Approximating 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 were independent parameters for the computations. An optimized proportion of insulation mass and vaporized propellant mass was obtained. Maximum payload capacity was the optimizing criteria where the total mass and velocity requirement of the stage were given. (Author)
An Analytical Mass Model of Chemical Rocket Stages for Space Flight Missions. Part 2: Long Duration Missions
1976
41 pages
Report
No indication
English
Rocket Propellants , Unmanned Spacecraft , Chemical propulsion , Propellant tanks , Upper stage rocket engines , Mass , Models , Flight time , Payloads , Propellant evaporation , Propulsion system configurations , Space missions , Structural weight , Thermal insulation , Transfer orbits , Translations , West Germany
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