Shock propagation in the exhaust gas handling system of the proposed large altitude rocket cell: methods and preliminary analysis

Technical Report · Thu Oct 04 00:00:00 EDT 1984

OSTI ID:6189320

Sutton, S B; Pierce, R E

Numerical predictions are to be performed of the shock pressures that would result from the detonation of 100,000 lbm TNT. The initial phase of the project was to develop the methodology for analyzing the problem, develop a preliminary conceptual design to use in initial simulations, and estimate over-pressures, inside the conceptual facility, resulting from the propellant detonation. This report discusses the methods of analysis used to study the problem of the detonation of the propellant, and the propagation of the shock wave inside the exhaust gas processing system, and presents preliminary results. The KOVEC computer code was used to simulate the detonation of 100,000 lbm TNT and develop a boundary prescription for use in the gas dynamics code GASP which models the propagation of the shock wave through the LARC exhaust gas processing system. Results are presented showing the effect of cross-sectional area changes and variations in the initial pressure in the gas processing system on the shock wave peak pressure and propagation speed.

• Research Organization: Lawrence Livermore National Lab., CA (USA)
• DOE Contract Number: W-7405-ENG-48
• OSTI ID: 6189320
• Report Number(s): UCID-20179; ON: DE85003055
• Country of Publication: United States
• Language: English

Related Subjects

45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEFENSE
PROPELLANTS
DETONATIONS
COMPUTER CODES
COMPUTERIZED SIMULATION
EXHAUST GASES
K CODES
PRESSURE GRADIENTS
ROCKET ENGINES
SHOCK WAVES
TEST FACILITIES
WAVE PROPAGATION
ENGINES
FLUIDS
GASEOUS WASTES
GASES
SIMULATION
WASTES
450100* - Military Technology
Weaponry
& National Defense- Chemical Explosions & Explosives