Presented are the results and interpretation of tests performed to investigate storability of propellants in space. The purpose of the work was to demonstrate the long term storage capability of cryogenic and earth storable propellants in a simulated orbital environment. A variety of tank sizes and shapes was tested. The test articles included a simulated meteorite shield and employed advanced support techniques suitable for a low 'g' environment. A simulated sun was utilized as the source of heat input. The sun was cycled to represent the conditions in a high inclination, low altitude earth orbit. The test results were analyzed and related to the storage of actual propellants. (Author)
Propellant Storability in Space
1964
2 pages
Report
No indication
English
ROCKET PROPELLANTS , PROPELLANT TANKS , STORAGE , ENVIRONMENTAL TESTS , SPACE ENVIRONMENTAL CONDITIONS , WEIGHTLESSNESS , SOLAR RADIATION , METEORITES , SIMULATION , ORBITAL TRAJECTORIES , VACUUM SYSTEMS , COATINGS , EPOXY PLASTICS , GLASS TEXTILES , THERMAL INSULATION , HEAT TRANSFER , LIQUEFIED GASES , EVAPORATION , METEORITE SHIELDS
Long-Term Storability of Propellant Tankage
NTIS | 1971
|Storability design criteria for space propulsion
AIAA | 1963
|Storability design criteria for space propulsion
AIAA | 1964
|