Test data taken with nitrogen, hydrogen, and ammonia propellants are presented over a wide range of operating conditions at thrust levels up to 225 mN (50 mlb). The design adaptation of a flight-qualified thruster for operation with gaseous propellant inlet is described. Post-test analysis includes evaluation of thruster performance and efficiency, and shows the effects of propellant contamination on an immersed heating element.
Electrothermal Thruster Diagnostics. Volume 2: Technical
1983
57 pages
Report
Keine Angabe
Englisch
Electrothermal thruster diagnostics. Volume 2: Technical
NTRS | 1983
|Electrothermal Plenum Thruster
AIAA | 2021
|Microwave Electrothermal Thruster Performance
Online Contents | 2007
|Microwave Electrothermal Thruster Power
Online Contents | 1998
|