Abstract: A composite gun barrel 10 with active cooling having a breech end and a dharge end. The barrel includes an outer jacket 11 having radially inwardly projecting ports 15 proximate the breech end 25 extending inwardly from the outer diameter of the jacket, and an inner liner 13 inside the jacket and extending beyond the discharge end of the jacket prestressed by autofrettage to form a permanent integral assembly. The inner liner has a circumferentially located annular space 17, the ports being in operable communication with the annular space. A plurality of circumferentially spaced longitudinal channels 19 on the liner extend from the annular space to a location 21 beyond the discharge end of the jacket. The liner includes a shoulder 23 located between the breech end of the barrel and the inwardly projecting ports for locating the jacket on the liner.

Abstract: A launcher is disclosed having means for directing and concentrically spreading, as well as dispersing, exhaust gases created by an internal combustion of an object, such as a missile, that is operatively launchable therefrom. The concentric duct provides the directing, spreading and dispersing means and cooperates with a cup having means to arrange a port in operative relationship with an exhaust outlet of the object being launched. The cup which mates with the concentric duct has one of its ends open to the ambient so that the exhaust gases are lead into and out of the concentric duct so as to be concentrically dispersed into the atmosphere.

Abstract: An airbag deflection mount for mounting an airbag cushion to an airbag module and for deflecting hot inflation gas away from a throat of the airbag cushion. The airbag deflection mount includes a generally flat retainer ring for securing a collar of the airbag cushion around an inflator of the airbag module that produces and expels the inflation gas from a plurality of inflation ports for inflating the airbag cushion upon a vehicle collision. The airbag deflection mount also includes a plurality of deflectors extending upwardly from the retainer ring and positionable, spaced-apart from the inflator, between the plurality of inflation ports of the inflator and the throat of the airbag cushion. The plurality of deflectors deflect hot inflation gas away from the throat of the airbag cushion and substantially prevent the throat of the airbag cushion from being burned by the hot inflation gas.

Abstract: A shoulder-launched multiple-purpose assault weapon having a modified spotter rifle with a top-mounted rocket launcher tube is provided. The spotter rifle forms the base structure of the weapon and all weapon controls are located on the spotter rifle. The spotter rifle has several dual-function mechanisms which perform the combined functions of assembly and safing, bolt-locking back and cartridge ejecting, simultaneous adjustment of both open and optical sights, firing, selectively, of both the spotter round and the rocket round. The combination of these dual-firing mechanisms provides a lighter weight, better-balanced and smaller weapon. The reduction in parts count improves reliability and lowers cost. Other improved features include an adjustable spotter rifle barrel used to match the boresight of the rocket tube and an improved locking mechanism. A dual function trigger assembly operated two sears from a single trigger.

Abstract: It is possible to improve the hit probability of programmable projectiles by means of this method. For this purpose a predetermined optimal disaggregation distance (Dz) between a disaggregation point (Pz) of the projectile (18) and an impact point (Pf) on the target is maintained constant by the correction of the disaggregation time (Tz) of the projectile (18). The correction is performed by adding a correcting factor, which is multiplied by a velocity difference, to the disaggregation time (Tz). The velocity difference is formed from the difference between the actually measured projectile velocity and a lead velocity of the projectile, wherein the lead velocity is calculated from the average value of a number of previous successive projectile velocities.

Abstract: An apparatus and method for improving stability in a transmitter receiving a staggered pulse train includes maintaining a constant temperature of the transmitter at the start of each pulse of the pulse train. Such maintenance may be accomplished by inserting "false", "phantom" or "synthetic" pulses into the pulse train. These pulses may be inserted between pulses, prior to a cooler pulse, or after a hotter pulse. The inserted pulses are then gated out prior to the final RF transmission.

Abstract: A detonator (10) contains an SCB initiator assembly (35) in initiation relation to an ignition charge (18). The SCB initiator assembly (35) contains an initiator element (36) having a bridge (60) of semiconductor material between two conductive lands (62a, 62b). The bridge (60) provides a resistance of at least about 50 ohms and has a volume between 48,600 cubic microns and 600,000 cubic microns with a typical thickness of two microns. A firing current of more than 200 milliamp provided to the initiator assembly (35) via input leads (26a, 26b) causes the bridge (60) to initiate the ignition charge (18).

Abstract: A range correction module which is designed to fit onto a spin stabilized llistic projectile for correcting range error. The range correction module is a self-contained module within the fuze which screws into the forward portion of the projectile. The range correction module is designed such that changes are not required to the existing projectile. During the course correction phase, sixteen semi-circular plates will deploy from the module. The plates create a blunt cross-sectional area in front of the projectile, thus creating more drag and effectively slowing the projectile.

Abstract: This invention concerns a missile launching system, and particularly a missile launching and orientation system. It can be used to modernize missiles with an inclined launch at an angle by transforming them into missiles controlled for circular defense, avoids ejection of the passive mass within the launching area. In order to do this, the launching system comprises launching means, aerodynamic control surfaces with drive and means of orientation including at least one gas generator and nozzles connected to it. Orientation means are located in an annular body rigidly connected to the rear part of the missile body. The outside surface of the annular body is cone-shaped and is covered with a thermal insulating material forming a gas pipe, the profile of which is a continuation of the profile of the nozzle of the missile cruise engine.

Abstract: A safety and arming device interconnecting a bomb with a target detector ures safe mine laying deployment thereof through a detonation explosive train that is armed in delayed response to payout of a lanyard under enablement control exercised by a hydrodynamic piston in response to water impact during such deployment.

Abstract: A range correction module which is designed to fit onto a spin stabilized ballistic projectile for correcting range error. The range correction module is a self-contained module within the fuze which screws into the forward portion of the projectile. The range correction module is designed such that changes are not required to the existing projectile. During the course correction phase, semi-circular plates will deploy from the module. The plates create a blunt cross-sectional area in front of the projectile, thus creating more drag and effectively slowing the projectile.

Abstract: A bipod mounting assembly for attaching a bipod to the forearm stock portion of a firearm, which includes a mounting yoke adapted to quickly and easily attach to the swivel stud connector mounted to the forearm stock portion of the firearm. The mounting yoke is adapted to receive a mounting block thereover, with the mounting block being attached to the mounting yoke to thus attach the mounting block to the forearm stock portion of the fire arm. A bipod mounting frame that includes a pair of extensible telescoping legs is releasably attachable to the mounting block by a quick-release locking catch to enable the quick attachment/detachment of the legs of the bipod from the mounting block, and thus the firearm. In one embodiment the mounting yoke has a threaded stud that extends through the mounting block and receives a securing bolt to secure the mounting block to the firearm.

Abstract: Internal heat transfer of air cooled turbine blades of a gas turbine engine is enhanced by orienting the impingement holes that interconnect the air-cooled feed passage to the hybrid passageway internally of the blade in a more radial direction to minimize pressure drop losses. By improved mixing of the cooling air in the hybrid passageway the additional mechanical turbulence promoters can be utilized without sacrificing pressure losses.

Abstract: An arrangement for selectively disconnecting an airbag fitted within a passenger compartment of a motor vehicle. The arrangement includes a visible warning means retractable within a component and adapted to be withdrawn to extend over at least a predetermined region of the component. The warning means cooperates with airbag deployment means such that when the warning means is in its retracted position, the airbag deployment means is armed and when the warning means is in its withdrawn position, the airbag deployment means is disarmed.

Abstract: A multiposition folding control surface for missiles designed to provide improved launch stability therefor. The control surface can be folded in one of two positions depending upon size and stability requirements, a first folded position for compact carriage with minimal stability requirements, and a second folded position for a less compact carriage with added stability requirements. The multiposition folding control surface comprises a spindle fitting which is attached to the missile, and which is rotatably controlled by a flight control actuator. A center fitting is hingedly attached to the spindle fitting, and provides a nonactuated folding of the center fitting to accommodate more compact missile storage in a shipping container. An actuator housing is hingedly attached to the center fitting, and provides the major aerodynamic surfaces for the control surface.

Abstract: It is possible to improve the hit probability of programmable projectiles by means of this method. For this purpose a predetermined optimal disaggregation distance (Dz) between a disaggregation point (Pz) of the projectile (18) and an impact point (Pf) on the target is maintained constant by the correction of the disaggregation time (Tz) of the projectile (18). The correction is performed by adding a correcting factor, which is multiplied by a velocity difference, to the disaggregation time (Tz). The velocity difference is formed from the difference between the actually measured projectile velocity and a lead velocity of the projectile, wherein the lead velocity is calculated from the average value of a number of previous successive projectile velocities.

Abstract: It is possible to improve the hit probability of programmable projectiles by means of this method. For this purpose a predetermined optimal disaggregation distance (Dz) between a disaggregation point (Pz) of the projectile (18) and an impact point (Pf) on the target is maintained constant by the correction of the disaggregation time (Tz) of the projectile (18). The correction is performed by adding a correcting factor, which is multiplied by a velocity difference, to the disaggregation time (Tz). The velocity difference is formed from the difference between the actually measured projectile velocity and a lead velocity of the projectile, wherein the lead velocity is calculated from the average value of a number of previous successive projectile velocities.

Abstract: A broad-band radio wave absorber including a radio wave reflecting surface, and a plurality of magnetic members provided on the reflecting surface and arranged in columns and rows, each of the magnetic members being composed of a first layer in the form of a square tile or a cross and a second layer superimposed on the first layer and having at least one cylindrical block having a diameter smaller than the width of the first layer. The first layers of adjacent two magnetic members are in contact with each other. When the second layer has a plurality of cylindrical blocks, they are coaxially superimposed in turn in a step wise manner.

Abstract: A projective device especially useful against hollow charge projectiles is formed of a plurality of spaced apart layers inclined obliquely to the main firing direction of the projectiles. A centrally located combination layer consists of two disrupter layers sandwiching a reaction or explosive layer. On either side of the combination layer is a retardation layer. A movably displaceable layer is located on the opposite of one retardation layer from the combination layer and forms the outside surface of the device, while an immovable layer is on the opposite side of the other retardation layer from the combination layer and forms the inside surface of the device. When a hollow charge projectile impacts against the device, the hollow charge spike generated by the projectile is disrupted on its path through the device so that the effectiveness of the spike is seriously impeded.

Abstract: An integrated system and method for guiding an inflight missile during its boost phase to increase the accuracy of the missile flight and increase the probability that the missile reaches its intended target. The system includes four sub-systems that each perform a separate missile guidance function, but that each are integrated to form a single guidance system. The system includes a position rectified velocity wire guidance sub-system for steering the missile to maintain the same trajectory as determined in a prelaunch solution through measuring velocity error at a given position along the path of the missile. The system also includes an ignition delay sub-system for correcting missile position along the flight path by navigating position between burnout of the given missile stage and ignition of the subsequent stage, and modifying the ignition time to correct the missile position after all missile stages are burned.