This paper presents the results of a program to describe the operational characteristics of an engineering model multipropellant resistojet for application as an auxiliary propulsion system for space station. Performance was measured on hydrogen, helium, methane, water (steam), nitrogen, air, argon, and carbon dioxide. Thrust levels ranged from 109 to 355 mN, power levels ranged from 167 to 506 W, and specific impulse impulse ranged from 93 to 385 sec, depending upon the propellant, chamber pressure, and heater current level selected. Detailed thermal maps of the heater and heat exchanger were also obtained for operation with carbon dioxide.
Preliminary performance characterizations of an engineering model multipropellant resistojet for space station application
Leistungseigenschaften des technischen Modells einer Multitreibstoff-Resistoduese fuer Raumstationen
AIAA-Papers ; Jul ; 1-22
1987
22 Seiten, 10 Bilder, 9 Tabellen, 16 Quellen
Conference paper
English