Accession Number:

ADA023346

Title:

Flame Spread into Solid Rocket Propellant Cracks.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1974-12-01

Pagination or Media Count:

173.0

Abstract:

An experimental study was conducted to investigate the spread of combustion flames into solid rocket propellant cracks. Experiments were performed using a combustion vessel with a free flowing nitrogen atmosphere under pressures of 300, 500, and 750 psig. Samples of three different propellants having crack widths varying from 0.022 in to 0.044 in were used. The ignition of the samples and the flame spread were recorded with a high-speed motion camera. Tests showed that the flame velocity inside the crack channels increased as the crack width decreased, and an entrance delay time usually exists prior to the flame entering the crack channel. For the range of crack widths investigated, no crack width was found for which flame penetration did not occur. Crack width demonstrated a greater effect on flame spread velocity in the crack than combustion pressure. The flame velocity flow inside a crack as a function of pressure and crack size is unique for each propellant tested.

Subject Categories:

  • Combustion and Ignition
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE