Fundamental structure of propellant storage station flight model was determined based on the studies of operation scenarios, storage methods, transfer methods, and merits and demerits of the various station orbit altitudes in comparison with that of the station. Technical problems concerning cryogenic propellant storage and transfer were picked up along presumable sequence of events from the viewpoints of problematic feasibility, necessity of design data, and durability. The subjects of the engineering test mission selected by the above study were as follows: (1) verification of automatic connection and self sealing capabilities; (2) validation of Thermodynamic Vent System (TVS) in microgravity; and (3) liquid volume (mass) measurement in microgravity. An overview of test equipment to meet the above subjects, the system structure and configuration, and operation plan for the engineering test satellite is presented.
Suishinzai Chozou/Isou Gijutsu Shiken Eisei No Gainen Kentou (Conceptual Study of Propellant Storage and Transfer Engineering Test Satellite)
1992
17 pages
Report
Keine Angabe
Englisch
Unmanned Spacecraft , Rocket Propellants , Liquid rocket propellants , Propellant storage , Propellant transfer , Satellite design , Space storage , Japanese spacecraft , Fuel tank pressurization , Fuel tanks , Liquid hydrogen , Liquid oxygen , Orbit transfer vehicles , Propellant storability , Reusable spacecraft , Spacecraft components , Foreign technology