First phase of program of development work on plasmajet thruster suitable for attitude control and orbit adjustment of satellite is described; effort resulted in thruster capable of delivering required thrust (0.01 lb) at specific impulse in excess of 1100 sec; kinetic efficiencies in excess of 35% were obtained using hydrogen as propellant; specific design, along with other designs tested, is reported.
Research and development of 1-kw plasmajet thruster
AIAA J
AIAA Journal ; 1 , n 2
1963
5 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
RESEARCH AND DEVELOPMENT OF A 1-KW PLASMAJET THRUSTER
NTRS | 1963
|RESEARCH AND DEVELOPMENT OF A 1-KW PLASMAJET THRUSTER
AIAA | 1963
|Micro-Multi-Plasmajet Array Thruster
AIAA | 2010
|RESEARCH AND DEVELOPMENT OF A 1 KW PLASMAJET THRUSTER
NTRS | 1962
|EXPERIMENTAL PLASMAJET THRUSTOR RESULTS
AIAA | 1963
|