The laser-driven rocket in which remotely generated laser power is used to heat propellant belongs basically to the class of specific-impulse limited propulsion systems if difficult missions are considered. It was previously established that trip time reaches a minimum as specific impulse is varied for payload transfers from low earth orbit to synchronous orbit and return via laser-driven rocket propulsion, the computations being based on the perigee-propulsion laser drive described by Minovitch (1972). The present study shows that such minimum occur for all missions and that optimum specific impulse is primarily determined by the mission difficulty. More generally, this optimum specific impulse maximizes payload kinetic energy achievable with a fixed jet power and propulsion time. A formula relating propulsion time parameter to payload ratio is obtained for estimating mission capabilities of laser-driven rockets.


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    Titel :

    Optimum exhaust velocity for laser-driven rockets


    Beteiligte:
    Moeckel, W. E. (Autor:in)


    Erscheinungsdatum :

    01.11.1975


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch





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