During the start-up of a number of launch vehicles that include solid rocket motor (SRM), the ignition transient and acoustic environments are mitigated by the implementation of a water spray system located immediately below the SRM nozzle exit plane (NEP). For NASA’s Space Launch System (SLS), this water system is referred to as the Ignition Overpressure / Sound Suppression (IOP/SS) system. The SLS Induced Environments (IE) technical discipline conducted a comprehensive evaluation of the design and as-tested performance of the IOP/SS water that will operate underneath both Boosters during the Artemis I launch. As part of this evaluation, flow rates and imagery from a number of integrated launch pad / mobile launcher IOP/SS flow tests were studied. Additional insight was leveraged from the Shuttle heritage IOP/SS system that includes data and imagery from a number of Flight Readiness Firings (FRF) and water flow tests. Lastly, the IE study included a qualitive comparison of the Shuttle and SLS systems to the equivalent water flow systems for Titan and Atlas V and determined that the NASA water flow systems are substantially different than those supporting other launch vehicles.


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    Title :

    SLS Ignition Overpressure-Sound Suppression System Performance Evaluated Against Historical Configurations


    Contributors:

    Conference:

    2024 AIAA Science and Technology Forum and Exposition ; 2024 ; Orlando, FL, US


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    SLS Ignition Overpressure/Sound Suppression System Performance Evaluated Against Historical Configurations

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