STP1111: Analysis of Oxygen Mechanical Impact Test Apparatuses and Methods

    deQuay, L
    Lead Mechanical Project Engineer, Component Test Facility Project Office, National Aeronautics and Space Administration, John C. Stennis Space Center, MS

    Scheuermann, PE
    Propulsion Test Engineer, Propulsion Test Operations, National Aeronautics and Space Administration, John C. Stennis Space Center, MS

    Pages: 39    Published: Jan 1991


    Abstract

    An independent analysis using theoretical calculations with nominal test chamber configuration geometries was performed to evaluate the effects of small and large variations in test apparatus chamber configurations, test chamber test pressures [446KPa to 69.07 MPa], and in preset initial striker pin positions [striker pin transmits mechanical impact energy from the test apparatus drop plummet to material test samples within the test chamber]. The effects evaluated were the total energy losses between the drop plummet energy impartation to striker pin and the striker pin energy impartation to the test sample of different given test apparatuses. These total energy loss effects directly determine whether or not a sufficient percentage of the drop plummet energy is in fact transmitted to the test sample during mechanical impact tests.

    Keywords:

    compatibility, ignition sensitivity, variations, repeatability, mechanical impact test, total energy losses, gap distance, delivered energy, adiabatic compression, adiabatic expansion, elastic modulus, coefficient of kinetic friction


    Paper ID: STP17759S

    Committee/Subcommittee: G04.01

    DOI: 10.1520/STP17759S


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