Approximation equations were derived to design optimal propellant insulation systems for transfer stages. Propellant, mission duration, thermal environment, insulating material, transfer stage design, and the orientation of the stage to the heat source are independent parameters for the computations. An optimized proportion of insulation mass and vaporized propellant mass is obtained. Maximum payload capacity is the optimizing criteria where the total mass and velocity requirement of the stage are given. (Author)


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    Title :

    Analytic Mass Model of Chemical Rocket Stages for Space Flight Missions. Part 2: Long Duration Missions


    Contributors:
    J. Broschk (author) / M. M. Bunn (author) / D. Manski (author)

    Publication date :

    1976


    Size :

    46 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English