Equation of motion for powered flight of particular stage of multistage vehicle is reduced to first-order linear differential equation in vehicle weight, whose coefficients are known functions of time, by assumption that trajectory is known; design parameters include total weight, payload weight, specific impulse, propellant mass fraction, and vehicle diameter; it is possible to include specified constraints on vehicle such as fineness ratio or burning rate of solid propellants; method for choosing best propellant and chamber pressure from given set of propellants, and example of determining optimum chamber pressure for sustainer stage of two-stage vehicle.


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    Title :

    Rocket design for specified trajectory


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1965


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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