Design and Testing of a Cold Gas System
Abstract
Cold gas propulsion systems are relatively low-tech cheap devices. Total system mass disadvantage may be limited for low total impulse systems. Mission analysis of a cold gas system was conducted for the two binding extremes of isothermal and isentropic propellant expansion within the tank. Nozzle performance was initially modeled using empirical relations; subsequently two-dimensional axisymmetric, turbulent Navier-Stocks model was used. The results were in close agreement. For specified total impulse and average thrust a preliminary design analysis was conducted. The impact of hardware characteristics on optimum design configuration is discussed. An experimental dual thrust cold gas system, with a turn down ratio of 10 was designed. Test results include high and low thrust pulses and the effects of varying the pressure regulators set pressure. Close agreement with specified design values was achieved.
- Publication:
-
4th International Spacecraft Propulsion Conference
- Pub Date:
- October 2004
- Bibcode:
- 2004ESASP.555E..86H