STP345: Testing Materials in a Plasma Arc Under Simulated Re-Entry Conditions

    Hagan, M. A.
    North American Aviation, Inc., Los Angeles Division (Research and Development), Los Angeles, Ca.

    Martin, George
    North American Aviation, Inc., Los Angeles Division (Research and Development), Los Angeles, Ca.

    Pages: 15    Published: Jan 1963


    Abstract

    The problem of materials for re-entry vehicles is unique in that the design criteria by which a material was selected in the past is no longer sufficient. For example, strength versus temperature data, section modulus, and similar traditional structural properties are of limited value where a material must perform in environments approaching or at its softening point. Temperature gradients, thermal shock, chemical reactions, erosion rates, producibility, and other related properties now assume a much greater importance than ever before. The material requirement that must be determined at temperatures above 3000 F may be categorized as follows: (1) maintenance of structural integrity under aerodynamic loads, (2) thermal shock resistance, (3) ability to withstand large thermal gradients and (4) surface resistance against corrosion and erosion.


    Paper ID: STP45102S

    Committee/Subcommittee: F07.07

    DOI: 10.1520/STP45102S


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