Characterization of Rocket Propellant Combustion Products. Chemical Characterization and Computer Modeling of the Exhaust Products from Four Propellant Formulations
Abstract
The objective of this work was the determination of the chemical composition of exhaust products from the firing of scaled down rocket motors at the Army Signature Characterization Facility at Arsenal, and the comparison of those results with component levels predicted by a selected computer model. Both real time and off-line sampling and analysis approaches were employed. Four types of propellant compositions were evaluated. CO levels ranged from 85 - 350 ppm, while particle concentrations ranged from 30 - 100 mg/meters cubed. All of the airborne particles were in the inhalable range. For two of the propellants, airborne lead was greater than mg/meters cubed. For the predominantly perchlorate formulation, hydrogen chloride (HCl) levels were greater than 100 ppm. Particulate PAH levels were about a factor of 10 lower than that in outside ambient air particulate matter. The computer model predicted mole fractions for CO were typically 20 - 35%, except for the predominantly inorganic formulation. The model correctly predicted only minor amounts of ammonia and essentially no hydrogen cyanide. The accuracy of the predicted CO/CO2 ratios was low for all but one of the formulations. A modification of the model accomplished by mathematically accounting for mixing of hot exhaust gases with ambient air brought the predicted CO/CO2 ratio into greater agreement with that which was observed experimentally.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 31, 1990
- Accession Number
- ADA246346
Entities
People
- C. W. Nestor
- C. Y. Ma
- Carl V. Thompson
- R. A. Jenkins
- T. M. Gayle
Organizations
- United States Army Medical Research and Development Command