Abstract: A device for safely attaching sections of a rocket motor is disclosed. The device is constructed such that if the temperature of the rocket motor is elevated to the point where ignition of the propellant within the rocket motor becomes a significant danger, the device allows the sections of the motor to disengage. The device comprises a bimetallic retaining ring which either contracts or expands in diameter upon heating. The retaining ring is positioned in such a manner as to lockingly engage two sections of the rocket motor at normal temperatures. At elevated temperatures, however, the expansion or contraction of the bimetallic retaining ring causes the sections of the motor to unlock from one another, such that if the propellant ignites the sections will disengage and the rocket will be rendered non-propulsive.

Abstract: An ammunition propellant temperature measuring assembly comprising a first emperature measuring device for determining at least two surface temperatures of a round of ammunition and for transmitting a first signal indicative of the surface temperature, a second temperature measuring device for determining ambient temperature in a storage area for the ammunition and for transmitting a second signal indicative of the ambient temperature, and computer apparatus for receiving the first and second signals and a temperature profile for the ammunition, and adapted to compute therefrom a propellant temperature of the round.

Abstract: An ammunition temperature emulating system is provided for use in a tank ch carries ammunition. The temperature of the ammunition (which comprises liquid propellant) is needed to be known for firing accuracy. The temperature is indirectly approximated by measuring the temperature of the wall of the chamber in which the ammunition is stored, using a simulating thermal insert. The system includes a gauge having a sensor bulb, a vacuum bottle having a cavity receiving the sensor bulb and receiving the simulating thermal insert.

Abstract: A single-use firing indicator device for a projectile having a hollow rear extension includes a stopper and an indicator member. The stopper is shaped to at least partially cover the rear extension of the projectile. The indicator member is connected to the stopper and may secure the firing indicator device to the projectile. Removing the firing indicator device to prepare the projectile for firing requires permanently deforming the indicator member. As a result, the firing indicator device reliably conveys the firing status of the projectile without requiring costly modification or added parts.

Abstract: An intermetallic thermal sensor comprised of a hermetically sealed housing containing alternating layers of electronegative and active metals or their alloys in intimate contact. The layers may be wafer or washer-shaped. If washer-shaped, the holes in the wafers are aligned with each other to create a well within the housing and any extension thereof. A tubular-shaped liner extends into the well and may contain an energetic composition such as BKNO.sub.3. In one embodiment a thermite charge in the sensor can be ignited for venting applications. The active metal and electronegative metal and their alloys are selected so that when the melting point of one or both metals, alloys, or metal and alloy pairs has reached its or their melting point in response to external heat within a design range of the sensor, a vigorous exothermic reaction occurs to initiate a gas-producing reaction in the well or to ignite the thermite for operation of a cook-off mitigation system.

Abstract: An initiation device includes a primer-container system placed inside a casing box able to move from a safety position to an armed position through the action of a motor. The system is immobilized in its security position by at least one lock that is released by a shape memory actuator when the surrounding temperature rises above a given value.

Abstract: An air bag system (10) includes an inflator (14) containing ignitable gas generating material (60) which, when ignited, generates gas for inflating the air bag (12). The system (10) further includes a collision sensor (96), a first actuator assembly (64) and a second actuator assembly (62). The collision sensor (96) senses a predetermined amount of vehicle deceleration which is indicative of a collision, and provides a collision signal upon sensing such deceleration. The first actuator assembly (64) ignites the gas generating material (60) in response to the collision signal. The second actuator assembly (62) ignites the gas generating material (60) when the ambient temperature of the inflator (14) reaches a predetermined elevated level. The second actuator assembly (62) includes a bi-metal disk (112) which deflects from a concave shape to a relatively convex shape when the ambient temperature increases to the predetermined elevated level.

Abstract: The joint construction comprises a coupling ring slidably received in a motor tube connected to the front end of the military rocket motor. The coupling ring is formed with longitudinal slots alternating with flexible fingers having locking projections engageable with a locking channel and an adjacent locking flange within the tube. An adapter ring is connected to the warhead by first screw threads and is adapted to be connected to the coupling ring by second screw threads including external threads on the adapter ring and internal threads in the coupling ring. The adapter ring has a reduced tapered end portion for receiving a wedging tapered expansion ring made of a eutectic metal alloy having a low melting point. As the second screw threads are engaged, the expansion ring flexes the fingers outwardly by a wedging action and causes the projections to interlock with the channel and the flange.

Abstract: A rocket motor or other gas generator the case of which is ventable at a predetermined temperature substantially greater than the ambient temperature range for storage and operation thereof and substantially less than the auto-ignition temperature of gas generant material contained therein so as to prevent catastrophic propulsion or burst in case of fire. In order to provide such venting without requiring any shaped charges or other auxiliary system for that purpose at all, the case is composed of a matrix-impregnated fibrous material wherein the fibrous material is characterized by having a melting point which is substantially higher than the ambient temperature range and which is substantially lower than the auto-ignition temperature of the gas generant material. The matrix material is preferably actinic radiation-curable at a temperature which is substantially lower than the melting point temperature of the fibrous material.

Abstract: A burster for rupturing a casing containing an active explosive or propelt material of an ordnance device to prevent cook-off has an inert and thermally expansible material in an enclosure defined by a wall fixed to the casing so that thermal expansion of the inert material exerts on the wall a force to rupture the casing and vent the active material. The wall may have a stress riser groove to promote rupture at a predetermined location on the casing, and the volume of the inert material at ambient temperature may be less than the volume of the enclosure so that rupturing force is not exerted until a selected venting temperature is approached.

Abstract: Ignition means being provided to ignite pyrotechnic materials, this ignition is produced by the activation of these ignition means. As long as the ignition means have not been activated, the casing is maintained firmly attached to a closing plug only by a first set of locking means so that at pressures within the casing in excess of a given pressure, the plug is ejected from the casing. As soon as the ignition means have been activated, the casing is maintained firmly attached to the plug by a second set of locking means at pressures within the casing in excess of the given pressure.

Abstract: A stator jacket (12) and a stator lining (22) of elastomeric material together form a tubular pump stator (10) the ends (20) of which are connected to a connecting piece (36) of a casing portion (32, 34) each. The stator jacket (12) has at least one parting area (14) extending throughout its length. This and the region of the stator lining (22) located radially inside thereof as well as the junctions of the connecting pieces (36) with the stator jacket (12) are designed such that the pump stator (10) will burst in at least one parting area (14, 16) when a predetermined positive internal pressure is exceeded. This provides pressure relief before a risk of explosion can develop when explosives are being conveyed.

Abstract: A heat sensitive case/nozzle interface is provided for an insensitive propellant-loaded munition such that the interface loses its structural integrity when high external heat is applied. The joint between a rocket case housing a rocket motor and nozzle forming the interface is received by an internal spring retainer positioned in a first groove in the case or nozzle in cooperation with a fusible material housed in an aligned second groove in the nozzle or case, respectively. A plurality of aligned openings extend into said first and second grooves. When the rocket is exposed to a high ambient temperature greater than melt temperature of the fusible material but lower than the auto-ignition temperature of the rocket, the fusible material melts and is forced through said holes by the spring retainer permitting the nozzle to separate from the case rendering the rocket motor safe if it auto-ignites.

Abstract: A composite/metal hybrid rocket motor case made by rolling sheets of continuous, unidirectional fiber reinforcement pre-impregnated with an uncured, thermoset or thermoplastic resin about the mandrel using a tube rolling machine to form a liner having discontinuous layers of fiber reinforcement. The liner is inserted into a metal shell configured with elongated slots. A mold is placed around the shell with a bladder placed within the liner. The bladder within the mold is then pressurized to force the liner against the metal shell while the contents of the mold are heated. As the liner cures, it bonds to the shell. Fins, launch lugs, domes and bulkheads may be attached to the metal shell by known attachment methods.

Abstract: The present invention relates to an effective and explosive munition component of low vulnerability, consisting of a casing 1 containing an explosive charge consisting of an internal layer 2 made of plastic bonded explosive in which the filler contains at least one organic nitrated explosive, coated with a peripheral adjacent coaxial layer 3 made of less sensitive pyrotechnic composition consisting of a filled polymeric matrix in which the filler contains at least one inorganic oxidizing agent or an organic nitrated explosive.The interface between the two layers 2 and 3 is of star-shaped cross-section.The invention also relates to the process for obtaining a fragmentation effect by detonation of the layer 2, reaction of the layer 3 followed by bursting of the casing due to the pressure of the gases formed.

Abstract: The invention is a propellant rocket motor case designed to meet insensitive munitions requirements comprising a propellant surrounded by a case having slots therein, and a wrapping around the case, the wrapping comprising a load bearing material which can withstand the hoop load on the case during normal firing of said rocket, the material also having the characteristic of losing strength or melting at undesired temperatures above normal storage temperatures, but below the autoignition temperature of said propellant, so that during undesired high storage temperatures the propellant will exhaust any subsequently generated gases, due to any subsequent propellant burning, by venting through said slots thereby avoiding any explosion or undesired operative one-way thrust.

Abstract: A thermal battery activated by external heat comprising an anode, e.g. cosed of a lithium-aluminum alloy, a cathode, e.g. composed of iron disulfide, and an electrolyte, e.g. a lithium chloride-potassium chloride eutectic, the electrolyte being inactive at ambient temperature but being activated by melting at a predetermined temperature when exposed to external heating. The battery can be used as a sensor or to ignite pyrotechnic and power electronic devices, in a system for reducing the hazard of ordnance exposed to detrimental heating. A particular application is the use of the battery to activate a squib to function in conjunction with one or more other components, to vent an ordnance case, preventing its explosion in a fire.

Abstract: A tailorable, roll-bonded, insensitive munitions motor case and method of production. The motor case comprises a sheet of fiber reinforced thermoplastic, thermoset or other suitable material rolled to form a case with a tubular configuration having at least one layer of material, and a coating of adhesive on at least part of said sheet for bonding the sheet to itself for maintaining the tubular configuration. The adhesive has a bond-strength breakdown temperature which is below the autoignition temperature of the housed propellant, thereby enabling the case to separate and un-roll when the breakdown temperature is reached to preclude dangerous propellant pressurization within the case. The method of production includes the steps of applying an adhesive to the sheet, rolling the sheet around a cylindrical tool to form a tubular case having at least one layer, and curing the case. Preferably the case is cured while on a tool which has a coefficient of thermal expansion which is greater than that of the sheet.

Abstract: An igniter which is triggered by a thermocouple for detonating an explosive material for forming an opening in a rocket motor case to render it non-propulsive in the event of a fire dangerously close thereto or for any other suitable purpose. The bridge therefor is preferably a suitable semiconductor bridge for handling a reduced amount of electrical energy which may be provided by the thermocouple. The thermocouple may be a plurality of pairs of dissimilar metal layers or foils alloyed together and the pairs connected in series.

Abstract: A thermally activated case venting safety apparatus is used to minimize the otential for detonation of a warhead or other encased explosive when such item is subjected to excessive thermal environments. An aft end closure plate to a warhead casing is secured using an expandable snap ring with a temperature activated releasing mechanism. The snap ring is expanded using a caliper device with an adjustable slide assembly which adjust the snap ring to the required dimensions. An eutectic solder plug or similar plug is attached to the bottom base of the adjustable slide assembly and holds the snap ring in the expanded position. The plug will melt at a predetermined temperature and thus allow the expandable snap ring to retract. Once the snap ring has retracted, the closure plate will be ejected due to the internal case pressure and the warhead case will vent.

Abstract: Controlled venting of combustion gases from an explosive material encased in a shell, as used in ordnance constructions such as rocket motors, warheads and bombs, is achieved by affixing a composite solid mass to the shell casing at a preselected location presenting low risk of damage to surrounding equipment or personnel. The solid mass is in two portions, the first being an ignition mix (in direct contact with the shell) which ignites at a temperature of 400.degree. F. to 600.degree. F. to react exothermally. The second is a reaction mix ignitable by the energy released by the ignition mix to itself release sufficient energy to degrade the metallurgical structure of the case. With the case thus weakened at a localized point, the case will rupture preferentially at that point upon an interior pressure buildup, and explosion of the entire case can be avoided.

Abstract: A rocket motor or other gas generator the case of which is ventable at a predetermined temperature substantially greater than the ambient temperature range for storage and operation thereof and substantially less than the auto-ignition temperature of gas generant material contained therein so as to prevent catastrophic propulsion or burst in case of fire. The venting is provided by memory metal members which are interleaved between plies of matrix-impregnated fibrous material in the case and which have a transformation temperature which is substantially higher than the ambient temperature range and substantially lower than the auto-ignition temperature and characterized by a change in shape when heated to a temperature above the transformation temperature.

Abstract: An ordnance or munition casing is described which comprises a hollow outer casing having a shock attenuating inner liner made from successive layers of material of inwardly decreasing acoustic impedance. The inner liner reduces the sensitivity of the munition to sympathetic detonation and cookoff. Also described is an attenuation barrier made from a layer or layers of less detonation sensitive explosive material. The layers of less detonation sensitive material are preferably arranged in successive layers of outwardly decreasing detonation sensitivity. The same layers may combine sequenced acoustic impedance and detonation sensitivity. The layers may be made of material compounded with flaked or granular materials to provide preselected acoustic impedances. A coating for desensitizing the outer surface layer of a main explosive charge is also disclosed.

Abstract: A spherical warhead is disclosed which yields a greater than 120.degree. ped charge of preformed fragments and which further permits non-destructive cook-off of explosives to prevent undesirable detonation.

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: 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: 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: 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 metal cup encloses layers of armoring material to enhance the penetration esistance of a guided missile warhead to mechanical countermeasures. A layer of ceramic material is inserted in the cup followed by the insertion of at least one pair of layers consisting of a layer of metal backed by a layer of polymethylmethacrylate. The metal cup is attached to the forward end of a missile warhead section and the exterior of the cup is conformal with respect to the exterior of the warhead section. The layered materials act to blunt or break incoming projectiles, absorb their kinetic energy, and prevent their penetration into the interior of the warhead.

Abstract: A housing for the protection of explosive charges comprises several layers of different compositions surrounding the explosive charge. The successive layers have alternately a high and a low shock wave impedance, where further the outermost layer has the lowest melting point and the melting point increases toward the innermost layer.

Abstract: A method and means for sealed joinder of case and cap members of a capsular shaped charge wherein opposing frustoconical shoulders are formed in adjacent walls of a case and cap and a resilient ring is retained therein to hold the case and cap in operative assembly and an elastomeric ring is positioned in a groove in the case member whereby it is under compressive deformation between the case and cap members when joined to seal the shaped charge from external pressures and fluids while allowing relative rotation of case and cap; wherein increasing external pressures, as in the well bore, will increase the sealing effect and strength of joinder of the assembly.

Abstract: A method and means for sealed joinder of case and cap members of a capsular shaped charge wherein mating grooves are formed in adjacent walls of a case and cap and a resilient O-ring is compressively retained therein to hold the case and cap in operative assembly to seal from external pressures and fluids while allowing relative rotation of case and cap; wherein increasing external pressures, as in the well bore, will increase the sealing effect and strength of joinder of the assembly.

Abstract: A payload projectile including a carrier body having an ogival region in which a receptacle for an ejection charge is provided. A perforated disc is seated immediately in front of the receptacle and a lifting ring screw closes an opening in the carrier body at the forward tip of the ogival region. A chamber, reserved for an igniter, is defined between a rear face of the screw and a front face of the disc and has radial dimensions wider than those of the seat of the disc so that the disc is movable forwardly toward the screw peripherally unimpeded in the chamber.

Abstract: An enabling device 24 for a gas generator 42 of a forced dispersion munitions dispenser 10 includes a housing 58 in which and formed a bore 60, an outlet lead 88 and a detonator opening 68 in which is positioned an electrically initiated detonator 70. A piston 62 is located in the bore 60 and has a disabled position and an enabled position. A safety groove 64 is formed in the outer surface of the piston 62, and a safety passage 72, a safety aperture 74, 75 and a transfer lead 86 are formed in the piston 62. A gas generator 42 containing a quantity of pyrotechnic material 84 is mounted on the housing 58. The gas generator 42 is provided with a safety outlet 46, 47 and an inlet lead 44.

Abstract: A unitary device for venting a rocket motor of an ordnance item having a warhead comprises a circumferential belt containing a cutting explosive charge and constructed for removable mounting around a housing of the rocket motor, and an activating device having a casing permanently connected to the belt. The activating device further includes, in the casing, a striker for movement therein, a spring located and operatively associated with the striker for urging the striker toward the primer from a rest position, and a latch for retaining the striker in said rest position, said latch including a part of eutectic alloy normally opposing movement of the striker and becoming ineffective above a predetermined melting temperature.

Abstract: A general purpose aerial bomb and a thermoplastic liner therefor consisting essentially of a melt blend of polypropylene and polybutene.

Abstract: A carrier shell for secondary projectiles having a shell casing, a plurality of secondary projectiles within the casing, an explosive dispersal charge for dispersing the projectiles and a safety device having a body closing a venting aperature in the casing. A first mechanical connection secures the body to the casing and yields on detonation of the charge before firing to vent any explosion before firing without dispersing the projectiles. A second mechanical connection is moved in response to firing to a condition preventing venting.

Abstract: An arming fuze for ordnance type munitions having but one movable part comprising a solvent desensitized liquid explosive contained in a ported (ventilated) cavity that is normally sealed by a sleeve. Upon movement of the sleeve and exposure of the liquid explosive within the cavity to the air, the liquid explosive loses a volatile solvent, the desensitizing agent, and becomes progressively more sensitive. A first embodiment is that of an inertia armed nose fuze for a projectile wherein the desensitized liquid explosive is enclosed in the cavity in a porous solid matrix. Upon rapid acceleration, as when the projectile is fired, the sleeve undergoes set-back thereby exposing the porous matrix to a violent slip stream of air and to a strong desiccating action. The liquid explosive rapidly loses solvent to the air, rapidly becoming more sensitive whereby it is impact sensitive by the time impact on the target occurs.

Abstract: Positive rocket motor pressure hull venting in the case of deck fires is vided by placement of thermite masses at spaced locations on the interior of the hull. Small cylindrical masses as well as strip formed masses are employed. The thermite mass includes a small amount of structurally formed aluminum as well as the conventional powdered aluminum.

Abstract: This hand grenade comprises a timer for preserving the user's safety when throwing the missile by breaking the pyrotechnic train of the fuse a stabilizing system utilizing the concurrent effects of a weighted ogive and a spread-out empennage adapted when released and operative to brake the missile by aerodynamic effect, thus improving the efficiency of the missile when striking with a low incidence a horizontal surface such as the roof of an armored vehicle. The fins of the empennage are released when removing a safety pin, thus causing the missile to be stabilized in a substantially vertical axial position.

Abstract: An arming fuze for ordnance type munitions having but one movable part comprising a solvent desensitized liquid explosive contained in a ported (ventilated) cavity that is normally sealed by a sleeve. Upon movement of the sleeve and exposure of the liquid explosive within the cavity to the air, the liquid explosive loses a volatile solvent, the desenistizing agent, and becomes progressively more sensitive. A first embodiment is that of an inertia armed nose fuze for a projectile wherein the desensitized liquid explosive is enclosed in the cavity in a porous solid matrix. Upon rapid acceleration, as when the projectile is fired, the sleeve undergoes set-back thereby exposing the porous matrix to a violent slip stream of air and to a strong desiccating action. The liquid explosive rapidly loses solvent to the air, rapidly becoming more sensitive whereby it is impact sensitive by the time impact on the target occurs.

Abstract: An enclosure for a warhead case which prevents a high order detonation of e warhead due to inadvertent initiation from physical, bullet, fragment impact, fire exposure or other factors causing a pressure buildup in the case. The warhead explosive is assembled in a hollow cylindrical warhead case having an open end and a closed end. An enclosure plate is positioned in the open end to close off the warhead in the case. The enclosure is circular and provided with a first plurality of radially extending apertures. The warhead case is provided with a second plurality of radially extending apertures which are positioned to coincide with the aperture in the enclosure plate. A plurality of pins are press fit into the case apertures so as to extend into the enclosure plate apertures and attach the enclosure plate to the warhead case.

Abstract: An improved booster construction having a metallic covering with a plural of apertures therein encases a booster charge which, in turn, is encased in a nonmetallic cup having a low temperature melting characteristic permitting the booster charge to expand during thermal cook-off to prevent reaching critical temperature pressure relationships.

Abstract: An arming fuze for ordnance type munitions having but one movable part comprising a solvent desensitized liquid explosive contained in a ported (ventillated) cavity that is normally sealed by a sleeve. Upon movement of the sleeve and exposure of the liquid explosive within the cavity to the air, the liquid explosive loses a volatile solvent, the desensitizing agent, and becomes progressively more sensitive. A first embodiment is that of an inertia armed nose fuze for a projectile wherein the desensitized liquid explosive is enclosed in the cavity in a porous solid matrix. Upon rapid acceleration, as when the projectile is fired, the sleeve undergoes set-back thereby exposing the porous matrix to a violent slip stream of air and to a strong desiccating action. The liquid explosive rapidly loses solvent to the air, rapidly becoming more sensitive whereby it is impact sensitive by the time impact on the target occurs.

Abstract: Within a cylindrical container or canister, closed at both ends by a respective cover member, there is located a flare or illuminating rocket. For firing the flare rocket it is sufficient to remove the rear cover and by pulling at a tear line there is activated a tear ignition device or fuze. The ignited flare rocket then pierces the front cover member. This front cover member preferably possesses a ring-shaped or annular reference fracture location which subdivides the cover member into a disk-shaped inner portion and a ring-shaped outer portion.

Abstract: A solid propellant rocket motor comprising a motor case, solid propellant and at least one end closure, wherein at least one end closure is connected to the casing by at least one fusible connector which melts at temperatures below those that will cause autoignition of the motor but does not melt during normal propulsion, so that the end closure releases before the antoignition and is retained in place during normal propulsion.