The feasibility of using a single metallic heat sink thermal protection system (TPS) over a projected flight test program for a hypersonic research vehicle was studied using transient thermal analyses and mission performance calculations. Four materials, aluminum, titanium, Lockalloy, and beryllium, as well as several combinations, were evaluated. Influence of trajectory parameters were considered on TPS and mission performance for both the clean vehicle configuration as well as with an experimental scramjet mounted. From this study it was concluded that a metallic heat sink TPS can be effectively employed for a hypersonic research airplane flight envelope which includes dash missions in excess of Mach 8 and 60 seconds of cruise at Mach numbers greater than 6. For best heat sink TPS match over the flight envelope, Lockalloy and titanium appear to be the most promising candidates


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Study of heat sink thermal protection systems for hypersonic research aircraft


    Contributors:

    Conference:

    Aerospace Sciences Meeting ; 1978 ; Huntsville, AL


    Publication date :

    1978-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Aircraft Thermal Management -Heat Sink Challenge

    Dooley, M. / Lui, N. / Newman, R. et al. | British Library Conference Proceedings | 2014


    Aircraft Thermal Management -Heat Sink Challenge

    Lui, Clarence / Dooley, Matthew / Lui, NIcholas et al. | SAE Technical Papers | 2014


    Aerodynamic thermal protection device and hypersonic aircraft

    LI XUEYING / REN JING / TANG ZHENYUAN et al. | European Patent Office | 2024

    Free access

    Energy Management for Hypersonic Heat-Sink Nozzles

    Felderman, Elmer / Shope, Fred / Akers, Dennis | AIAA | 2003