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)
Analytic Mass Model of Chemical Rocket Stages for Space Flight Missions. Part 2: Long Duration Missions
1976
46 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Manned 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 , West Germany , Translations
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