Ignition Testing of U.S. Army Rocket Launch Tubes with Comparative Heat Transfer Analysis

Abstract

The objective of this research was to determine the time to ignition of U.S. Army fiberglass epoxy rocket tubes in various conditions. Experiments were conducted using an oxygen calorimeter and a propane burner for determining the ignition time. The Biot number and heat transfer coefficient was determined. A lumped capacitance method was used to calculate the energy input.

The energy input from the rocket plume into the tube was calculated using a semi-infinite solid with surface convection.

The two energy calculations were compared indicating that approximately 1.4 rockets must be fired in rapid succession to lead to ignition conditions. Tube condition was found to have no affect on ignition time.