Abstract: A reciprocating bolt assembly has delayed blowback and a firing pin block. Features prevent out-of-battery firing, when the bolt assembly is not fully engaged to the firing chamber or barrel face, a movable member within a bolt body functions as a blocking member that blocks the firing pin and prevents the firing pin from striking a cartridge. In embodiments, the firing pin has two stop portions that the movable member can engage depending on the cycle status of the firearm. A reverse cam mechanism associated with the firing pin blocking provides a resistance to and delays blowback.

Abstract: A reciprocating bolt assembly has delayed blowback and a firing pin block. Features prevent out-of-battery firing, when the bolt assembly is not fully engaged to the firing chamber or barrel face, a movable member within a bolt body functions as a blocking member that blocks the firing pin and prevents the firing pin from striking a cartridge. In embodiments, the firing pin has two stop portions that the movable member can engage depending on the cycle status of the firearm. A reverse cam mechanism associated with the firing pin blocking provides a resistance to and delays blowback.

Abstract: A breech assembly for a weapon may include a breech ring and a carrier fixed to a shaft. The shaft may be rotatably mounted to the breech ring. A breech block may be fixed to the carrier and insertable into and out of an opening in the breech ring by rotating the shaft. A notch may be formed in an end of the shaft. A lock may be translatably disposed in the breech ring and translatable into and out of the notch in the end of the shaft. Translation of the lock into the notch may rotatably lock the shaft with respect to the breech ring.

Abstract: A drive for a breech/breech carrier renders it axially adjustable relative to a weapon barrel. The drive includes a motor, two engaging cams mounted on a chain arranged below the breech and guided around two sprocket wheels. A slide is mounted in a guide at the bottom of the breech/breech carrier so as to move at a right angle to the direction of fire, with a groove extending over its entire width. The respective engaging cam entrains the breech in forward motion relative to the direction of fire, or in reverse motion, once the shot is fired, and transports the breech forwards, is displaced from the groove, and moves backwards without the breech, thereby allowing breech rest periods in a forward position. During firing, the slide moves, whereas it remains stationary when no shot is fired so no further engaging cam can entrain the breech backwards.

Abstract: A drive for a breech/breech carrier renders it axially adjustable relative to a weapon barrel. The drive includes a motor, two engaging cams mounted on a chain arranged below the breech and guided around two sprocket wheels. A slide is mounted in a guide at the bottom of the breech/breech carrier so as to move at a right angle to the direction of fire, with a groove extending over its entire width. The respective engaging cam entrains the breech in forward motion relative to the direction of fire, or in reverse motion, once the shot is fired, and transports the breech forwards, is displaced from the groove, and moves backwards without the breech, thereby allowing breech rest periods in a forward position. During firing, the slide moves, whereas it remains stationary when no shot is fired so no further engaging cam can entrain the breech backwards.

Abstract: A contact safety device between two mechanical parts mobile which respect to one another to guarantee the internal kinematics, by the release or activation of control means, wherein said device incorporates a safety unit connected to one of said two mechanical parts enclosing a probe activated by one of said two mechanical part and amplifying means constituted by an amplifying lever activated by said probe and an immobilizing lock activated by said amplifying lever meshed on said control means so as to transform a rectilinear micro-movement into a circular movement of large magnitude.

Abstract: A modular horizontal launching system is disclosed comprised of modules hng scalable dimensions so as to easily accommodate the handling of different launchable devices. The launching system has a canister that not only serves as a launch tube but also has a shipping container for the launchable devices.

Abstract: A cover closes off the open end of a missile launch canister. The cover is esigned so as to seal off the interior compartment of the canister to protect the missile or the like contained within it from moisture, contaminants and the conflagration created by nearby fired missiles. The cover is designed to maintain a minimum vapor pressure within the canister for storage purposes and to burst prior to contact by the nose of the missile contained within the canister upon the occurrence of a predetermined accumulation of vapor pressure within the canister after firing of the missile or the like. The cover is formed of a laminate of fiberglass cloths having an electromagnetic interference shield and vapor barrier adhered to the interior surface of the cover. A layer of rubber protects the fiberglass laminate from scratching or puncturing and a polyurethane layer over the rubber layer provides a moisture seal as well as insulation from other contaminants.

Abstract: Carbon fiber material and carbon fiber material that is saturated with hydrocarbon solid-liquid phase change material may be used as thermal management materials for providing a thermally conductive interface between a heat source and its housing. Such carbon fiber material may also be used for mechanical isolation of the heat source from its housing. Carbon fibers used in the carbon fiber material may be unidirectionally oriented to provide for low friction, thus optimizing critically controlled friction tolerances. Additionally the carbon fiber material saturated with hydrocarbon solid-liquid phase change material may be used to transfer heat into the an inherently nonconductive medium.

Abstract: A test system and a method for testing the final stages of a submarine wen fire control system so as to obtain a complete end-to-end test of the submarine weapon fire control system. The test system includes a launchable test vehicle that can be inserted and launched from a launch tube such as a torpedo launch tube. The test vehicle is the same size and shape as standard launchable vehicles of the type to be tested and preferably includes actual fleet replacement standard components. The test vehicle includes a data recorder that passively records a plurality of signals including power related signals, power crossover signals, preset information, launch sequence information, processor record data, and the like. The test system also includes a data extractor that is used to extract data from the test vehicle in between launches from subsequent launch tubes. The data extractor connects to an umbilical connection on the test vehicle that is normally broken during each launch.

Abstract: A launch vehicle mounting system for use in launching either of first and second launch vehicles having different booster diameters is disclosed. In one embodiment, the launch vehicle mounting system includes a mounting frame and a plurality of arms pivotally interconnectable to the mounting frame for supporting either of the first and second launch vehicles positionable thereon. In particular, the launch vehicle mounting system of the present invention is adapted to support either the first or the second launch vehicle as the arms are at least radially adjustable relative to the mounting frame to at least first and second radial positions corresponding to the booster diameters of the first and second launch vehicles.

Abstract: An apparatus and methods are provided for sheltering and/or launching devices such as projectiles or a tracking device. The apparatus preferably includes a main body having a bottom, a plurality of walls connected to and extending upwardly from the bottom, and an inner chamber defined by the inner confines of the bottom and the plurality of walls. An inner chamber cover is connected to the main body for covering the inner chamber of the main body when in a closed position and for accessing the inner chamber when in an open position. A sheltered device mount preferably is positioned in the inner chamber and connected to the main body for mounting a device to be sheltered thereto.

Abstract: A submarine signal launcher is disclosed for preventing pinched control ws therein. The submarine signal launcher includes a gas generator, an acoustic device countermeasure, a launch tube for housing the gas generator and the countermeasure, and a ram plate positioned between the gas generator and the countermeasure. A status cable is connected to the countermeasure and intermediately threaded through the ram plate and joined to the gas generator. A collapsible tube connected to the ram plate and to the gas generator. The status cable is confined within the collapsible tube. Securing members are formed on opposing ends of the collapsible tube for securing the collapsible tube to the ram plate and the gas generator, wherein upon assembly of the gas generator with the ram plate and the countermeasure within the launch tube, the collapsible tube will protect the cable from being pinched between joined ends of the ram plate and the gas generator.

Abstract: A missile, in particular for combatting moving targets, has several propulsion units arranged one after the other along the longitudinal axis of the missile. At least two propulsion units arranged one after the other can be operated simultaneously, and the missile contains an ignition control that is set up for optional ignition of these propulsion units at the same time or successively.

Abstract: An anti tip-off device for rocket rockets adapted for collapsible tube-inbe launchers is provided. The dual-diameter launch tube requires stabilization of the rocket within the larger diameter tube. The anti tip-off device has two segments which together form a hollow cylinder which fits over the nose section of a standard high explosive anti-armor rocket. A sliding surface is located around the circumference of the cylinder to provide support for the rocket during transit of the larger launch tube. The surface contact prevents the rocket from wobbling or tipping during the rocket's transit of the launch tube. Alternately, permanently-bonded stabilizer legs or a bonded ring may be attached to the rocket to match the diameter of the larger launch tube. The anti tip-off device may be fabricated using any material suited to the launcher and rocket combination, including lexan, teflon, nylon, wood, or aluminum.

Abstract: A weapons security system composed of containers for storage of warheads or warhead material. The containers are equipped to detect breaches in the enclosure walls and to transmit an alarm signal in the event of a breach. The alarm signal is received by a local control center for transmission to a central weapons command. The central weapons command may also receive the alarm directly. The central weapons command despatches forces to counter the threat identified by the alarm. Also, the central weapons command dispatches electronic authorization or opening codes to the containers or their local guardians. The containers may be equipped with entry deterrent devices and warhead destructive devices which are triggered by the detection of a breach in the enclosure.

Abstract: A modular launch pad for a launch vehicle which comprises a frame and a plurality of building units separably connected to the frame by means of connectors. The building unit comprise a concrete slab and a peripheral frame made of U-shaped channel sections connected to one another to form a frame, wherein the legs of the U are directed inwardly to engage the major surfaces of the slab. At least one of the legs of the channel sections is partially embedded in the slab so that the outer surfaces of the legs lie flush with the portion of the major surface extending between the legs. A plurality of longitudinally and transversely extending reinforcement bars are embedded in the concrete slab and a plurality of connecting means are secured to the slab. The pad has a launch vehicle mount for supporting a launch vehicle and defines exhaust gas channels in flow communication with an exhaust gas opening in the mount.

Abstract: A missile launcher for use on a surface vessel includes an array of vertical sleeves each being of a size to receive a missile carrying container. The sleeves are maintained in a linear array by means of a series of frames and the lower, or breech, ends of the sleeves are collectively connected to a plenum into which water is injected during a hot launch of a missile. A selected one of the sleeves does not carry a missile but rather, functions as an exhaust or gas take up for the exhaust gases of the other missiles.

Abstract: A cooling system for a missile launcher having a plurality of missile-containing cells connected to a common plenum. Disposed in the plenum beneath each missile is an impingement plate in the path of hot exhaust gas from the missile. A cooling water injection nozzle is arranged below each impingement plate and is supplied with cooling water during a hot missile launch to cool the hot exhaust gas and the plenum.

Abstract: A launch vehicle pedestal and an umbilical mast in which the pedestal includes a launch mount pedestal and four pedestal adapters. The launch mount pedestal includes a launch vehicle support base having an exhaust opening. Four legs extend downwardly from the support base and pedestal connecting means are secured to lower ends of each of the legs. The four pedestal adapters serve to secure the legs to existing launch vehicle support posts, the pedestal adapters each having adapter connecting means complementarily engageable with the pedestal connecting means. The umbilical mast comprises a plurality of round cylindrical segments connected by means of connectors at their ends. The connectors comprise radially extending flanges with circumferential holes in them. The mast further includes an access door and at least one opening in at least one of the segments for electrical cables and an air conditioning duct.

Abstract: An improved missile restraining apparatus capable of effectively protecting a missile from an external impact and quickly releasing a missile restraining state when launching missile, which includes a pair of protrusions having a circular cross-section and formed in the rear portion of a missile, and a pair of brackets fixed to the inner surface of a launch tube and formed so that a pair of restraining grooves corresponding to said protrusions are formed in a predetermined direction, wherein one end of said restraining groove has a circular cross-section, and the other end thereof is shaped to have an elongating axis longer than the diameter of the protrusion in the radial direction and to have the same shorter axis as the restraining groove in the vertical direction.

Abstract: A submarine launched unmanned aerial vehicle comprises an elongated genery cylindrically-shaped body. Tail fins are stored in the body and are self-deployable to extend outwardly from the body. A booster motor is fixed to an aft end of the body and is self-releasable from the body. A propeller is disposed at the aft end of the body and is self-deployable to an exposed position at the aft end of the body after release of the booster motor. A propulsion motor is mounted in the body and is operative to drive the propeller. Rotors are stored in the body and are self-deployable to an exposed position wherein the rotors provide lift to the vehicle.

Abstract: A hoop seal for a large annular opening having a high strength ring disposed in the hoop, the hoop having a sealing lip extending at an angle into the high pressure side of the seal, a base and a membrane connecting the hoop to the base which allows the hoop to rise on the side where the annular opening narrows and thereby provide a lateral force which acts to equalize the annular opening.

Abstract: A blanking-off element, intended to be mounted on one end of a tube for storing and launching a munition to protect its interior from external attacks, embodies a cap intended to extend over the entire section of the tube end and to be fixed in a tight manner right along the edge of the tube end and to become detached at least partially with respect to the end at the moment of launching, characterized in that the cap is fixed to the interior of a protective cover made from pliable material which has a retaining lug fixed to the outside of the tube close to the end, whereby the cap is recovered by the protective cover at the moment of launching.

Abstract: This invention relates to pneumatic guns that use a source of compressed gas to launch a projectile toward a target. A variety of trigger mechanisms have been used to apply the compressed gas to the base of the projectile in such a gun. In the present invention, replaceable discs of known rupture pressure threshold are mounted in the gas launcher between a compressed gas chamber and the launch tube. The gas launcher launches its projectile by the operator causing the pressure in the launcher to build up to the rupture threshold of the replaceable disc, at which point the disc ruptures and the compressed gas escapes from the compressed gas chamber past the rupture disc to push the projectile out of the launch tube. The rupture disc is a metal disc of known burst pressure.

Abstract: In a canister carrying a missile having two stages of different diameters, flexible pads are provided to cushion the smaller diameter stage of the missile. The pad is a relatively flexible elastomer folded over on itself which, when the missile is fired, unrolls to a stowed position to allow passage of the larger diameter first stage of the missile.

Abstract: An adaptive trajectory apparatus and method provide vehicle control comma to steer an underwater vehicle launched from a vessel towards a contact. A plurality of measured/estimated position and motion parameters associated with the contact are provided. The contact parameters also include information on quality and alertment status. The contact parameters are compared with an information matrix that defines a plurality of trajectory strategies and data parameters required to effect each of the trajectory strategies. A trajectory strategy is defined as a candidate trajectory strategy when the required data parameters are included in the measured/estimated contact parameter set. An expert system periodically selects a unique possible trajectory strategy based upon a predetermined set of rules that utilize the received contact parameters, quality thereof, contact alertment status and vehicle state information received from the underwater vehicle.

Abstract: An exhaust gas management system for missile launch arrangements which incorporates multiple launch cells exhausting into a common plenum. The system provides a flow passage configuration with a transition section that permits rocket exhaust flow gas to expand to fill the channel area downstream of the nozzle exit. Automatic aft closure members are included which serve to close off the flow passages to inactive cells while providing an open passage for exhaust gases from an active cell undergoing a missile firing. This arrangement prevents back flow or recirculation of exhaust gases into the volume in the cell which is upstream of the rocket nozzle exit.

Abstract: A convoluted fan structure is provided along the bottom surface of each diagonal segment of a petal-formed aft cover for a missile canister. As the cover petals open under influence of rocket exhaust impingement on the cover, the fan structures cover the diagonal areas toward the corners of the opening. This prevents recirculation of rocket exhaust gases from the plenum into the canister through the formerly open corner areas and augment the closure force to restore the petals to the closed position after completion of missile launch.

Abstract: The invention provides a cocoon/launcher for encanistered missiles. The cocoons provide environmental protection and temperature and humidity control for the encanistered missiles. The cocoon/launcher with its mechanical/electrical and conditioned air interface also provides a flexibility that allows missiles to be launched from a variety of ships and locations on ships.

Abstract: The invention is low-noise, low-pressure torpedo launching system having cially designed ports connecting a water cylinder to an impulse tank and to a method for designing such ports. The invention uses specially designed C-shaped water cylinder discharge ports to provide a continuous and minimized pressure gradient as the ports are closed by the water piston. The resulting controlled deceleration of the water piston reduces operational noise, reduces mechanical stresses and eliminates the need for auxiliary dashpot components.

Abstract: A movable ocean launching apparatus includes a semi-submersible ocean launcher for space rockets and a carrier for carrying it while holding the upper supporting deck thereof. This arragement makes it possible to inexpensively realize the transporation of the ocean launcher, preparation for ocean-based launching and the like and also to reduce the total construction costs of the launching base.

Abstract: Disclosed is a method for ejecting an interceptor missile from the silo in hich it is stored. The method employs an ultrahigh-burning rate (e.g., burning rate 10-20 inches per second) booster solid propellant grain in combination with a fuse or a combination of fuses having a burning rate (e.g. 25 to 100 inches per second) or a rate which is well above that of the ultrahigh-burning rate booster solid propellant grain. The fuses are designed to a predetermined exterior contour which is the same as the exterior contour of the mandrel which would normally be used to provide the contour to the internal perforation of the booster propellant grain. The method include positioning the fuses longitudinally in the booster motor instead of the normally used mandrel, and then casting the propellant around the fuse or a combination of fuses and curing the propellant to yield a booster solid propellant grain.

Abstract: Apparatus for launching a projectile which has a nozzle for emitting gas during launch, said apparatus comprising means for supporting a projectile and a chamber having an orifice positioned to receive some or all of a jet from the projectile nozzle wherein the chamber is configured so that pressure is developed therein to provide an additional boost to the projectile during launch.

Abstract: A device at a launcher at an air vehicle for detachably carrying and guiding a missile or the like is shown. The launcher comprises means for detachably carrying the missile and means for guiding the missile in the longitudinal direction of the launcher. The latter comprises a first profile element (2) secured in the launcher and a second profile element (4) secured in the missile, which profile elements are arranged to interact in order to admit a free mutual movement in the longitudinal direction of the launcher, while movement in lateral directions is limited.

Abstract: A missile canister hatch cover is provided which deflects the rocket exhaust from an adjacent uptake channel away from a missile as it leaves the canister. After diverting the uptake exhaust flow away from the missile, the hatch cover is returned to its closed position by the missile rocket exhaust as the missile nozzle clears the canister opening. Overall wear and tear on the launching system from the rocket exhaust is reduced and the uptake flow plume is stopped from expanding above the launcher. During missile launch the hatch cover is unlatched and spring loading opens it more than 90.degree. to a locked position where it interferes with the exhaust flowing from the uptake. The interference deflects the uptake flow away from the missile during flyout to avoid the heating, side thrusts, and contamination associated with the uptake exhaust flow field.

Abstract: A jack-up type of offshore oil-drilling platform is adapted for rocket launching, wherein the rocket is assembled on a mobile launch pad in a protected on-shore facility then loaded onto the floating jack-up barge for transport to a launch site miles offshore. The barge is jacked up to create a stable, sea-bottom supported structure; a particular feature is the used of a movable cantilever structure on which the rocket and its supporting pad are loaded while in the on-shore facility, then this structure is moved to a central location on the barge, the barge is floated, and the floating barge is towed to the launch site. At the launch site the structure is moved back to a cantilevered position for launch. In this manner the exhaust gasses from the rocket motors can be directed harmlessly into the sea.

Abstract: Missile support cables are passed through cable fitter support blocks, which are ridgidly affixed to the silo, and are swaged to heavy blocks resting upon the support blocks via a canister having ductile mesh therein. Upon a downblast, the cables are maintained in tension due to the low downward acceleration of the heavy blocks, while the support blocks are rapidly downwardly accelerated and upon rebound, smash into the energy absorbing canister which prevents the failure of the cables by controlling excess tension therein.

Abstract: To effectively recover and stow hardware items from air launched missiles, a housing containing a rotor is mounted on the launching aircraft. The housing has a suitable opening and recess so that a lanyard can connect such hardware items as the missile air inlet cover to the rotor. The rotor has a spring therein under high tension sufficient to retract the missile cover into the housing recess in a short period of time. The spring powered rotor is activated by movement of the missile away from the aircraft but can be manually reloaded and the attachment point of the cover to the rotor manually reset, as desired.

Abstract: A missile with upstanding hook members for engaging a slideway forming part of a launch station for the missile, e.g. beneath an aircraft, is fitted with a sub-frame incorporating ram and cutter knife assemblies for severing the hook members from the missile as it is launched leaving the missile with a better aerodynamic shape.

Abstract: A device for generating transverse force on a ballistic missile mock-up for air tests by means of an installation including a mock-up launching tube adapted to slant at an angle and a recovery mock-up gantry composed of a support structure for the mock-up which is pivotably mounted to the recovery mock-up gantry so as to permit the support structure to slant to the same angle as the mock-up launching tube; a carrier provided with a guide along the support structure for supporting a mobile jack including a stem for adjusting the transverse force applied on one end of the stem which is in turn transmitted to the mock-up via another end of the stem; an adjustable assembly of loads for imparting a desired transverse force to the mock-up which are fixed to an end of a cable wound on an electric winch mounted at an upper end of the support structure, wherein the cable runs on return pulleys fixed to the carrier and wherein at least one of the pulleys is mounted on the stem of the jack so as to transmit the transver

Abstract: A rocket exhaust recirculation obturator or cover member is designed to extend across the base of a missile in a launch tube between the exit nozzle of the missile rocket exhaust and the walls of the launch tube. The cover member has a central opening which seals against the rocket motor nozzle exit, and an outer periphery which seals against the launch tube walls. During launch, pressure of exhaust gases recirculating back up the launch tube will urge the obturator against the base of the missile, and both the missile and obturator will accelerate together up the launch tube. A release assembly is provided at the upper end of the launch tube which engages corresponding release devices at the outer periphery of the obturator. The engagement releases the pressure bond between the obturator, the missile base, and the launch tube. This allows the rocket exhaust to impinge upon the upper surface of the obturator in opposition to the obturator's momemtum.

Abstract: A missile support structure comprises at least two sabots or packing bodies which surround a missile in a launch tube and extend along at least part of its length. The sabots substantially fill the gap between the outer surface of the missile and the walls of the launch tube to restrict lateral movement. A capture assembly is provided to capture the sabots at the launch tube exit as the missile leaves the tube, and a return mechanism is provided on each sabot for intercepting the missile exhaust flow to urge the sabots back down into the launch tube.

Abstract: Disclosed is a missile launcher (142) which includes frontal electrical access to electrical apparatus mounted in the aft portion of the luncher. A connectorized extender electrical cable (66) is connected to the aft-mounted electrical apparatus (50). The other end of the cable (66) is routed internal to the launcher (142) and exits a frontal sway brace (24). A hole (108) is bored at a 30-inch launcher mounting location (28), and a connector (90) of the extender cable (66) is mounted therein. Aircraft pylons utilizing 14-inch mounting centers and frontal electrical umbilical connections can thereby utilize existing launchers modified according to the invention.

Abstract: Pivotable deflector panels are installed in the transition sections between a plurality of rocket storage and launch chambers and a lower plenum or manifold chamber which is provided to dispose of the exhaust gases from missile firings. The deflector panels are in addition to the sets of doors which are provided to close off the missile storage chambers upon the firing of a missile in another chamber in order to prevent recirculation of exhaust gases into the closed off chambers. The deflector panels act with the doors to control exhaust gas flow, thereby improving the effectiveness of the gas plug which is formed by exhaust gases within a transition section.

Abstract: A transition region for a missile launch chamber providing a smooth transition from a generally square cross-section chamber in which a missile is stored and launched to a round exit opening of the chamber which connects with an exhaust manifold or plenum. The transition section is provided with a pair of pivoted doors for closing off the bottom of the missile chamber to prevent the flow of recirculation gases from the plenum into the chamber when a missile in another chamber coupled to the same plenum system is being fired. The portion of the missile exhaust chamber between the square cross-section and the circular exit opening serves to direct the exhaust gases of a missile being fired into a smooth round exhaust plume which functions as a "gas plug", preventing the recirculation of the exhaust gases back into the chamber of the missile being fired.

Abstract: A shock resistant missile longitudinal support assembly provides axial support to a canisterized missile while allowing the missile to translate under shock in any radial direction relative to the longitudinal axis of the canister.

Abstract: The invention disclosed is a novel bulkhead structure for use with rocket launchers which employ a plurality of cylindrical launch tubes. The bulkhead includes openings which are aligned with corresponding launch tube openings. The bulkhead openings are counterbored to receive the launch tube ends and to provide a smooth transition between the launch tubes and the bulkhead to prevent rocket-to-bulkhead interference when the rockets are launched.

Abstract: A lightweight composite launcher pod which includes a multiplicity of eloted launcher tubes that are accurately aligned in a composite material with the composite material having four outer sides with alignment surfaces on three of the sides and bearing and alignment surfaces on the other side, and the lightweight composite launcher pod being capable of serving as the shipping and storage container for rockets before launching of the rockets as well as for launching the rockets therefrom when mounted in a launcher structure.

Abstract: A desiccant containing plug for insertion through a launcher tube into a sle containing tube which is coaxially received in one end of the launcher tube. The plug has a perforate end which extends into the container tube and which is circumscribed by a humidity sealing ring fitted to the container tube interior. The plug has a valve disk disposed at the perforate end and actuated from the closed end to open and close communication through the perforate end to the desiccant.