Abstract 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 therein for bringing about combustion. At the time of actuation of the igniter assembly (20), hot gases are directed 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.
A propellant configuration for a solid propellant rocket motor, comprising a generally cylindrical housing (14) containing an essentially 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) characterised by an igniter assembly (20) supported in said central cavity (16) having means therein for bringing about combustion, so that hot gases can flow therefrom at the time said igniter has been actuated, at least part of such flow of hot gases being directed on the flutes (24) formed in the interior (16) of said 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 portion of the main propellant grain (12).
Claim 2
Dependent Claim
141 words
A propellant configuration for a solid propellant rocket motor, comprising a generally cylindrical housing (14) containing an essentially 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) characterised by an igniter assembly (20) supported in said central cavity (16) having means therein for bringing about combustion, so that hot gases can flow therefrom at the time said igniter has been actuated, at least part of such flow of hot gases being directed on the flutes (24) formed in the interior (16) of said 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 portion of the main propellant grain (12).
Claim 3
Dependent Claim
28 words
The propellant configuration as claimed in claim 1, wherein the propellant utilized in said main grain (12) is the same as that utilized in said igniter assembly (20).
Claim 4
Dependent Claim
94 words
A propellant configuration as claimed in claim 1, wherein the relationship of the burn surface of the igniter grain (64) to the burn surface area of the fluted main propellant grain (12) is 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, thereby reducing the total burn area of the main grain (12) to a value which produces a distinct and highly desirable reduction in the total motor mass flow rate adjacent the end of the launch mechanism.
Claim 5
Dependent Claim
32 words
A propellant configuration as claimed in claim 1, wherein said igniter assembly (20) has a plurality of outlet ports (22,26) therein, through which hot gases flow when combustion has been brought about.