Current electric propulsion system concepts employ number of thruster modules operating in parallel; design of optimum system is much more flexible if individual thrusters are electrically decoupled and if they operate from propellant distribution manifold rather than each requiring separate propellant reservoir; three approaches to electrical isolation are -- use of device which permits isolation while Hg is flowing, use of insulating value which provides isolation when valve is closed, or provision of separate feed storage reservoirs for each thruster; analysis based on 17-kw system for Jupiter flyby is conducted; optimum system configuration for each approach is defined.
System concepts for liquid mercury cathode thruster
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 8
1968
8 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
System concepts for a liquid mercury cathode thruster.
NTRS | 1967
|System concepts for a liquid mercury cathode thruster.
AIAA | 1968
|System concepts for a liquid mercury cathode thruster.
NTRS | 1968
|System concepts for a liquid mercury cathode thruster
AIAA | 1967
|Development of a Liquid-Mercury Cathode Thruster System
AIAA | 1971
|