The MOL orbital flight test program for a surface tension device and a dielectro-phoretic device will provide vital data in support of future development of liquid-propelled space propulsion stages. These propellant orientation and venting devices, suitable for use in low-gravity fields, obviate the need for ullage-settling rockets prior to each vent cycle or before each engine restart. Consequently, their use will increase payload and space velocity capabilities. The dielectrophoretic device also has potential multiple-use capabilities (if these can be verified in an orbital flight test) which further enhance its attractiveness for future propulsion stages. Typical of these additional capabilities are the support of propellant management and conditioning. The surface tension device appears to be most effective when used with storable propellants (since their surface tension properties are more favorable than those of cryogens); the dielectrophoretic device is better suited to cryogens because of their excellent dielectric properties.
In-Space Propellant Orientation and Venting Experiments
1967
41 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Liquid propellant rocket engines , Fuel systems , Dielectrics , Liquid rocket propellants , Orbits , Venting , Cryogenics , Interfacial tension , Acceleration , Electrodes , Vibration , Cavitation , Force(Mechanics) , Dielectric properties , Space stations , Dielectrophoresis , Mol(Manned orbiting laboratories) , Restarting , Ullage , Zero gravity
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