Abstract: A retainer mechanism for releasably securing a kinetic energy penetrator to he forward end of a missile while the missile is stored, transported and subsequently fired at a target such as a tank. The retainer releases the penetrator in flight responsive to acceleration acting on the missile, to reduce drag on the penetrator in its travel to the target.

Abstract: A missile which has folding wings at opposite side of the missile and exting longitudinally of the missile for allowing high density packaging of the missile in a launcher or container and the folding wings are deployed after the missile is ejected from a launcher or otherwise extended to a launch position to provide a cruciformed shaped wing structure about said missile for accurate guidance thereof.

Abstract: This invention disclosure describes a wing concept which can be folded al two axes. In the folded configuration, the semi-span of the wing lies parallel to the centerline of the missile fuselage. At deployment, the wing rotates about an axis parallel to the missile centerline. A second rotation follows when the wing's semi-span is made perpendicular to the missile's centerline. Finally the wing is locked into place and the deployed flight configuration is assumed.

Abstract: An explusion system in which an inner tank is nested within a second and er tank to provide a very compact and space saving arrangement for an expulsion system for a rocket with the first and inner tank as well as the second and outer tank being reinforced with composite material to provide a space saving and relatively light expulsion system for a rocket.

Abstract: Apparatus for centering the aft end of a missile in a telescoping launch e including equally spaced bore rider members bonded in the detent groove of a missile at the aft end of the missile. Each bore rider member includes upper and lower portions having a notch therebetween. The bore rider shears at the notch as the rider impacts the inner launch tube ramp. The remaining base is retained in the detent groove and centers the missile in the smaller launch tube as the missile moves along the smaller tube.

Abstract: A missile disposed for launching from a telescoping launcher having inner d outer sections. The missile is provided with fins folded along the body. A resilient spring clip member is carried on each said fin and engages the inner surfaces of the launcher sections as the missile traverses the launcher to retain the fins in folded position in the launcher.

Abstract: An automatic hard-soft detent system for releasably retaining a missile in telescoping launcher/carrier. The system includes a detent that is a beam spring having a projection thereon that is rigidly held in engagement with a detent groove in the missile by a ramp or tapered surface on the inner launch tube when the launcher is collapsed in the carry mode. When the tubes are extended, the tapered surface is moved from under the projection and the projection is held in the detent groove by spring tension. The detent projection is completely released from the detent groove responsive to forward motion of the ignited missile after the launcher/carrier has been extended to the launch position.

Abstract: In a missile having a shaped charge warhead that is pivotable from a posin in which the axis of the shaped charge is in alignment with the axis of the missile to a canted position in which the axis of the shaped charge warhead is canted relative to the axis of the missile and a rigid detonation transfer system for transferring detonation from safe and arm mechanism of the missile to the shaped charge warhead and utilizing a rigid arm with explosive therein and a precision initiation coupler on the shaped charge warhead to transfer detonation from the safe and arm mechanism to the shaped charge of the warhead to initiate explosion thereof.

Abstract: Apparatus for stabilizing the flight of a rocket wherein the body of the ket is provided with a plurality of petals arranged around the periphery of the aft end of the rocket with the leading end of each petal being pivotally attached to the rocket body such that the trailing end of each petal is free to move outward away from the rocket body. A ring slidably mounted on the rocket is linked to each of the petals in such a manner that as the ring moves in an aft direction on the rocket body the trailing ends of all of the petals simultaneously move outward equal distances from the rocket body.