Propellant configuration for a solid propellant rocket motor

F - Mech Eng,Light,Heat,Weapons – 02 – K

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F02K 9/18 (2006.01) F02K 9/95 (2006.01)

Patent

CA 1255509

Abstract A propellant configuration for a solid propellant rocket motor A propellant configuration has a generally cylindrical housing (14) containing a generally cylindrical main grain (12) having a central cavity (16) and a plurality of interior flutes (24) formed in the main grain (12) about said central cavity (16). At the time an air launched vehicle is being fired, it is desirable for the rocket motor to quickly accelerate the missile from the launch rack as well as to minimize the effects of the rocket exhaust on the launching means. This is accomplished by an igniter assembly (20) supported in the central cavity (16) having means there- in for bringing about combustion. At the time of actua- tion of the igniter assembly (20), hot gases are direc- ted along flutes (24) formed in the interior of the main grain (12), to cause burning thereof to take place, with the burn surface area of an igniter grain (64) being in a pre-established relationship to the burn surface area of the fluted main propellant grain (64), such that the igniter grain (64) will be totally consumed at the time that the flutes (24) of the main propellant grain (12) are consumed. In this way the total burn area of the main grain (12) is reduced to a value which produces a distinct and highly desirable reduction in the total mass flow rate, this preferably occuring adjacent the end of the launch mechanism. Fig.2.

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