MONITORING OF ROCKET ENGINE PERFORMANCE BY SPECTROSCOPIC TECHNIQUES
Technical rept. for 10 Apr-10 Aug 1964
ASTROSYSTEMS INTERNATIONAL INC FAIRFIELD NJ
Pagination or Media Count:
An analytical investigation was conducted to study the emission spectra of the exhaust stream of selected rocket engine liquid propellant combinations to determine the feasibility of detecting exhaust specie spectra as a measure of various propulsion system characteristics. The propellants selected for analysis were oxygenhydrogen, oxygenRP-1 and nitrogen tetroxide unsymmetrical dimethylhydrazine as being most representative. A rocket engine for test was designed having a chamber pressure of 50-100 psia and a flow rate of 0.1 gmsec. Calculations of signal strength with mixture ratio were made and the species OH, NH, CO and NO found to be of most interest. It was determined that mixture ratio variations and flow rate variations could be separately detected. A system for detecting incipient burnout by monitoring metallic oxide emissions and instability by intensity frequency pattern variations was presented. A flight weight system was shown to be feasible.
- Atomic and Molecular Physics and Spectroscopy
- Liquid Propellant Rocket Engines