The objective was to prepare for the design of the space station propulsion system. Propulsion system concepts were defined and schematics were developed for the most viable concepts. A dual model bipropellant system was found to deliver the largest amount of payload. However, when resupply is considered, an electrolysis system with 10 percent accumulators requires less resupply propellant, though it is penalized by the amount of time required to fill the accumulators and the power requirements for the electrolyzer. A computer simulation was prepared, which was originally intended to simulate the water electrolysis propulsion system but which was expanded to model other types of systems such as cold gas, monopropellant and bipropellant storable systems.
Space Station Onboard Propulsion System: Technology Study
1987
106 pages
Report
No indication
English
Rocket Engines & Motors , Electric & Ion Propulsion , Chemical propulsion , Design analysis , Propulsion system configurations , Rocket propellants , Space stations , Spacecraft propulsion , Cold gas , Computerized simulation , Electrolysis , Hybrid propulsion , Hydrazine engines , Liquid rocket propellants
Space Station propulsion system technology
Elsevier | 1987
|Space station propulsion system technology
NTRS | 1987
|Space Station propulsion system technology
NTRS | 1987
|Space Station Propulsion System Technology
NTIS | 1987
|