This work adapts manufacturing and metrology industry standards to create a risk-based approach for the determination of electric propulsion performance specifications. The developed process is applied to 208 total thrust measurements acquired using three different NASA Hall Effect Rocket with Magnet Shielding (HERMeS) Technology Demonstration Unit (TDU) 12.5-kW Hall thrusters in three different test facilities in order to generate thrust specifications at the 300 V/6.25 kW, 400 V/8.33 kW, 500 V/10.42 kW, and 600 V/12.5 kW operating conditions. These thrust specifications are used to perform a set of sample acceptance tests to illustrate the importance of adding additional conservatism using a parameter known of the Test Accuracy Ratio in order to control the risk to the thruster producer and consumer from false rejection and acceptance of thruster units.


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    Title :

    Risk-based Methodology for the Determination of Hall Thruster Performance Specifications


    Contributors:

    Conference:

    2021 AIAA Propulsion and Energy Forum ; 2021 ; Virtual, US


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Risk-based Methodology for the Determination of Hall Thruster Performance Specifications

    J. D. Frieman / J. Mackey / H. Kamhawi et al. | NTIS | 2021


    RISK-BASED METHODOLOGY FOR THE DETERMINATION OF HALL THRUSTER PERFORMANCE SPECIFICATIONS

    Frieman, Jason D. / Mackey, Jon / Kamhawi, Hani et al. | TIBKAT | 2021


    Risk-Based Methodology for the Determination of Hall Thruster Performance Specifications

    J. D. Frieman / J. Mackey / H. Kamhawi et al. | NTIS | 2021



    Risk-based Methodology for the Determination of Hall Thruster Performance Specifications

    Frieman, Jason D. / Mackey, Jon / Kamhawi, Hani et al. | AIAA | 2021