Abstract: A control system for providing directional control to a missile during bo phase operation. The kinetic energy of the propellant exhaust gases is utilized to pump a vacuum in an annulus located around the rocket nozzle. To provide a reaction force to guide the missile, a closure is removed from one of several reaction nozzles located around the periphery of the aft end of the rocket and in communication with the vacuum chamber and the atmosphere. A thrust is generated by the air flowing through the reaction nozzle, into the vacuum chamber responsive to opening predetermined reaction nozzles.

Abstract: A pure fluid interface device for proportional linear control of high temature, high pressure, hot gas flow from the exhaust of a rocket motor. The interface device receives the hot gas by direct bleeding from the rocket exhaust system and directs the gas to the control system of a missile airframe.The proportional linear control of the interface is achieved through a pair of positive displacement pistons which engage a jet pipe, charged with the hot gas, for pivotal movement of the jet pipe for alignment of the orifice of the jet pipe with one or both exit ports in the body of the interface device to direct the hot gas through the desired exit port.

Abstract: A hold-down latch having an overcenter pivot arm which is spring biased in perative position. The latch includes a spring for engagement with a lug on the device to be held down. The latch functions as a shock absorber against vertical movement or vibrations while allowing longitudinal movement of the hold-down device.

Abstract: A rocket having flip out tail fins with cooperating surfaces on said fins d the rear of said rocket to maintain said fins in extended position. Spring means for urging said cooperating surfaces into engagement with each other.

Abstract: A rocket having flip out tail fins with cooperating surfaces on said fins d the rear of said rocket to maintain said fins in extended position. Spring means for urging said cooperating surfaces into engagement with each other.

Abstract: A launcher carried on the flatbed of a mobile vehicle to provide the dual le of missile transporter and pre-launch positioning of its multi-missile payload. The launcher is not trainable in azimuth or elevation. When emplaced the launcher carriage erects the missiles to substantially a 75.degree. launch angle and a missile is fired from a combination launch tube shipping container by a small propellant charge and uses its own control to put it on the proper trajectory. Missile motor ignition is delayed for a predetermined time after launch.

Abstract: A small cylindrical pyrotechnic pellet having an igniter, a time delay, and n output charge of easily ionized material for placing a predetermined number of ions and free electrons at a predetermined position in the upper atmosphere or space.

Abstract: A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are predetermined to fit the desired motor performance. The release of motor pressure is controlled by the rate of change of momentum of the nozzle closure.

Abstract: A man transportable rocket launcher including a pair of telescoping secti, launch tubes, which are telescoped to a short length for transporting and extended to a longer length for launching of the rocket. A locking device is provided for maintaining the launch tubes in the extended condition for rocket launching.

Abstract: A man transportable rocket launcher including a pair of telescoping secti, launch tubes, which are telescoped when being transported and extended for launching of the rocket. The warhead of the rocket always rides on the inner surface of the front tube which is carried inside the rear tube. Retention means cooperate with the fins to assist in retaining the rocket fins in folded position in the launcher prior to rocket launch. The retention means is moveable, with the rocket in the rear tube, for a predetermined length of travel of the rocket at which time the fins are released by the retention means and engaged by the inner surface of the front tube.