Patent ID: 8336287
Filing Date: 2012-12-25
Classification: C06B,F02K

Abstract:
1. A solid rocket motor, comprising: a combustion chamber bounded by an outer casing; a propellant grain within said combustion chamber; an igniter within said outer casing for igniting said propellant grain, and a nozzle coupled to said combustion chamber for releasing hot gasses evolved from burning said propellant grain to provide thrust for propelling said solid rocket motor, wherein said propellant grain comprises at least one fuel, at least one oxidizing agent, at least one binder, and at least one surfactant in an effective amount of at least 3.33 wt % of said propellant grain, said propellant grain exhibiting a burning rate as a function of pressure that includes a negative pressure dependence portion, said burning rate in said negative pressure dependence portion decreasing with increasing pressure until a cutoff pressure is reached which results in extinguishment of said propellant grain.