AbstractExperimental investigations of the 10 N catalytic hydrazine thruster are reported. These thrusters find applications in orbit raising functions of a spacecraft. The hardware was realized and tested in a vacuum chamber (10−3 mbar vacuum) for its performance. When tested at the design propellant supply pressure of 21.5 bar the thruster developed 10.25 N thrust at an operating chamber pressure of 16.4 bar. The thruster was also tested for off-design conditions (24, 18 and 14.5 bar propellant supply pressures) of operation to determine the steady-state performance. The chamber pressure and vacuum thrust follow more or less a linear law with the propellant-supply pressure. The thruster was also tested for its response characteristics for short (100 ms) firing durations at various propellant-supply pressures (15.5, 18.8, 22.5, 25.6 and 29.5 bar) and the experimental results are reported and discussed. The hydrazine was injected at the room temperature (300±5 K).
Experimental investigations of the 10 N catalytic hydrazine thruster
Acta Astronautica ; 12 , 4 ; 237-249
1984-09-18
13 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Electrothermal hydrazine thruster development
AIAA | 1972
|Augmented electrothermal hydrazine thruster development
AIAA | 1983
|Hydrazine electrothermally augmented thruster /HEAT/
AIAA | 1979
|Experimental MPD thruster investigations
AIAA | 1987
|