The NASA Engineering and Safety Center initiated the Max Launch Abort System (MLAS) Project to investigate alternate crew escape system concepts that eliminate the conventional launch escape tower by integrating the escape system into an aerodynamic fairing that fully encapsulates the crew capsule and smoothly integrates with the launch vehicle. This paper proposes an ascent abort flight test for an all-propulsive towerless escape system concept that is actively controlled and sized to accommodate the Orion Crew Module. The goal of the flight test is to demonstrate a high dynamic pressure escape and to characterize jet interaction effects during operation of the attitude control thrusters at transonic and supersonic conditions. The flight-test vehicle is delivered to the required test conditions by a booster configuration selected to meet cost, manufacturability, and operability objectives. Data return is augmented through judicious design of the boost trajectory, which is optimized to obtain data at a range of relevant points, rather than just a single flight condition. Secondary flight objectives are included after the escape to obtain aerodynamic damping data for the crew module and to perform a high-altitude contingency deployment of the drogue parachutes. Both 3- and 6-degree-of-freedom trajectory simulation results are presented that establish concept feasibility, and a Monte Carlo uncertainty assessment is performed to provide confidence that test objectives can be met.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Proposed Ascent Abort Flight Test for the Max Launch Abort System


    Beteiligte:
    P. V. Tartabini (Autor:in) / M. G. Gilbert (Autor:in) / B. R. Starr (Autor:in)

    Erscheinungsdatum :

    2016


    Format / Umfang :

    14 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    A Proposed Ascent Abort Flight Test for the Max Launch Abort System

    Tartabini, Paul V. / Gilbert, Michael / Starr, Brett R. | AIAA | 2016


    A Proposed Ascent Abort Flight Test for the Max Launch Abort System

    Tartabini, Paul V. / Gilbert, Michael G. / Starr, Brett R. | NTRS | 2016


    A Proposed Ascent Abort Flight Test for the Max Launch Abort System (AIAA 2016-0783)

    Tartabini, Paul V. / Gilbert, Michael / Starr, Brett R. | British Library Conference Proceedings | 2016


    An Ejectable Data Recorder Subsystem for the Ascent Abort-2 Test Flight of the Orion Launch Abort System

    Rojdev, Kristina / Hagen, Jeff / Burlone, Michael et al. | IEEE | 2020


    Orion Launch Abort System Flight Test Program

    Parikh, P / Stover, G / Stadler, J et al. | AIAA | 2008