Abstract: The space debris clearing device of the invention, following launch and placement in or near an orbit considered to be highly populated with debris, is intended to clear the debris allowing safe paths and orbits for space assets. The device is made of a castable, energetic material, and shaped to meet specific clearing requirements. Once in position the device is remotely detonated, and an impulse, caused by the expanding detonation products, is imparted to the debris, pushing the debris into a reentry or earth escape trajectory.

Abstract: An individual mine launcher is designed to pneumatically launch high explve VOLCANO and MOPMS mines to simulate flight and impact typically encountered in field use. Electronic components and controls are used to monitor and initiate the arming sequence of the mine. Two configurations are used with the same pneumatic and electronic controls. The air-launch configuration allows the mine to be launched into the air at various specified testing elevation angles. The control impact configuration shoots the mine into a chamber where the mine hits an impact surface and then falls into a test monitoring area below.

Abstract: In a seeker head assembly in a guided missile, particularly a high-speed guided missile, the seeker head (22) is covered by a dome (28) which is rotatably mounted in the structure and is rotated. The dome (28) is circumferentially surrounded by the structure (10) of the guided missile except for a window section (14). A coolant is supplied to an interspace (46) formed between dome (28) and structure (10) of the guided missile.

Abstract: A guided missile for air to ground deployment having a modular construction which can be readily configured to suit varying deployment roles. The missile comprises a common central fuselage 1, 2, 3 carrying a fuel tank and mounting points for an engine, wings and nose-cone 7. Bolted onto either side of the fuselage are panniers 6a, 6b of variable length and payload capacity. In one embodiment the panniers 6a, 6b carry munitions for lateral ejection through frangile panels. In an alternative embodiment, munitions are mounted in the fuselage and the panniers carry fuel.

Abstract: An electronic fuze package and method includes a left casing comprising a substantially flat left surface having left casing recesses and a right casing comprising a substantially flat right surface having right casing recesses. The combination of the left casing and the right casing defines a fuze casing for the mounting of fuze components. The fuze package also includes plated-on electrical tracks on the left casing, including component connections immediately adjacent to the casing recesses for electrically coupling the fuze components in a fuze circuit. The fuze package can be made of thermoplastic left and right casings which can be epoxy-glued together. Copper can be used for the plated-on electrical tracks.

Abstract: A clip-lock cap for protecting saboted projectiles or penetrators. This cap is formed of several independent segments held together by mechanical clips, the latter being designed to be released from the segments and thus allow dispersal of the segments only when the combined penetrator and cap is exposed to high axial acceleration. It will be understood that because the cap separation from the projectile is achieved through mechanical means, the cap segments can be designed to be as rugged as required to meet rough handling loads and environmental requirements without affecting the reliability or repeatability of the discard process and irrespective of segment material, environmental conditions or projectile spin rate.

Abstract: The present invention relates to a method of disassembling large-caliber combat cartridges, particularly armor-piercing cartridges, including a combustible casing jacket that conically widens in the direction of the projectile, a casing bottom and a casing cover to which is fastened a sub-caliber projectile equipped with a propelling sabot.To be able, on the one hand, to reduce expenditures for the disassembly of such combat cartridges and, on the other hand, to reuse a major portion of the original combat cartridges for the production of corresponding training cartridges, it is proposed to separate the casing jacket as well as the casing cover starting at their outer circumference, in regions having approximately the same, predetermined diameter D1. This diameter D1 here corresponds to the maximum diameter of the component of the new cartridge to be produced later from the disassembled components.

Abstract: A dual mode semi-passive nosetip cooling system for a hypersonic weapon. A cone shaped capsule or pressure vessel is positioned within the nosetip and it is filled with a sublimating material in solid state. The capsule has a nozzle formed adjacent its forward end that directs a steady impingement stream of sublimation material to the back side of the nosetip shell in its stagnation region when the sublimating material is being heated by the surface heat on the nosetip itself. The concept is based on utilizing the advantages of both a subliminating and impingement cooling system designs.

Abstract: Enclosure of reception of electronic components is embarked in a missile. The missile is first fixed to an aircraft carrier and to follow a carried flight, then after being fired, to follow a free flight. The enclosure is located inside of an exterior casing. Sectors sensitive to the acceleration are provided, on this side of a given acceleration, in order to form a thermal bridge between the enclosure and the casing and, beyond the given acceleration in free flight, to break that thermal bridge and to insulate the enclosure from the exterior. In free flight, the electronic components of the enclosure are no longer subject to a source of thermal energy.

Abstract: A munition incorporating a miniature transmitter (25) and a piezoelectric power supply (45) which converts a portion of the kinetic energy of the projectile (20), upon impact, into radio frequency energy and radiates that energy into space. The transmitter (25) can be made in suitable sizes to fit various calibers of ammunition. Different caliber ammunition can be made to radiate different frequencies. The transmitted RF energy allows the point of impact of the projectiles to be located with a high degree of precision. This type of munition may be used in the scoring of air to ground gunnery in training environments by receiving the RF energy at several known locations and determining the point of impact using time of arrival or angle of arrival techniques. Frequency discrimination allows simultaneous scoring of multiple weapons from the same aircraft or from multiple aircraft. The munition may be employed in tactical applications by allowing the fall of fire to be located and adjusted.

Abstract: The detonation wave velocity in a solid explosive body of material, incred by the "channel effect", is further increased by compounding of the "channel effect" and/or by partial shock wave interruption by means of a threaded or rifled passage wall surface in a continuous, open channel arrangement. The high velocity detonation wave can be used to increase the jet velocity of shaped charges.

Abstract: An explosive round is formed by a bundle of fibers made of explosive matel held in peripheral contact with each other within an outer casing. Axially extending channel passages thereby extend between the fibers to conduct shock waves periodically impacting explosive blockage plugs in order to generate auxiliary detonation waves in forward and reverse directions. The auxiliary waves propagated in the reverse direction collide with the original detonation wave in the fibers between the blockage plugs at the locations of axial gaps between the fiber segments so as to reduce peak pressure oscillation.

Abstract: An endothermic cooler (10) for electronic components (16) in, for example, a missile (12) includes an enclosure (14) having a thermally conductive coupling to the electronic component. A source of water in a first compartment (28) is segregated from salts in a second compartment (30). The salts are capable of providing an endothermic reaction when mixed in a water solution. The two compartments are segregated from one another by a membrane or conduit (32). The membrane is pierced by a spike (34-2 or 34-3) through an actuating mechanism (36) and the conduit is opened by a valve (34-4). Formation of the solution provides cooling for conduction of heat from the electronic component through a thermally conductive plate (24) and its fins (26).

Abstract: The invention is directed to apparatus whose weapon efficiency is effected in cooperation via a highly compressed magnetic field, wherein the base magnetic field is maintained or increased beforehand by magnetohydrodynamic generator stages which are operated by propelling charges and/or explosives.

Abstract: A device and method are provided for sealing off an explosive charge compartment in a shell of the type in which the shell includes a shell case at its forward region and an element which is inserted into said shell case to cover an explosive charge and is provided with an outer annular abutment surface abutting against the inner contour of the shell case. The device includes a strand of sealant compound which is applied at least along an edge of the upper end portion of the element covering the explosive charge and a radially expendable ring which is forced by radial flaring against the sealant compound to straddle at least a joint between the edge of the upper end portion of the covering element and the inner contour of the shell case to accurately follow inner contours of the element and the shell case.

Abstract: A soft-recovery projectile having an aft portion, a forward portion and a gas seal mounted between the portions. The aft portion includes a recoverable payload such as projectile components or the like. The forward portion includes a parachute that is attached to the payload and is stored in a housing which is separably attached to the payload. The housing includes an explosive charge which is slectively triggered to cause separation of the housing from the payload and deployment of the parachute. A fin assembly, mounted on the housing, exerts a destablizing moment on the projectile when it is oriented with the fin assembly directed into the flight path. The projectile is launched with the fin assembly as the nose and the payload as the tail. After launch, the destabilizing moment will reorient the projectile into a position where the payload is the nose and the fin assembly is the tail. In this position, the fin assembly exerts a stabilizing moment on the projectile.

Abstract: A pressure responsive and pressure operative device which includes an intrinsically safe detonation circuitry particularly designed for the suppression of explosive situation where the initial indication of a developing explosion and subsequent fire is an increase in pressure within a protected volume which is normally related to a building or other structure. The device includes a directed housing serving as a cannon which holds an extinguishant containing canister which incorporates an explosive charge for producing a rapidly rising pressure within the canister for substantially instantaneous discharge of extinguishant from the canister and instantaneous release of propelling fluid pressure from a pressure supply tank for additional extinguishant propulsion. The unit is operative with only low voltage and pressure thus making the same intrinsically safe.

Abstract: An electronic countermeasure (ECM) simulator which fits into the housing of any actual ECM payload device and substitutes electrical components for the chaff, flares or other countermeasures which are emitted into the environment. The ECM payload simulator electrically verifies firing ability for any ECM dispensing system using a magnetic indicator which sets when the electrical signal required to fire an actual ECM payload device operates properly. The magnetic indicator can be viewed, tested and reset by a ground crew upon return of the aircraft to ground. The magnetic indicator has a parallel resistor so that the aircraft's arsenal inventorying device will indicate an unfired ECM payload device. An optional radio frequency (RF) transmitter may be substituted for the magnetic indicator to send coded transmissions to a radar site while in flight.

Abstract: A dual purpose fuze for a projectile which can activate a quantity of material selected from a group including high explosive, low explosive, propellant and pyrotechnic compounds. The fuze includes a charge holder having a socket therein facing the quantity of material to be activated. A fuze charge located in the socket has a depression in it so formed as to cause the fuze charge to explode in a jet directed outwardly from the socket of sufficiently high energy to activate a high explosive in a high explosive projectile, the fuze charge being sufficiently small to prevent rupture of containment for a propellant in a cargo projectile. The fuze further includes mechanisms for arming and detonating the fuze charge as well as for activating detonation. A safety mechanism is provided to prevent premature detonation of the fuze charge.

Abstract: The invention relates to a protective cover which is complementary in shape to and is mounted on a sensing head such as that of a missile.The protective device performs a dual function in that it is resistant to abrasion by impacting material such as dust, sand or ice, while at the same time being transparent to incident electromagnetic radiation which the sensing head is adapted to sense. The protective device may be moulded from a thin sheet (0.2 mm thick) of polytetra-fluoroethylene when this radiation is infrared.

Abstract: A submunition unit for a spin stabilized carrier projectile (1), with the submunition unit including an antenna disposed at the nose of its casing (7), and with the antenna (5) being covered by a protective cover (6). The casing (7) and the protective cover (6) are provided with respective axially overlapping collars (8, 9) which are each provided with respective opposed circumferential grooves (14, 15) to form an annular recess to accommodate an elastic securing ring (16). The securing ring, which is normally positioned within the innermost of the circumferential grooves, expands under the influence of centrifugal forces to connect the casing and protective cover together in a form-locking manner.

Abstract: A separable nose fairing assembly includes a forward, massive portion slidably coupled to a rearward, light portion. Forward sliding movement of the massive portion relative to the light portion is limited by a stop. An explosive actuator is operable to drive the forward portion forwardly until it reaches the stop, whereupon the momentum transferred to the rearward portion is sufficient to pull it off the missile. Due to the high ballistic coefficient of the assembly it follows a ballistic trajectory different from that of the missile, thus minimizing the possibility of damage to the missile.

Abstract: The invention relates to an underwater mine or decoy which should lie on the ocean bottom or which has buoyancy characteristics. The mine or decoy is made up of at least an expandable material and a foldable, preferably webbed shell which determines the external form of the mine. The disadvantages associated with the storage, transportation and stowage of heavy mines of fixed shape in submarines, small ships and aircraft are thereby avoided. It is possible to manufacture decoys or mines rapidly and economically, and they may have variable magnetic and/or sonar reflecting properties. The release of the decoys or mines from submerged submarines via forceful ejection is possible.

Abstract: A simulation decoy whose position and structural purport are determinable by infrared detection means is disclosed, which comprises a multi-dimensional display body containing a sufficient quantity of combustible carbon to provide a controlled burning for a predetermined length of time, means to initiate ignition of said carbon to produce sustained burning of said multi-dimentionsal display body to activate such simulation decoy for infrared detection, and specific metal coated fibers to provide radar-detection capability. It may be utilized to mimic mobile structures such as land-based vehicles, marine vehicles, or aircraft, as a two-dimensional or three-dimensional display, providing an infrared and radar signature useful as a defensive countermeasure in warfare or other battlefield conditions.

Abstract: A decelerator device for stopping a high energy projectile, including an elongated tube of a predetermined length and having an inlet and a terminal end to define an axial path for the projectile. The device includes a piston for moving on the axial path and having a cone shaped leading edge. Further included is a fluid container for filling the tube with a fluid to be displaced by movement of the piston through the tube and for collecting the displaced fluid as it is displaced. Also included in the tube are a plurality of port like slots for displacing fluid from the tube radially as the projectile enters the tube. The ports located proximate the inlet portion of the tube are of larger area, and become progressively smaller toward the terminal end.

Abstract: Testing apparatus for testing and evaluating the performance of laser seeking warheads for missiles under simulated weather conditions. The testing apparatus includes a support for supporting the warhead seeker and a laser for generating a laser beam, and for directing it towards the seeker. The laser beam extends through a diffusion screen which is interposed between the seeker support beams and the laser for diffusing the laser beam. A collimating lens is interposed between the diffusion screen and the seeker support for collimating the diffused laser beam and for directing the collimated laser beam onto the warhead seeker. A background illuminator is provided with an operating position between the diffusion screen and the collimating lens for simulating background lighting comparable to various weather conditions. The intensity of light generated by the background illuminator is varied by either individual rheostat controls or by a microprocessor.

Abstract: The invention relates to a projectile having an interior space in which disposable payloads and/or electronic components are arranged, and which are of a type intended to have an extended lifetime. To protect the interior components from corrosion, the interior space is filled with a protective gas, for example, argon, nitrogen or hydrogen, or a mixture of these gases. The protective gas may be present in the interior space at a greater than atmospheric pressure of, for example, three bar.

Abstract: The invention concerns a guided munition, fired from a launching system with a cannon effect. This munition comprising sub-assemblies is supported, during acceleration in the cannon, by a peripheral casing which rests on the first sub-assembly of the munition placed at the front of the munition and is fixed to an ejectable sub-assembly placed at the rear of the munition. The weight of this casing is necessary to withstand the forces due to acceleration and it enables the range of the munition to be increased during the ballistic phase. During the transition from the ballistic phase to the guided phase, the ejectable sub-assembly is ejected, taking with it the casing which thus frees the airfoil surfaces to open out. The casing thus positioned also provides sealing and protection of the sensitive parts and rigidity of the whole of the munition.

Abstract: An electrically controllable pyrofuze pin device for ordnance device actiion which functionally replaces the mechanical barrier and arming wire or other rigid and removable means used to provide ordnance device activation. The device includes a pyrofuze pin, a connecting ignitor transfer charge, and ignitor, and electrical terminals to provide power from an external power supply, and a weatherproof housing. When electrically activated the pyrofuze pin is reduced to molten by-products which functionally eliminate the mechanical barrier and permits the activation of the ordnance device.

Abstract: A simulation decoy whose position and structural purport are determinable by infrared detection means is disclosed, which comprises a multi-dimensional display body containing a sufficient quantity of combustible carbon to provide a controlled burning for a predetermined length of time, and means to initiate ignition of said carbon to produce sustained burning of said multi-dimensional display body, to activate such simulation decoy for infrared detection. The simulation decoy of this invention may employ metal coated fibers with the combustible carbon to provide radar-detection capability and may be utilized to mimic motive structures such as land-based vehicles, marine vehicles, or aircraft, as a two-dimensional or three-dimensional display, providing an infrared and radar signature useful as a defensive countermeasure in warfare or other battlefield conditions.

Abstract: The present invention relates to an apparatus and method for clearing the uling black powder residues deposited on the electrical connectors of electrically detonated munitions. A female connector is provided with a recurved lanced outer spring clip which automatically scrapes off the residue on an insulator and contact surfaces of a male bipolar connector plug when the two connectors are rotated with respect to each other.

Abstract: Method for air dispersion of filamentary type organic material from an initial compressed form comprising a component of a propellant and/or air-activated shell-like structure.An invention comprised of a plurality of compressed filamentary organic materials, a vehicle for storing and dispersing said materials and a method for effecting air dispersion of such materials.

Abstract: A marker that can be used to increase the precision and efficiency of the guidance of homing heads towards a target. In order to mark targets on land, this marker has: an ovoid casing provided with a firing fuse, and a magnet and a coil for detecting flux variations during an impact on a magnetic surface. Inside the casing there are: a battery, an electronic control and transmission circuit, and a cylinder of thrustors connected to one another by pyrotechnical delaying mechanisms. The cylinder opens out on to a single nozzle which is inclined with respect to the axis of the casing. After impact on the ground, the electronic circuit controls the firing of the first thrustor. The other thrustors cause leaps until the marker gets fixed to a magnetic surface, through the magnet.

Abstract: A projected grenade simulator test circuit is used for checking the operaity of a grenade launcher system by exactly duplicating both the physical and electrical characteristics of an actual grenade.

Abstract: A method for manufacturing explosive logic circuit trails using conventio silk screening techniques. Silk screening is used to build up both the explosive trail, as well as the inert substrate. This is accomplished one layer at a time onto a circuit base material. The explosive logic circuit herein is reliable, cost efficient and relatively easy to produce. The invention herein encompasses both the method of manufacturing said explosive logic circuits and the circuits themselves.

Abstract: A connector for a bomb includes a case capable of covering a projected opening of the bomb; a case fastening device for fastening the case onto the bomb by utilizing an outer circumferential recess of the projected opening; a handle having a shaft portion and a handle portion with the shaft portion being arranged to rotatably and movably pass through a top wall of the case and the handle portion being positioned outside the case; a threaded plug retainer which is fixed to an end of the shaft portion and is detachably engaged with a threaded plug screwed onto the projected opening; a first sealing member for sealing between an end portion of a side peripheral wall of the case and the bomb; and a second sealing member for sealing between the shaft portion and the case.

Abstract: A pyrofuze ordnance arming system, for air delivered ordnance, which provs a removable physical barrier to prevent the premature operation of ordnance device arming activation systems. An electrothermally initiated, alloyably removable pyrofuze pin extending from a pyrofuze device is employed as a physical barrier in an arming system to replace the conventional arming wires. The system increases safety and reliability for ordnance arming while decreasing the complexity and labor involved in preparing and loading ordnance on aircraft.

Abstract: A pyrotechnic composition containing from 55 to 65 percent by weight Fe.s2 O.sub.3 powder, 15 to 25 percent by weight aluminum powder, 5 to 15 percent by weight Ba(NO.sub.3).sub.2, 2 to 3 percent by weight MoS.sub.2 and 5 to 10 percent by weight Viton A (a copolymer of vinylidene fluoride and hexafluoropropylene) is disclosed as being useful in the destruction of metal oxide-semiconductor chips.

Abstract: A protective door assembly is disclosed which will cover missile altitude control system engines during storage and launch while still being easily jettisoned when the ACS engine is fired. The titanium door attaches to the missile skin by a hook on it's lower edge and by a tapered boss which attaches to the skin and fits into a tapered hole near the door upper edge. Behind the door, the ACS engine nozzle is surrounded by a seal housing which prevents engine gases from escaping into the body of the missile and causing a pressure buildup when the engine is fired. At pressures between 35 and 60 psi, the door retainer screw fails in tension and the door is blown off.

Abstract: An electrically controllable "Pyrofuze" pin device for ordnance device acation which functionally replaces the mechanical barrier and arming wire or other rigid and removable means used to provide ordnance device activation. The device includes a "Pyrofuze" pin, a connecting ignitor transfer charge, and ignitor, and electrical terminals to provide power from an external power supply, and a weatherproof housing. When electrically activated the "Pyrofuze" pin is reduced to molten by-products which functionally eliminate the mechanical barrier and permits the activation of the ordnance device.

Abstract: A device mounting a fuze in the casing of an ordanance item and providing r pop-out of the fuze to reduce cook-off hazard when the casing is heated. The device has an outer sleeve fixed to the casing, an inner sleeve slideably mounted in the outer sleeve and receiving the fuze, and a resilient element urging the inner sleeve and the fuze from the casing. The sleeves are retained together at normal temperature by a layer therebetween of material which melts at a higher temperature to release the inner sleeve and fuze.

Abstract: An ordnance venting system is provided to reduce the danger of explosion in rdance items exposed to fires and includes an ordnance item having a number of holes in the ordance casing, each hole being covered by a bimetallic patch which will deform when subjected to high temperatures, and each patch being attached by means such as brazing, soldering or adhesive bonding.

Abstract: An ordnance venting system is provided to reduce the danger of explosion in rdnance items exposed to fires and includes an ordance item having a number of holes in the ordnance casing, each hole covered by a metallic patch having a different differential expansion in relation to the casing to provide shearing forces when subjected to high temperatures, and a means of attaching the patches to the casing over the holes.

Abstract: A system for powering and communicating with a mine or mine simulator, involving magnetic induction coupling between a powered search unit with a resonating primary inductance coil and a secondary inductance loop in the mine device. The current in the secondary loop is rectified in the mine device to provide dc power. The magnetic induction frequency can be in the range from 40 kHz to 1 MHz. The search unit can resonate sequentially or simultaneously at different frequencies, and rectification of the different frequencies in the mine device can provide information to the mine device. Feedback to the search unit can be by the mine device modulating the impedance of its secondary loop, for instance at an audio frequency 1/10th of the frequency of the induction coupling, and by detecting in the search unit the corresponding change in the reflected impedance. A mine device can be armed or disarmed, and report on its status when queried by the search unit coming sufficiently close to the mine device.

Abstract: A mechanism for upgrading a missile to be effective against reactive armor. The invention includes an adaptor (11) for mounting a probe module (10) with a warhead (13). The probe module has a charge in its extensible tip. A faring (12) over the five inch warhead reestablishes the aerodynamics of the missile.

Abstract: The invention is a carrier projectile 10 having a safety venting system wh prevents expulsion of the projectile cargo during accidental or inadvertent initiation of the expulsion charge 21. The venting system comprises a collar which closes vent holes when the projectile is fired. The normal activation sequence of the carrier projectile is firing to a predetermined range or time, activation of the expulsion charge thereby bursting open the carrier shell, and dispensing of the cargo. The venting system incorporated into the present invention precludes bursting of the carrier shell, even if the activation of the expulsion charge occurs, unless the vents have been closed by the actual firing of the projectile. The venting system provides a safety feature in the event that the projectile is subjected to fire or other thermal stress and in the event of a hot gun misfire the collar is operated by either angular acceleration or longitudinal acceleration.

Abstract: A lane marker preferably for delivery by a CATFAE weapon, has a mechanical imed device which is positioned and rides in the rear section of the CATFAE weapon as it is launched to a specified position on the ground. At first contact of the CATFAE with the ground, the lane marker is ejected vertically a short distance away from the ground and then falls onto the ground. On the ground the lane marker attitude is controlled for effective employment. Spring-biased probes deploy the makers which typically comprise two flags and two chemiluminescent lights to mark the impact point of the CATFAE. The two chemiluminescent lights are activated mechanically by cloud detonation overpressure prior to deployment of the spring-biased probes.

Abstract: A detonating cord transport package wherein detonating cord is installed on a plurality of separator-support members so as to provide crossover locations at frequent intervals at which crossover locations there is incorporated means for stopping any detonation that occurs, with the result that such detonation will be confined to a relatively short length of detonating cord and will also be confined to the container in which the detonating cord transport package is disposed.

Abstract: The invention is directed to a Pyronol torch and holder device for provid quick and efficient attachment of the torch to a barrier target (flat, curved, or irregular shape) that is made of steel or magnetic steel alloys. The device provides for attachment to the target and for holding a cutting torch containing pyrotechnic material at a predetermined standoff distance from the surface of the target for proper operation of the torch and for permitting escape of products of combustion to minimize liftoff forces on the holding device tending to lift it from the target to which it is attached.

Abstract: An improved parachute recovery system for a gun fired projectile is discld. The projectile has a nose, a payload and a base section. The base section has a hollow cylindrical parachute cannister which is separated from the base section by rearward motion of an internal piston which is actuated by expulsion gas pressure initiated by a time fuze. The parachute cannister is thereby exposed and jettisoned to cause inflation of a parachute attached to the base section so that the parachute floats down in a nose-deployed projectile position for a soft landing and recovery. Also disclosed are alternative embodiments of a projectile base-deployed parachute recovery system.