Experimental Study of the Plume Characteristics of a New Monopropellant Hydrazine Thruster
Final rept. 1 Oct 1977-30 Sep 1978
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An experimental study of the exhaust plume of a 0.44-N 0.1-1bf, hydrazine monopropellant thruster with a refurbished catalyst bed has been performed to characterize both the gas-dynamic and contamination properties of the vacuum plume expansion. The thruster was operated in a high-vacuum chamber over a thrust range of 0.44 to 1.10 N 0.1 to 0.25 bf with a nominal 0.14- secon9.86-sec-off duty cycle using initial catalyst bed temperatures of 367 and 478 K 200 and 400 F. The exhaust plume diagnostic systems employed included a mass spectrometer probe, a quartz crystal microbalance QCM, and a laser Raman Rayleigh scattering system. These systems determined plume species number densities and temperatures, mass deposition rates, and the level of particulates in the plume. Traditional engine performance parameters were also determined in order to relate performance and exhaust plume properties.
- Atomic and Molecular Physics and Spectroscopy
- Liquid Rocket Propellants