Two-stage rocket will carry payloads of 150 lb to 300 statute miles (altitude), or 1000 lb to 150 mi; second stage of 55-ft long, fin-stabilized vehicle is powered by four liquid-propellant Aerobee 150A engines; vehicle design phase included propellant-utilization calculations, six-degree-of-freedom trajectory and roll lock-in simulations, and aeroelastic body deflections analyses; severe pressure surges encountered in sustainer fuel system during propulsion testing were suppressed by prepressurizing fuel tank; first flight test, using boosted inert sustainer, demonstrated compatibility of 7000-lb vehicle with 160-ft long launcher rail system at Wallops Island; summary of measurements and directions of present efforts.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Development of aerobee 350 sounding rocket


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Lane, J.H. (Autor:in) / Chalfant, C.P. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1967


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    DEVELOPMENT OF THE AEROBEE 350 SOUNDING ROCKET

    LANE, J. / CHALFANT, C. | AIAA | 1967


    Development of the Aerobee 350 sounding rocket.

    Chalfant, C. P. / Lane, J. H. | NTRS | 1967


    Development of the Aerobee 350 sounding rocket.

    Chalfant, C. P. / Lane, J. H. | NTRS | 1967



    Sounding rocket instrumentation data Aerobee 350, Flight 17.05GT-CG

    Pincus, B. R. / Stephenson, J. S. / Thompson, T. E., Jr. | NTRS | 1971