Abstract: In a firearm having a trigger assembly with a trigger nose, a hammer with a sear hook and a trigger notch, a disconnector and an automatic sear, an improvement including a notched bifurcating the sear hook of the hammer for receiving the disconnector in a past-cocked position. Further improvements include the trigger notch being offset rearwardly from a center of the pivot point resulting in a slightly changed angle away from an acute engagement angle with the trigger nose.

Abstract: The stores ejection system of the present invention includes a single release hook and swaybraced ejection rams for releasably mounting and forcibly ejecting miniature munitions and other miniature stores on an aircraft. The pneumatically-driven stores ejection system can accommodate miniature stores having bail lugs sized to reduce store aerodynamic drag and radar signature and to improve store delivery accuracy.

Abstract: A digital interface device conveys signals between aircraft data busses and a wingtip weapons station. A first interface is provided, coupling to an F/A-18 Aircraft Instrumentation Subsystem Internal (AISI) input/output connector. A second interface is coupled to a secondary armament bus. A crossover cable interconnects the wingtip weapon station to the secondary armament bus. A digital data processing module is coupled to the first and second interfaces and programmed to convey signals between aircraft data systems coupled to the F/A-18 AISI input/output connector and the wingtip weapon station. Namely, the processing module monitors signals received on the input/output connector, and extracts signals addressed to one or more predetermined addresses. The module also transmits the reformatted signals to the wingtip weapon station. With a minimum of wiring changes, the interface easily converts an aircraft designed for a nose-mounted ACT pod for use with an ACT pod mounted at a wingtip station.

Abstract: A conformable weapons platform (52) has a cavity (60) in a skin of an aircraft. A weapon launching system (62) is contained in the cavity (60). A pair of elastomer doors (56, 58) are attached to a perimeter of the cavity.

Abstract: A suspension lug system for use with a jettisonable weapon that provides a mechanical interface between the weapon and a multiplicity of aircraft. The system has a dual-function lug that is disposed in a well when it is in a stowed position, and that is pivotable in opposite directions on a transverse pivot pin. A first end of the lug is configured as a saddle lug that is exposed above the outer surface when the lug is rotated into a saddle-deployed position. The second end of the lug is configured as a clevis that is exposed above an outer surface of the system when the lug is rotated into a clevis-deployed position. A spring is coupled to the lug that spring loads it and returns it to a stowed position when it is not engaged with the ejector release unit to preserve the outer contour of the weapon.

Abstract: The present invention relates to an integral hoist and weapon rack interface assembly adaptable for loading a weapon onto an aircraft. The assembly includes a hoist mechanism positioned at an aircraft weapon station and a separate rack attached to the hoist by straps is lowered into contact with the weapon. After the weapon is attached to the rack, the combination of weapon and rack are raised into engagement with a structural plate supporting the hoist mechanism. A plurality of uplock hooks mounted on the plate automatically engage swaybraces mounted on the rack to mechanically lock the rack to the hoist.

Abstract: A trigger arrangement for an automatic weapon with switch-over between continuous firing and single-shot modes includes a hammer, a breechblock, a latch, a pivotably mounted trigger, and a firing lever. In the single-shot mode, the firing lever engages the hammer and retains it in tension while the trigger is depressed. When the continuous firing mode is selected, the firing lever is moved to an inactive position and retained by an engaging element. The engaging element is preferably a slider which is controlled by a safety and firing cessation roller that is actuated by an operating lever.

Abstract: A stores ejection system for retaining a store on the underside of an aircraft and forcibly jettisoning the store away from the aircraft. The ejection system includes an ejector mechanism for releasably holding and jettisoning the store away from the aircraft and a storage device for storing pressurized gas at an operating pressure selected for actuating the ejector mechanism to release the store and forcibly jettison the store. The system further includes a dump valve movable between a closed position in which the storage device is isolated from the ejector mechanism, and an open position in which the pressurized gas is free to flow from the storage device to the ejector mechanism for pneumatic actuation of the ejector mechanism to release and jettison the store.

Abstract: The disclosure relates to a low cost and highly accurate precision guided system suitable for use in conventional aircraft launched bombs. The system includes a kit mounted upon the nose of the conventional bomb which replaces the conventional fuse disposed in a fuse well, the kit including guidance electronics controlling a self-contained jet reaction device and GPS P-code receiver electronics. The bombs are readied for discharge by radio frequency signals broadcast from the aircraft into the bomb bay which transfer initial GPS data and commence operation of a gas generator which powers the jet reaction device.

Abstract: As voltage and frequency dependent multiple payload dispenser system in which a variable voltage or frequency signal source is used to selectively fire squibs based on the pass voltages and pass frequencies of a filter network. The filter network is placed near, or incorporated into, the payload dispenser itself or attached to the magazine, reducing system wiring.

Abstract: A weapons launching system (20) is located in an internal weapons storage compartment of an airplane, preferably a widebody aircraft. The system includes a monorail assembly (22) supported by a rail frame (24), and a number of carriage trucks (26) movably engaged with the monorail assembly (22). The carriage trucks (26) deliver weapons (27) via the monorail assembly (22) to a launch bay (28) located near one end of the storage compartment. The carriage trucks (26) include handling-release units (30) for picking up and moving weapons (27) within the storage compartment and for releasing the weapons (27) out the launch bay (28). A portion of the weapons are initially held by the handling-release units (30), while the remaining weapons are supported on stationary support units (34) located in the rail frame (24).

Abstract: A functioning mechanism for a small caliber automatic weapon includes a translatable and rotatable sear, and a rotatable hammer. The sear includes a hooking element adapted to contact a bearing surface of the hammer to render the hammer immobile. Rotating movement of the sear is controlled by the hammer in such a way as to obtain clean contact between the hooking element and the bearing surface.

Abstract: A mechanical regulation system for controlling tow line payout between the aerobody and a towing vehicle. The system comprises a housing, a nonrotating spool, and a tow line wound around the spool that is coupled between the aerobody and the vehicle. The regulation portion of the present system comprises a rotatable wedge-shaped tube, having the tow line wrapped around it. A rotatable mechanical regulator is slidably coupled to the wedge-shaped tube. The regulator is adapted to rotate with the tube and move transversely along the length of the tube as the tow line is removed from the spool. A brake mechanism is provided as part of the regulator, and a brake drum is disposed adjacent the periphery of the regulator that is contacted by the brake mechanism.

Abstract: A launching and regulation system that incorporates an expendable towing and deployment mechanism for use with a towed aerobody that provides for launching and controlled tow line payout between the towed aerobody and a towing vehicle. The system comprises a housing, a nonrotating spool disposed in the housing, and a tow line wound around the spool that is coupled between the aerobody and the vehicle. The tow line preferably comprises a photonic, fiber optic, link. The launching mechanism comprises a plurality of impulse cartridges for deploying the aerobody and severing the tow line at a predetermined time. A spring piston is disposed inside a wedge-shaped tube that confines expanding gasses within the tube that are generated by an impulse cartridge and moves the spring piston to launch the aerobody. The regulation mechanism may comprise a mechanical system or adhesive resin system. The mechanical system comprises a rotatable wedge-shaped tube, and the tow line is wrapped around it.

Abstract: The member bearing electromagnetic decoys comprises a sliding member (23 to 27) having an open major face closed by a cover of which an extension projects opposite an opening (21A) in a compartment (21) provided for a pyrotechnic portion. When the pyrotechnic charge there disposed has caused ejection of the decoy-bearing sliding member, and after a given delay, it will act on the extension of the cover in order to remove the latter and thereby release it from the electromagnetic decoys. This ensures that the decoys are deployed at the end of a given delay after ejection of the decoy-bearing member from the aircraft.

Abstract: In a method for the ejection and distribution of submunition bodies to be ejected from a submunition carrier for combatting targets in a line, such as vehicle columns, the submunition carrier (3) comprises vertical ejecting tubes (3a) for the submunition bodies, which vertical ejecting tubes (3a) are directed downward as well as upward. Submunition bodies (7) which are connected with a wind sock for stabilization are ejected downward. The submunition bodies (9) which are to be ejected in an upward direction are connected with a parachute which is provided with at least one eccentric slot.

Abstract: A munition constituting a cartridge-launcher loader comprises a plurality of consumable modules each in the form of a flat strip of juxtaposed cartridges each comprising a payload of chaff, an ejector pyrotechnic charge, an electrical initiator, and a reusable support receiving the strips. The support has a system for immobilizing the strips and a handle for transporting and installing it. The strips are juxtaposed at their flat surface to perform a homogeneous block essentially constituting the body of the munition or a part thereof. The support includes a fixed plate carrying the strips and receiving the latter, when they are inserted, by virtue of them sliding in a general direction parallel to the plane of the plate.

Abstract: A dispenser (1) for connection to the sequencer breech plate (5) of a dispensing system on an aircraft having a plurality of firing contacts, comprises a main body (2) subdivided into a plurality of cells (6). The number of cells (6) in the main body (2) is greater than the firing contacts on the breech plate (5) by payloads (7) being received directly by the main body as opposed to being separately constrained. An interface plate (4) is provided for electronically and mechanically connecting the dispenser (1) to the breech plate (5) matching the firing contacts to the breech plate with firing positions corresponding to the plurality of cells of the main body. In order to provide the electrical matching, pairs of contacts on a first part (12) of the interface plate (4) are interconnected by selector means (18) allowing a first firing signal to pass only to one contact of the pair and then allowing a second signal to pass to the other contact.

Abstract: An air-launchable gliding sonobuoy store includes a canister enclosing an flatable-membranous wing folded in a collapsed state with an electroacoustic system. After launching, the wing inflates and a steering mechanism controls the wing glide path by skewing the trailing edge thereof. Upon reaching the sea, the wing serves as a buoy with the electroacoustic system transducer depending therefrom.

Abstract: A jettisonable means comprises means with a travelling-wave tube for emitting electromagnetic waves. It forms part of an assembly having external power supply means for supplying the filament of the travelling-wave tube. The external power supply means temporarily supplies the filament of the travelling-wave tube to heat it to its nominal temperature before jettisoning, whilst, at the moment of jettisoning, the external power supply means are disconnected. This enables a temperature appropriate to the operation of the travelling-wave tube to be provided temporarily, after the jettisoning.

Abstract: A system for releasably supporting a store on a rack comprises a conical lug mounted on the store and a hollow locking ring which extends between minor and major rims defining circular openings, respectively. A plurality of ribs extends between the minor and major rims at equally spaced circumferential locations. The ribs are aligned with the longitudinal axis of the locking ring and define windows between them. A collet includes a mounting head for attachment to the rack and a plurality of integral, circumferentially spaced, resilient, locking fingers, equal in number to the ribs and windows in the locking ring, which extend divergingly, away from the mounting head and have terminal projections which extend radially inwardly. Each locking finger is smaller than its associated window in the locking ring means. The collet nests with the locking ring such that the mounting head extends through its minor opening for attachment to the rack means and with the locking fingers projecting toward its major opening.

Abstract: A release unit for launching countermeasures from a vehicle. A first module in the form of a central body mounted on the vehicle. The first module includes at least three openings: a first opening facing the vehicle when the first module is mounted on the vehicle, and second and third openings directed obliquely with respect to the first opening in substantially opposite directions from each other. The directions the second and third openings face are separated by 60.degree.-120.degree.. A second module and a third module in the form of release cassettes are received respectively by the second and third openings and removably fixed by with a locking member. A plurality of countermeasures are launched from the release units. Each release cassette includes a plurality of countermeasure openings for receiving the countermeasures. The countermeasure openings in each cassette are aimed substantially in the same direction.

Abstract: An improved, multi-store dispenser is described which uses a solenoid and ring combination to eject individual stores after an electrical pulse is sent from the transporting aircraft. As each store is loaded into the dispenser, the loading action forces a spring into a compressed mode and a latch is closed to prevent expulsion. An electric pulse trips a solenoid, which in turn causes the latch to release, thereby allowing the store to be ejected.

Abstract: A device for indicating the type of ammunition provided in or on the ammunition unit comprises a distinguishable specific identification allocated for each type of ammunition and made up of electronic device with different electrical characteristics depending on the type of ammunition, including a status-changing element which can change between at least two statuses having different electrical characteristics. A control circuit is provided for controlling change-over of the status-changing element between the at least two statuses having different electrical characteristics, the process of the status changes controlled by the control circuit being indicative of the type of ammunition contained in the ammunition unit.

Abstract: A multiple missile ejection system (10) by which first and second missiles (14) and (16) are stored in a single launch tube (12). Each missile is ejected by a gas bag. In a particular embodiment, two gas bags are used. The first gas bag (18) is mounted between the first and second missiles (14) and (16) respectively. The second gas bag (20) is mounted between the second missile (16) and an end of the launch tube. When deflated, the first gas bag (18) has a longitudinal aperture (28) through the center thereof which allows for the ejection of the second missile (16) by the second gas bag (20).

Abstract: A technique and apparatus for rearward launch of a missile. The inventive apparatus (10) includes a launch tube (12) in which the missile (14) is mounted with the forward end of the missile being mounted at the forward end (16) of the tube. The rearward end of the launch tube is sealed with a break-away material (18) prior to expulsion of the missile (14). An expulsion mechanism expels the missile in a rearward direction from the launch tube. The expulsion mechanism includes an airbag (20) and a pressurization mechanism (30). The airbag (20) includes a bra (22) for maintaining the orientation of the missile (14) during the expulsion thereof. The airbag (20) also includes a metallized enclosure (24) for sealing the launch tube (14) after the expulsion of the missile (14).

Abstract: A paint ball delivery system (10) for incorporation into a radio controlled airplane (100); wherein, the system (10) comprises a housing unit (11) equipped with a magazine member (30) containing paint balls (51) and having an actuating unit (13) which controls the release of the paint balls (51) from the housing unit (11).

Abstract: A launch-chute extender is disclosed that snap-fits onto the end of a buoy ontainer in an aircraft that carries stores internally. This extender, by adding its tubular configuration to the end of the buoy container, provides guiding clearance to selected stores to enable them to exit from the underside of the aircraft without becoming jammed.

Abstract: An improved launching system for use on a platform and for selectively and ontrollably dispensing one or more elements of predetermined shape in carrying out its mission as used on any suitable platform; such as, e.g., an aircraft. The system is generally made up of elongated sleeve means being closed at one end and also having an aerodynamic profile as required. Depending upon the requirements of the system, it can be provided with external or internal control means. The system is generally comprised of selectively programmable motor-driven, feed-screw propelling means. The propelling means is arranged within the sleeve means such that the propelling means when in a retracted position provides a chamber for receiving one or more elements to be temporarily stored in nested but axially aligned relation to each other until selectively dispensed.

Abstract: An injection module for a subammunition container, of the type in which subammunitions, ejected transversely to the flight direction of the subammunition container, are situated in front of driving devices which are actuated by gas-generator-driven ejecting pistons. The ejecting pistons are arranged transversely with respect to the flight direction, and may extend along half the width or the full width of the ejecting module. The gas generator may be arranged transversely or longitudinally of the flight direction.

Abstract: An auxiliary target area chaff container for dispensing chaff and other rr counter measure materials from an aircraft includes a housing, chaff canister located in said housing; trigger wires for dispensing the chaff means for retaining said chaff canisters in said housing and means for attaching said housing to an aircraft. The chaff canisters are automatically dispensed when a bomb is released.

Abstract: An ejection system for payload deployment in a low gravitation exoatmospheric environment. In its broadest aspects, the ejection system includes an elongated launch tube; a payload mountable within the launch tube; and, a plurality of equiangularly spaced, axially aligned spring members secured to an outer surface of the payload. The launch tube includes pre-deployment payload securing means for securely maintaining a payload within the launch tube prior to depolyment. Each spring member provides a forward and an aft dynamic interface between the payload and the launch tube. The utilization of a plurality of spring members provides payload alignment relative to the launch tube prior to and throughout payload ejection.

Abstract: An improved store launching device is disclosed wherein the inside of a sdard sonobuoy launch container is modified to accept, and properly dispense, only one smaller and lighter store. A positioning ring is fitted securely onto the inner walls a preselected distance from the discharge end to provide a seat for a perforated obturator. A slotted pressure relief ring, with the edge adjacent the obturator having a biased cut of a predetermined angle therein, is placed adjacent the obturator and the discharge end of the container to surround the store.

Abstract: An arrangement for bracing a load in which a wedge is moved into frictional engagement between a mounting surface and a surface of the load. A spring biased rod is coupled to the wedge and moves it into and out of engagement with the mounting and load surfaces. A stop is provided to prevent the wedge from penetrating between said surfaces beyond a predetermined limit in order to avoid generating excessive forces between said surfaces.

Abstract: This invention comprises a multi-store, gas-fired launcher that fits into, nd is electrically connected with, a transporting vehicle and that contains sequentially-stacked assemblies that generate sufficient gas force to discharge an individual store. An electrical pulse from the transporting vehicle cause a sequencer in the launcher to divert the charge to a burn resistor. At burn-out, a spring-activated striking arm punctures a CO2 bottle which provides sufficient gas pressure to force the store out of the launcher.

Abstract: Disclosed is a system for securing sub-munitions on board a carrier. The system uses straps. Each strap is fixed by one end to a container wall by a tensioning means, and its other end is engaged in a cylindrical lock element mounted on another wall. The cylindrical lock element is connected to a resistant torque generator device which is itself connected to a torque limiting device which gets triggered at a determined threshold value, so as to release the cylindrical lock element in rotation in order to release the end of the strap. In these systems, the straps are released less suddenly than in the known systems, and they are released with perfect simultaneity. A development enables the sub-munitions to be ejected with controlled angles of incidence in relation to the trajectory of the carrier.

Abstract: A multi-store launcher has each store in a stacked sequence releasably held y a swinging paddle assembly against the ejection force of negator springs. Each paddle assembly carries a burn resistor that is wired to maintain the paddles in a locked position. A pneumatic pulse from the transporting vehicle causes electronic circuitry to make the resistor fail, freeing the paddles to open away from the store and thereby allowing it to be ejected by the negator springs.

Abstract: This invention comprises a multi-store, electrical pulse initiated launcher hat fits into, and is electrically connected with, a transporting vehicle and that contains sequentially-stacked assemblies. An electrical pulse from the transporting vehicle causes a resistor with the least value to transfer the electric to a gas generating cartridge. The cartridge provides sufficient gas pressure to force the store out of the launcher.

Abstract: A multi-store launcher receives initial power from a pneumatic source. The ir pressure causes a shear pin to fail, thereby allowing a firing pin to ignite a gas-generation cartridge. The gas pressure is channelled to the appropriate store, which is then discharged.

Abstract: A multi-store launcher has each store in a stacked sequence releasably held y a swinging paddle assembly against the ejection force of negator springs. Each paddle assembly carries a burn resistor that is wired to maintain the paddles in a locked position. An electric pulse from the transporting vehicle causes the resistor to fail, freeing the paddles to open away from the store thereby allowing it to be ejected by the negator springs.

Abstract: A self-retracting bomb suspension lug assembly for being releasably supported by a hook or the like of an airplane bomb rack. The lug is mounted within a housing for axial movement and has an outer surface conforming to the shape of the bomb so as to eliminate aerodynamic drag when the bomb is released. Springs, such as a stack of Belleville springs, are disposed for biasing the lug inward when the bomb is released and the weight of the bomb no longer bears on the lug. Finger springs and pawls engagable with a groove in the bottom surface of the lug are provided to maintain the lug in partially extended loading position wherein the top of the lug is accessible for being grasped. To cock the lug, it is moved slightly inward against the force of the lug biasing spring, and the finger springs are forced radially inward to engage the groove.

Abstract: A multi-store launch container is disclosed wherein a plurality of stores, aintained in a tandem configuration therein, can be sequentially ejected. The container is normally carried by a vehicle and receives the necessary charges, of for instance pressurized gas, at its breach end. A spring-biased cocking mechanism forces open a first port cover and maintains a second port cover in the closed position. After the first charge is fired, the cocking mechanism allows the port covers to pivot and the first port is now tightly shut and the second port open for the next charge.

Abstract: A multi-store, mechanically-actuated launcher is disclosed. Negator springs ut constant pressure on sequentially-stack stores inside a launch container and an electro-mechanical gate releases one store after another upon initiation of an electrial impulse from the transporting vehicle.

Abstract: An improvement for a caliber conversion kit for semiautomatic and automatic firearms to allow the use of smaller caliber ammunition within. The conversion kit comprises the replacement of the bolt, barrel and magazine clip of the existing firearm so that the firing speed and thus the action or feel is similar to a standard nonmodified firearm having larger caliber ammunition.

Abstract: A device for ejecting submunition from a scattering vessel with a plurality of ejecting tubes which receive this submunition, has one or more compressed-gas generators being assigned to these ejecting tubes for the purpose of an ejection which is uniform or variable with respect to time. Such a device regulates the pattern of the submunition in accordance with given conditions.

Abstract: The invention concerns a safety device positioned on a charge releasable from a carrier that, firstly prevents the untimely activation of the charge when this charge is hooked on beneath the carrier and, secondly, makes it possible to know whether any attempt at activation has been made beforehand, in doing so through the display of a position of a sensor of the carrier, forming part of the safety device. The safety device is deployed by means of a cable connected to the carrier. At the moment of release, the cable provided with a knob uses a driving system to drive a sensor which is itself locked by a locking system enabling the display of the position of the sensor and thus releasing the driving system permitting the activation of the charge.

Abstract: Disclosed is a device for unlocking a system for fixing sub-munitions on board a carrier, namely any flying vehicle (such as a rocket, missile, stand-off missile etc.). Each sub-munition is held on the body of the carrier by a movable holding clamp fixed to the sub-munition locked by a rod against which there lies a roller fixed to the end of the movable holding clamp. A pneumatic system formed by a piston activates the rod comprising different parts with different widths and diameters so that its step part, on which the roller lies, is translated and leaves place for its central part, in such a way that the movable holding clamp can pivot around the shaft, thus releasing the sub-munition.

Abstract: The disclosure concerns the field of charges releasable from an aircraft to which they are fixed and, particularly, the keel beam safety device that prevents the activation of the charge when it is hooked on beneath the aircraft. A mechanical safety device for the keel beam consists in using the driving force of a sensor that is rotationally free in a support, by means of cable going into said sensor, one end of which is fixed to an aircraft and the other end to means for activating a fuse for the firing of a charge. To this cable, there is fixed a ball which, when a tensile force is exerted on the cable, comes into contact with the sensor and draws it, after the unlocking of the holding system, through a sufficient tensile force exerted on the cable, into contact with the aircraft when the charge is fixed beneath the aircraft, thus preventing any additional movement of the cable. When the charge is released, the cable can be pulled freely and enables the charge to be activated.

Abstract: A buoy deployment system for an aircraft is disclosed which includes a multi-store gravity launching system which allows for discharge of different lengths and types of buoys. The gravity launch system includes a plurality of launch tubes, each including a spring biased door at the discharge end thereof, with the doors being either electrically actuated from the pilot cockpit via electrical controls, or, in the event of an electrical malfunction, being manually operable by an operator. Each buoy loaded therein is accessible for reconfiguration in flight, with each tube similarly being reloadable in flight. Also disclosed is a rotatable storage carousel including a plurality of semi-cylindrical tube section/latch assemblies, sized to restrain a plurality of buoys, which form storage stations on the carousel.

Abstract: A multi-store launch container is disclosed wherein a plurality of stores, aintained in a tandem configuration therein, can be sequentially ejected. The container is normally carried by a vehicle and receives the necessary charges, of for instance pressurized gas, at its breach end through apparatus known in the art. A fluid-controlled flow valve maintains an open flow pathway through a first channel while blocking the opening to a second channel. After the first charge is fired, the diverter mechanism forces the flow valve to pivot and tightly shut the first primary channel and open the second primary channel to receive the next charge.