Abstract: The invention relates to a firearm, in particular for shooting cartridge ammunition, having at least one weapon chassis 3, a weapon system support 4, and a weapon system apparatus 5; at least the weapon chassis 3 and the weapon system support 4 have corresponding engagement means 10 provided in spacing patterns via which they can be axially positioned differently relative to each other.

Abstract: A launcher device for launching ammunition or weapons provided with primers, contains a plurality of launch tubes combined so as to form a launcher battery. Each of the launch tubes is loaded with ammunition or a weapon, and each of the launch tubes is closed off by a cover. A device is provided for detecting damage to the covers closing off the launch tubes.

Abstract: A receiver body is provided herein having a plurality of barrel-tightening portions with at least one relief recess therebetween and relief recesses defined in the body on either proximal end. The relief recesses and barrel-tightening portions are sized to allow the barrel-tightening portions to be tightened and loosened independently of each other.

Abstract: A munitions disabling device is disposed in a storage container proximate the muzzle of a single-use weapon. A projectile having a fused warhead is loaded in the weapon prior to storing the weapon. If an unplanned stimulus launches the projectile while the weapon is in the storage container, the projectile will impact or strike the disabling device. The disabling device prevents detonation or explosion of the warhead.

Abstract: The application relates to a missile launch rail device including: a missile launch rail and a latch for attaching and releasing a missile situated on the missile launch rail, a latch pin inserted through both two latch pin holes and two rail pin holes positioned approximately halfway between the cam end and the spring end and a pin retainer securely mounted to the missile launch rail, the pin retainer including a latch pin catch which holds the latch pin in place to restrict radial pressure by the pin on inside surfaces of the two latch holes and inside surfaces of the two rail pin holes from pressure created by the missile on the latch, thus substantially preventing premature disabling of the missile launch rail and the latch by wear on the latch holes and the rail pin holes.

Abstract: A system that provides wireless power transfer between a weapon and a platform. A method for loading, testing, targeting, and launching a weapon.

Abstract: A system that provides wireless power transfer between a weapon and a platform. A method for loading, testing, targeting, and launching a weapon.

Abstract: Embodiments of a canisterized interceptor and method to prevent the launch of a canisterized interceptor that may have been penetrated by small arms fire are generally described herein. In some embodiments, the canisterized interceptor includes a composite canister for housing an interceptor. The canister includes an embedded winding to provide a conductive path and comprises a conductor arranged within composite material of the canister. A maximum spacing may be provided between windings of the conductor and penetration of the canister may be indicated by an open or short circuit in the conductive path.

Abstract: A munitions casing including an annulus of a shape memory alloy disposed around said casing where the shape memory alloy has been subjected to a combination of mechanical and thermal treatments so as to impart a memory, and a cutter located between the annulus and the casing wherein heating of the shape memory alloy to a predetermined temperature causes said annulus to contract radially inwardly and rupture the said munitions casing.

Abstract: The present invention generally concerns systems and methods for supplying electric power using supercapacitors; and more particularly, representative and exemplary embodiments of the present invention generally relate to improved methods and systems for supplying power to a guided rocket.

Abstract: A weapon having a barrel or launch tube and a projectile preloaded therein. An element prevents accidental firing of the projectile if the weapon becomes overheated.

Abstract: A gas generating propulsion system includes an igniter containing an igniter propellant and an auto igniter. A rocket motor is coupled to the igniter and has a housing containing a main propellant, a rocket motor throat and a nozzle. A release port extends through a portion of the rocket motor. This gas release port has a variable diameter through bore in fluid communication with the main propellant. In this way, the through bore has a variable area that forms an unobstructed open area with a cross-section effective to discharge gas generated by the main propellant such that a pressure increase within the housing remains below a safety value for the housing.

Abstract: The invention comprises devices for mitigating the explosive reaction of a munition when it is subject to an external thermal hazard threat. The devices are based on the use of shape memory alloys. In one arrangement there is device which consists of a connector that is at least in part formed from a shape memory alloy, which typically undergoes large dimensional changes when heated or cooled through a particular transition temperature range. The connector in this invention is designed to form a locking engagement, between two components of a munitions casing at one temperature, but when subjected to external heating through the transition temperature range will deform to allow the connector to disengage and thus release the two joined components, allowing any build up of pressure to be released quickly. Advantageously if the co-operative parts of the connector and components are threaded portions, then the locking engagement will be capable of being dismantled during normal servicing of the munition.

Abstract: A hydraulic circuit for prevention of inadvertent weapons launches in which a hydraulic firing valve provides hydraulic pressure to a backup select valve rather than the backup select valve receiving hydraulic pressure directly from a ship supply header. This hydraulic pressure shifts the backup select valve to allow hydraulic pressure to pass to a mode select control valve that actuates a controllable air-firing valve, until a hydraulic firing valve for the weapon is opened. The backup select valve actuation can only occur with the initiation of the hydraulic firing valve. Only after the hydraulic firing valve is open, does the backup select valve initiate hydraulic pressure to the mode select control valve thereby preventing hydraulic actuation of the backup select valve.

Abstract: A restraint for immobilizing a projectile with respect to its launch system is disclosed. When electromagnetic force is applied to the restraint, the restraint releases the projectile, thereby enabling its launch.

Abstract: The present invention generally concerns systems and methods for supplying electric power using supercapacitors; and more particularly, representative and exemplary embodiments of the present invention generally relate to improved methods and systems for supplying power to a guided rocket.

Abstract: The illustrative embodiment of the present invention is a munitions launch system. The launch system comprises a canister and a cold launch system. In the illustrative embodiment, the cold launch system comprises a sled and a release system. In the illustrative embodiment, the release system includes a sled release mechanism, which releasably secures the sled to the munitions canister, and a munitions release mechanism, which releasably secures a munition to the sled. Actuation of the sled release mechanism releases the sled for movement within the canister. After the sled moves some minimal distance under applied force, the munitions release mechanism “automatically” actuates, releasing the munition from the sled so that the munition can be ejected from the canister.

Abstract: The illustrative embodiment of the present invention is a munitions launch system. The launch system comprises a canister and a cold launch system. In the illustrative embodiment, the cold launch system comprises a sled and a release system. In the illustrative embodiment, the release system includes a sled release mechanism, which releasably secures the sled to the munitions canister, and a munitions release mechanism, which releasably secures a munition to the sled. Actuation of the sled release mechanism releases the sled for movement within the canister. After the sled moves some minimal distance under applied force, the munitions release mechanism “automatically” actuates, releasing the munition from the sled so that the munition can be ejected from the canister.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead having destructive elements. The weapon also includes a folding lug switch assembly that provides a mechanism to attach the weapon to a delivery vehicle and is configured to close after launching from the delivery vehicle, thereby satisfying a criterion to arm the warhead. The weapon still further includes a guidance section including an antenna configured to receive mission data before launching from the delivery vehicle and further configured to receive instructions after launching from the delivery vehicle to guide the weapon to a target.

Abstract: The invention is a detachable hanger assembly for attaching a flying object to a launch rail on a launch platform. The detachable hanger assembly is attached to the flying object by one or more bolts and is adapted to slide in a slot in the launch rail when the flying object is launched. When the flying object is launched, the detachable hanger assembly slides in the slot until it impacts upon a stopper, which is fixedly located in the slot. The force of the impact of the hanger assembly with the stopper creates shearing forces that break one or more of the bolts thereby separating the main body section of the hanger assembly from the flying object.

Abstract: A launcher includes a plurality of launch tubes for stowing and launching a plurality of air vehicles. A central air manifold is operatively connected to an air storage tank; a first launch tube air manifold is operatively connected to a first group of the launch tubes and operatively connected to the central air manifold. The first launch tube air manifold has a separate port corresponding to each launch tube of the first group of launch tubes. A release valve mechanism is removably mounted in one of the ports of the first launch tube air manifold, the release valve mechanism controlling the passage of launch air between the first launch tube air manifold and the launch tube corresponding to the port in which the release valve mechanism is mounted. A plug is removably mounted in each of the ports not occupied by the release valve mechanism.

Abstract: A pressure-released brake assembly restrains a projectile in a launch tube prior to launch and automatically releases the projectile at launch. A brake assembly housing defines cavities that extend substantially radially out from the projectile when the housing is attached thereto. A brake pad adjoins the housing and has holes formed therethrough with each hole being aligned with one of the housing's cavities. Means are provided for positioning a loose-fitting pin partially in each of the brake pad's holes and partially in a correspondingly aligned housing cavity. When a launch pressure is generated in the projectile's launch tube, the launch pressure acts on each pin via the holes in the brake pad. The launch pressure causes the positioning means to fail and drives each pin out of engagement with the brake pad to effectively uncouple the brake pad from the housing.

Abstract: A canister for launching a missile having a cylindrical outer tube with a hemispherical head releaseably secured to its lower end connected through stiffeners to an inner tubular member to form a passage for the gases generated when the missile is fired. A restraint mechanism secures the missile to a base plate, which is itself mounted on shock absorbers, with a release mechanism responsive to the firing of the missile for disabling the restraint mechanism.