A study has been performed on a laser-heated ramjet/scramjet vehicle concept for propulsion during the air-breathing portion of an orbital launch trajectory. The concept considers axisymmetric, high-thrust vehicles with external inlets and nozzles. Conceptual design and ramjet/scramjet cycle analysis are emphasized, with propulsive energy provided by combustion of on-board fuel. The conventional ramjet/scramjet combustion chamber is replaced by a laser energy absorption chamber. The elimination of on-board propellant can result in very high thrust-to-weight ratios and payload fractions, in a vehicle with a relatively small degree of mechanical complexity. The basic vehicle has a weight of 12,250 lbf, and a diameter of 5 meters, which is close to the size of the Apollo command module. The ramjet calculations are based on a Mach 3 isentropic inlet with a 13.7 degree half-angle conical tip. The scramjet analysis considers conical inlets with 10, 15, and 30 degree half-angles. Flight Mach numbers from 2 to 20 are considered in the calculations.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Analysis of beamed-energy ramjet/scramjet performance


    Beteiligte:
    Myrabo, L. N. (Autor:in) / Powers, M. V. (Autor:in) / Zaretzky, C. L. (Autor:in)

    Erscheinungsdatum :

    01.06.1986


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Analysis of beamed-energy ramjet/scramjet performance

    POWERS, M. / ZARETZKY, C. / MYRABO, L. | AIAA | 1986


    Ramjet and Scramjet Engine

    Babu, V. | Springer Verlag | 2021




    RAMJET-MODE OPERATION IN A SCRAMJET COMBUSTOR

    Kato, K. / Kanda, T. / Kudo, K. et al. | British Library Conference Proceedings | 2003