Abstract: A segmented rocket motor case includes wedge members for forcing the case segments into position to remove free play at the joint thereof which may otherwise interfere with or upset the missile's guidance system and throw it off target. A lap joint member for such a joint includes a shoulder having a surface for attachment of a membrane seal assembly for a pulsed rocket motor. A through bulkhead initiator communicates from the forward segment via a fitting which extends through the membrane seal assembly with an igniter for the propellant grain within the aft segment to eliminate the necessity of running explosive transfer lines along the outside of the case from a safe and arm device and other controls at the head end of the rocket motor.

Abstract: A safe and arm device is responsive to electrical signals by way of two solenoids that push and pull, respectively, an arm to rotate, in turn, each of a series of three cogwheels by steps. When each of the cogwheels has been rotated a given number of steps prescribed by a secret code, slots or cutouts in each of the cogwheels are aligned to permit passage therethrough of an elongated bar or rack that can then operate or enable a switch or other mechanism to fire a rocket motor, etc.

Abstract: A generally cylindrical housing construction for a light weight gas generator of minimum bulk includes two subassemblies, each of which have first and second concentric cylinders depending from a flat wall and which are joined together by inertia welding to form a central igniter chamber and an outer annular chamber. The outer chamber is divided into three axially extending annular chambers by two flat annular barriers. Solid fuel is contained in a first annular chamber. Communication between the three annular chambers is provided by openings in the barriers, the openings in the barrier adjacent the solid fuel being disposed on a circle adjacent the outer edge thereof while the openings in the other barrier are disposed on a circle adjacent the inner edge. A cooling and filtering means is provided in each of the second and third annular chambers, with an air space between the two subassemblies for clearance during welding.

Abstract: A closed urethane cylindrical case includes a mounting base or foot which runs parallel to the axis of the case and is bonded to the surface of the propellant grain of a full head-end-web rocket motor. Contained within the case are one or more spaced tube initiators and concentrically positioned discs or webs of high energy propellant. Flaming gases resulting from actuation of the tube initiators and consequent burning of the propellant wafers are projected over the surface of the rocket motor propellant from a plurality of nozzle ports that are provided in the cylindrical case, in the quadrants thereof adjacent the surface of the rocket motor propellant. Cylindrical case length and the number of tube initiators and propellant wafers including their spacing can be selected as required to achieve a desired mass flow rate.

Abstract: An igniter for high-performance rocket motors having a full, head-end web of propellant in the forward end of the motor comprises a closed, rigid pressure vessel having walls which are formed of a consumable filament structure. The igniter includes a hollow cylindrical solid propellant having a high surface grain area which operates at high pressure and is removably attached to a liner that is provided in a cavity in the aft end of the propellant. The liner is machinable with the motor propellant grain thereby facilitating propellant grain cutback if required by a change in mission of the motor. The thrust produced by the igniter neither applies stresses to the motor propellant nor exerts any forces tending to eject it from the cavity.

Abstract: A housing is mounted to the convergent portion of a convergent-divergent thrust nozzle for rockets via legs that space the housing from the nozzle so that it will not obstruct the flow of propulsive gases therethrough. A cavity in the housing holds a secondary nozzle member having a throat that is smaller in diameter than that of the primary nozzle. An electrically actuated, gas producing device in the housing forces the secondary nozzle member out of its cavity on command and seats it against the convergent portion of the primary nozzle. Simultaneously, ports in the housing are opened to the propulsive gases of the rocket, this forces a plug, that seals the secondary nozzle during storage, out through the primary nozzle.Some embodiments of the invention also provide for attaching a rocket igniter to the housing, so that the electrical wiring to the igniter can pass through the same ducts and holes as the wiring to the gas producing device for deploying the secondary nozzle.

Abstract: A barrier assembly for a safety and arming electro-explosive device of the type comprising a rotor containing detonators and rotatable between safe and arm positions includes a body of lead as an energy absorbing material in the safe position of the device. When the shock wave from a detonator hits the lead, the lead flows and attenuates the shock wave. Cycling after the device has been fired in the safe position is precluded by an undercut in the rotor into which the lead flows, thus preventing rotor rotation after firing.