of Aircraft Structures

    J. Schijve | NTIS | 1986


    Fatigue of aircraft structures

    Walker, P.B. | Engineering Index Backfile | 1949