Patent ID: 6494035
Filing Date: 2002-12-17
Classification: F02K

Abstract:
A rocket motor assembly comprising:a tubular solid propellant grain having exterior surface area and interior surface area; means coupled to said exterior surface area for inhibiting ignition of said propellant grain therefrom; a housing having a tubular region for encasing said propellant grain and said means for inhibiting, said housing further having a first end and a second end at either end of said tubular region, said first end defining a plenum having an annular region defined by a diameter larger than that of said tubular region, said first end provided with a plurality of holes therethrough communicating with said annular region connectable to outside the plenum and directed substantially in the direction of said second end; a burn inhibiting baffle fitted in said propellant grain wherein an annular spacing is defined between said baffle and said interior surface area of said propellant grain; and an igniter mounted at said second end for igniting said interior surface area of said propellant grain.