Abstract: Warhead fragment size can be selectively controlled by: (1) internally or externally grooving a warhead casing; (2) providing an internal casing liner or explosive charge with a predetermined cutting groove pattern confronting the grooves in the casing; (3) positioning the liner or explosive charge groove pattern relative to the casing groove pattern so that warhead fragments of one size will be produced if the grooves in the liner or explosive charge are rendered ineffective for cutting the warhead and so that fragments of another size will be produced if the grooves in the linear or explosive charge are not rendered ineffective and therefore are utilized to cut the casing; (4) providing apparatus in the warhead for delivering a fluid such as water to the grooves in the linear or explosive charge to selectively inhibit the cutting action of those grooves to provide desired warhead fragment size(s).

Abstract: There is disclosed a missile which automatically disintegrates after a predetermined flight time. The missile is made up of several parts which are positively secured together by a locking means which is released at a predetermined time after the firing of the missile by the action of the air through which the missile passes during its flight. The invention may by used to advantage in both practice missiles and service missiles.

Abstract: A separation nut system having bolt ejecting separation nut assemblies coned with bolt catcher assemblies. At least two separation nut assemblies with their respective bolt catcher assemblies are connected by a manifold tube so that, should the squib initiator of one separation nut assembly fail, the manifold tube will transfer and redistribute the gas generated from one squib to both separation nut assemblies to provide performance redundancy. Also, each separation nut assembly is capable of being tested for performance integrity prior to actual usage without the need for disassembly and subsequent reassembly and inspection after each use.

Abstract: An engine mount to position a rocket engine within a missile stage and to lease the engine upon burn-out. A separation ring comprising a bracket portion and a shroud portion encircles the engine. The bracket is located approximately mid-length of the engine and wound thereon to engage the engine-circling sheath having a grooved and unsymmetrically weakened cross-section. The shroud is joined to the interior of an on-flying missile stage. A small rocket and fail-safe abutment ensure that the motor will be released in a direction opposite to the continuing flight path of the parent stage.

Abstract: A pair of structural members are coupled by a tongue and groove joint hav a groove half and a tongue half. To secure the joint, bolts extend transversely through aligned bolt holes and, on each side of the tongue half holes, are so-called `collapsing` slots. A linear explosive is placed in the base of the groove near the inner end of the tongue. The metal thickness of the tongue lying between the explosive and its holes and slots forms a `web` which, upon detonation, collapses into the slots. The collapse stretches the web portion adjacent the bolt holes sufficiently to produce a rupture or opening through which the bolts pass to permit separation of the structural members. The separation also is responsive to the explosive force so that the members are accelerated apart in opposite directions.

Abstract: 1. A booster comprising an open ended housing, a propellant charge carried within said housing, a trap assembly interposed between said propellant and opening for restraining said propellant, said trap including an annular ring member, and a plurality of radially extending arms held in disengageable interlocking relation with said ring member, said interlocking arms and ring member being arranged to maintain a rigid assembly upon the application of force from one direction, but which are readily collapsible upon the removal of said force after the booster has been expended.

Abstract: A motion-induced stimuli initiation system for actuating various missile otechnic devices based upon attainment of specified values of acceleration, velocity and distance after launch. Data from accelerometers are integrated to obtain velocity, the velocity data are integrated to obtain distance. Comparison of acceleration, velocity and distance with predetermined values by appropriate logic circuitry provides the signals to initiate the pyrotechnic devices.

Abstract: This invention is a solid fuel air turbo rocket. A solid propellant charge, hich is richer in fuel than conventional propellant compositions, burns in an initial chamber. The gases so produced pass through turbine blades into a second chamber. The turbine, which is rotated by the gases impinging on and passing through the blades, drives a compressor which compresses air from the atmosphere. This compressed air is fed into the second chamber where the oxygen in the air reacts with the fuel rich gas to produce further combustion and gas expansion. The gasious products so generated pass through a nozzle into the atmosphere, resulting in thrust to the missile. As the missile accelerates a variable area air inlet is reduced to maintain a normal shock at the throat. When ramjet take-over velocities are reached, the turbo-compressor is jettisoned to allow the second chamber to function as a ramjet burner.

Abstract: A hypervelocity ammunition round in which a spin stabilized artillery projectile contains a plurality of subcaliber gun tubes for launching subcaliber spin stabilized projectiles from the artillery projectile at a predetermined point in its trajectory, as the artillery projectile performs as a moving gun platform to more effectively defeat a multiplicity of targets through the kinetic energy impact of the subcaliber projectiles.

Abstract: A nozzle ejection system having an outer nozzle, an inner nozzle located within the outer nozzle and a snap ring within the outer nozzle for holding the inner nozzle in place. An explosive charge is operatively connected to the snap ring, with the explosive charge detonating at a preselected time thereby either breaking or releasing the snap ring and allowing the inner nozzle to be ejected from the outer nozzle.

Abstract: A pressure activated, timed missile flight termination system for destroy a test missile after a predetermined period of flight to shorten its hazard space so that it can be used on firing ranges having a minimum amount of area. A delayed destruct sequence is initiated by pressure in the missile combustion chamber upon ignition of the missile. A pressure driven piston is compressed by the pressure created in the combustion chamber, causing it to strike a primer which initiates a delay fuse, a detonator, and a linear-shaped charge to destroy the missile.

Abstract: An apparatus for coupling the stages of a missile or other multistage mov object which is adapted to release the stages at a desired time. A separation bolt connects for and aft stages prior to a desired signal. The bolt is held at its lower portion in an assembly capable of thrusting it entirely into the other stage upon the signal. A bolt catcher captures the bolt in the other stage.

Abstract: Thrust termination of a solid propellant rocket motor is obtained by connecting the nozzle to the combustion chamber pressure vessel by means of explosive and extrusable bolts. When it is desired to obtain thrust termination, the explosive bolts are blown leaving the nozzle connected to the pressure vessel by the extrusable bolts. The extrusable bolts have sufficient strength to retain the nozzle assembly; however, upon elimination of the strength of the explosive bolts, the nozzle is permitted to separate from the pressure vessel and move to the rear by drawing the extrusable bolts through dies. The bolts deform to absorb the energy of the nozzle and the jolt of forward acceleration which would normally be obtained if the nozzle were ejected, is reduced or eliminated.

Abstract: An actuator adapted for use in separating two interconnected bodies, while maintaining their respective desired directions. In the preferred embodiment, the actuator includes a housing which supports and guides a captive coiled spring that is adjusted for proper preload compression by a nut, and a center plunger to which is removably connected a bolt, headup. The actuator is attached to one of the interconnected bodies. The proper plunger travel is adjusted by a retraction tool that is then removed; and, the bolt is extended to touch the other interconnected body. When the interconnection is broken, the spring is released and, without changing the direction of the body to which the actuator is attached, imparts the desired direction to the first body.

Abstract: An explosive linear cutter for cutting materials comprising an explosive rge sheathed in a metal covering, a support for said charge surrounding the covering except for a slot facing the target material to be cut. Separation of the target material is effected by propelling a fragment of metal sheath at high velocity through the slot and into the target upon detonation of said explosive charge to thereby achieve a clean highly directional cut along a desired separation line.This abstract is for the purpose of providing a non-legal brief statement to serve as a searching tool and is not intended to limit the scope of the invention as disclosed herein nor limit the scope or fair meaning of the appended claims.