Launch Vehicle Abort Source Strength Model - Volume 2: Source Characterization.
Abstract
A mathematical model was generated to predict toxic chemicals released from an explosion involving a Titan II, Delta II, or Titan IV launch vehicle. The model was based on a variety of scientific and engineering input: the chemical description of interacting rocket propellants, data from previous accidents involving these or similar launch systems, an analysis of vehicle failure modes and propellant mixing characteristics, and thermochemical properties of reacting rocket propellants and their combustion products. Outputs of the model include the chemical composition and average molecular weight of the fireball cloud, the adiabatic flame temperature, the fireball size, and the total heat release. Input variables to the model include the time and altitude of abort, the mixing ratio for liquid propellants, amounts of unreacted liquid rocket propellants thermally decomposed, and the amount of air entrained into the fireball cloud. The mathematical model has been encoded into Fortran 77 for integration with the Rocket Exhaust Effluent Diffusion Model (REEDM) currently used at the Vandenberg Air Force Base (VAFB) Space Launch Complex.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 04, 1995
- Accession Number
- ADA302750
Entities
People
- Douglas W. Banning
- Stephen P. Prince
Organizations
- Martin Marietta