This paper describes an experimental program undertaken to study the impact damage of laminated graphite/PEEK plates and cylinders subjected to particle impacts at velocities ranging from 3 to 7 km/s. This velocity range corresponds to that found in space due to impacting micrometeoroids and space debris (MOD). To assess this problem, impact tests were conducted at three facilities in the U.S., with most of the tests undertaken at the NASA Johnson Space Center in Houston, using their two-stage light gas guns. Aluminium spheres were fired at composite material targets using various diameters and velocities to determine the damage correlation with energy, laminate thickness and material properties. Flat plate targets were first investigated to establish damage thresholds, followed by tests on laminated cylinders characteristic of the robot arm structures being designed for the Space Station. This paper presents the results of these studies showing the correlations found in terms of impact crater size, front face total damage, rear face spallation damage and secondary damage resulting from the ejecta plume impacting the rear wall of the cylinder.


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    Title :

    Hypervelocity impact damage to composite materials


    Contributors:


    Publication date :

    1997


    Size :

    11 Seiten, 11 Bilder, 2 Tabellen, 3 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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