Abstract: A missile launch system is disclosed that allows for the rapid reloading of missiles in support of missions (e.g., littoral warship missions, etc.) that require a high-volume assault of one or more targets. In particular, the illustrative embodiment of the present invention uses a munitions module that is capable of launching missiles and is able to fit inside a warship. In addition to accommodating multiple missiles, the munitions module accommodates one or more missile types. The munitions module is configured with a door at a breech end to provide access to multiple launch cells for the rapid reloading of missiles. The door is physically configured to define a plenum that couples the launch cells to an exhaust duct for the purpose of venting exhaust gases. The munitions module mitigates some of the problems associated with launch systems in the prior art.

Abstract: A missile launch and guidance apparatus of a rail-shoe launching type is disclosed. In a missile adapted to be launched while moving along a rail of a launch tube, a missile launch and guidance apparatus comprises: a bushing inserted into a missile body; a shoe, one end of which is inserted into the bushing, and the other end of which is in contact with the rail; and a spring inserted between the bushing and the shoe so as to provide a separation force to the shoe against the bushing. By separating the shoe from the missile in a lateral direction of the missile launching direction by an elastic force of the spring after launching the missile, the missile launch and guidance apparatus can keep constant the gap between the missile and the launch tube rail irrespective of the behavior of the missile taking place in a launching process, and the drag and weight of the missile launched from the launch tube is reduced to thereby exhibit the maximum flight performance.

Abstract: Apparatus and methods are described for a weapon simulator. An example weapon simulator includes a pressure piston, which is couplable to a weapon, which acts to open a breech, and which is seated in a pressure cylinder. An example pressure piston includes a slider. The slider holds a pressure intake opening open and keeps one or more pressure outlet openings closed when the breech is in a front-most position. In addition, the slider keeps the pressure intake opening closed and holds the one or more pressure outlet opening open when the breech is in a rear-most position.

Abstract: In a multiple projectile launcher system, cartridges are securely held within a cassette that can be loaded into a locking and priming mechanism in a base of a multiple projectile launcher. Once the cassette is loaded into the locking and priming mechanism, the cartridges in the cassette may be primed by moving the locking and priming mechanism (which is holding the cassette) such that electric igniter contacts in the launcher base are in contact with electric igniters at the priming end of each cartridge. Once the cassette is locked (thereby priming the plural cartridges held in the cassette), the cartridges may be fired singly, severally, and/or all at the same time, using an electrically initiated fire control system. The multiple projectile launcher is particularly effective in crowd and/or riot control, where the payload of the cartridges comprise non-lethal and/or less-lethal munitions, such as tear gas grenades, sting-ball grenades, flash-bang rounds, bean bags, etc.

Abstract: A fast acting active protection system for military vehicles defeats RPG (rocket propelled grenade) threats fired from close ranges. The system minimizes the hazard to troops and civilians nearby. The system uses a plurality of passive sensors to locate the threat and initialize the system. A low cost radar or laser tracker is used as the means to determine range, velocity, and (if required) angular position of the threat. The countermunition used may be one of several choices, with the requisites being that the countermunition provides fast response with low inertia, and is able to damage or destroy the detected threat. A multi-barrel recoilless gun is the weapon of choice. A launching device is used to deploy and aim the countermunition and the tracking means. On board software and electronics are used to control the system.

Abstract: A launch tube system has two concentric sleeves. An inner sleeve having holes formed therethrough defines a launch tube, and an outer sleeve surrounds the inner sleeve and is spaced apart therefrom. One or more flexible bladders are disposed between the inner outer sleeves. When filled with fluid, the flexible bladder(s) expands and extends into and through the holes and into confines of the inner sleeve to thereby form shock isolation for a projectile housed in the inner sleeve.

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 reconfigurable missile launcher that avoids some of the costs and disadvantages associated with missile launchers in the prior art. In particular, the illustrative embodiment of the present invention uses a variable-size receptacle for locating and holding a missile canister chosen from a set of missile canister types. The illustrative embodiment also includes a controller that includes data sets that are specific to each of a plurality of missile types.

Abstract: A container (1) for acting as a storage enclosure and launch tube for a missile (3), the container (1) comprising an integral missile efflux management system including an efflux deflector (1d) positioned for receiving the missile efflux and deflecting it into a series of ducts (8) which run alongside the missile to the missile exit end (16) of the container (1), which end may have an openable cover (7) operable to close both the missile exit and the exits from the ducts (8). The efflux deflector is a dome-shaped base-plate (1d) spaced from the ducts to define a plenum chamber. The particular interior shape of the base plate (1d) ensures optimum efflux management.

Abstract: An adapter device (10) is used in order to allow a projectile (12), such as missile, to be launched from a standard launching tube (14), without having to modify the latter. This device comprises an adapter tube (24) in which the projectile (12) is placed, a retaining ring (22) which is mounted on the end of the launching tube (14) and a hooking system (26) for securing the adapter tube (24) to the launching tube. The adapter tube (24) has a front portion (38) provided with grooves for guiding the folded fins of the projectile (12) and a rear portion provided with a bottom onto which is fixed a pulley (36) for returning an optical fiber (20) used for guiding the projectile (12).

Abstract: A method of defense against optically guided missiles, said method comprising the steps of: mounting a single-ended laser adjacent the area to be protected emitting electromagnetic radiation at a frequency within the sensitive frequency range of said guided missile, directing said radiation toward an area within which said radiation may be reflected by components of said missile, causing lasing operation of said laser in response to reflection of said radiation by components of said missile, and modulating the output of said laser in response to said lasing operation for misdirecting said guided missile.

Abstract: Based on pyrotechnic launch tubes (1) with a cylindrical body which houses in their interior both the pyrotechnic objects or materials (3) and the lifting powder (5), the system consists in providing each cylinder (1), on its lower base, with a series of tabs (6), determining a radially deformable neck, wherein said tabs (6) are finished in barbs (7) for engagement by pressure in a securing piece (11–11?), fastenable to the frame of the tubes or incorporated by way of a single piece in the actual frame, provided with an external and rigid neck with a gradation (14) for the engagement of the barbs (7) and provided with an axial and cylindrical core (10) which, perforating the bottom of the cylinder (1), is of a size to house in its interior the igniter (12) with its corresponding cable (13), which is thereby perfectly protected from possible environmental humidity.

Abstract: A reloadable launcher for use with rocket-propelled projectiles. An inner and outer tube define a concentric tube arrangement with at least one gas flow channel being defined therebetween. A ring is fixedly coupled to a first end of the outer tube that is adjacent to the breech end of the inner tube. The ring defines a keyway and an annular channel that lies between the keyway and the first end of the outer tube. A cap having a concave inner surface terminates in a peripheral edge that defines a key shaped for passage through the keyway of the ring. When the cap's key is aligned with and moved axially through the keyway, the key resides in the annular channel adjacent the first end of the outer tube. A link is hingedly coupled on one end thereof to the ring to permit the cap to be moved such that a projectile can be loaded into the inner tube from the breech end thereof. The link is also rotationally coupled to the cap's central portion such that the cap can be rotated thereabout.

Abstract: Based on pyrotechnic launch tubes (1) with a cylindrical body which houses in their interior both the pyrotechnic objects or materials (3) and the lifting powder (5), the system consists in providing each cylinder (1), on its lower base, with a series of tabs (6), determining a radially deformable neck, wherein said tabs (6) are finished in barbs (7) for engagement by pressure in a securing piece (11-11?), fastenable to the frame of the tubes or incorporated by way of a single piece in the actual frame, provided with an external and rigid neck with a gradation (14) for the engagement of the barbs (7) and provided with an axial and cylindrical core (10) which, perforating the bottom of the cylinder (1), is of a size to house in its interior the igniter (12) with its corresponding cable (13), which is thereby perfectly protected from possible environmental humidity.

Abstract: A rocket assisted payload launch system includes a heavy gauge metal shipping container that houses an array of containerized concentric launch tubes, or canisters. Spacers on each containerized concentric launch tube contact the adjacent tubes and retain the centers of the tubes a predetermined distance apart, and in a vertical orientation. A missile including rocket assisted payload (RAP) can be inserted into the open upper end of each tube, which also has a curved, closed bottom end. Umbilical cords are connected to each tube for providing target location information to the missile placed therein. A sequence controller selects the rocket assisted payload to be fired, and initiates the firing sequence by delivering power, via the umbilical cord, to the selected missile. The sequence controller may be manually operated, or may be operated, automatically, via a datalink, in the preferred mode of operation.

Abstract: The invention relates to the aerospace engineering and can be used for jettisoning boost rockets from an aircraft. The inventive device comprises a landing container (3) with an open end (4) provided with a high-pressure source (5). The freight to be jettisoned (2) is arranged in two sections inside the container (3) on mounting elements (10), one of which is embodied in the form of a calibrated support (9). The values of maximum efforts and acceptable lateral movements (13) of the supports (9) are chosen in such a way that a minimum positive allowance (12) between the container (3) and the freight (2) is provided. The supports (9) are provided with dampers. The aim of the invention is to reduce a transverse load affecting the freight to be jettisoned landing.

Abstract: The invention relates to a container for propellant charge modules to be loaded into a weapon using conveyance means. It comprises protection means insulating said modules from the conveyance means, constituted by a rigid tubular body, a sheath intended to receive the modules and means to block the modules in the sheath. The sheath is made of a deformable material. The blocking means ensure the deformation of the sheath to immobilize the modules. Application to charge module conveyance.

Abstract: An ammunition drum (110) and firearm with an ammunition drum (110). The ammunition drum designed for being mounted on a firearm has at least two projectile channels (118), which are arranged around a longitudinal drum axis (112). The ammunition drum (110) has at least two drum segments (114.1, 144.2, 114.3), which are connected with each other.

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state.

Abstract: A modular missile assembly includes a pair of modules which are separately transported and handled until just prior to firing, when they are coupled together. A forward payload-carrying module includes a forward canister which encloses a missile payload section, for example, consisting of a penetrator rod, fins, and ancillary sub-assemblies. An aft booster module includes a missile propulsion section, encased in an aft canister. Prior to firing, suitable forward and aft modules are selected, are individually loaded into a launch tube, and are coupled together. In this coupling the missile payload section and the missile propulsion section are coupled together to form a missile, and the forward and aft canisters are likewise coupled together to form a combined canister assembly. Division of the missile into separate payload and booster modules facilitates handling as compared to unitary missiles. The modular design also allows increased flexibility.

Abstract: The detachable shock-absorbing ram-plate is used in a projectile launching system to mitigate launching impact forces and to prevent ram-plate re-strike during launch. The detachable shock-absorbing ram-plate is detachably coupled to the projectile using break-away fasteners that allow the ram-plate to be attached to the projectile during launch and detached from the projectile at the end of the launch. One embodiment of the detachable shock-absorbing ram-plate is a single impact, viscous fluid ram-plate including a cylinder, a perforated piston, and a viscous fluid disposed between the cylinder and the perforated piston. Upon receiving a high initial launch impact force, the piston compresses causing the viscous fluid to be forced through the perforated piston, thereby absorbing the shock of the initial launching impact force. Another embodiment of the detachable shock-absorbing ram-plate is a gas spring ram-plate having a cylinder and piston that compresses a gas to absorb shock caused by launching forces.

Abstract: A launch canister for a missile, including an outer canister shell and a concentric inner liner. The inner liner augments the canister shell with structural load capability and bending inertia to enhance canister stiffness. The inner liner can be constructed from structural load carrying composite materials, and also acts as a thermal and ablative insulator to enable vertical plume venting away from the enveloped missile. A shock and vibration isolation layer can be laminated between the inner liner and canister shell.

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state.

Abstract: A support and alignment assembly for use on a moving vehicle having a fixed receiver mounted thereon. The assembly comprises a support assembly including (i) a loading tray for supporting a missile, (ii) a storage structure for supporting the loading tray, and (iii) mounts resiliently connecting the storage structure to the vehicle.

Abstract: The detachable shock-absorbing ram-plate is used in a projectile launching system to mitigate launching impact forces and to prevent ram-plate re-strike during launch. The detachable shock-absorbing ram-plate is detachably coupled to the projectile using break-away fasteners that allow the ram-plate to be attached to the projectile during launch and detached from the projectile at the end of the launch. One embodiment of the detachable shock-absorbing ram-plate is a single impact, viscous fluid ram-plate including a cylinder, a perforated piston, and a viscous fluid disposed between the cylinder and the perforated piston. Upon receiving a high initial launch impact force, the piston compresses causing the viscous fluid to be forced through the perforated piston, thereby absorbing the shock of the initial launching impact force. Another embodiment of the detachable shock-absorbing ram-plate is a gas spring ram-plate having a cylinder and piston that compresses a gas to absorb shock caused by launching forces.

Abstract: A system for boosting the velocity of a rocket utilizing a container having a bottom and a side wall portion extending outwardly from the bottom. The side portion terminates in a peripheral edge and forms a chamber. A platform is supported in the chamber and is movable from a first position to a second position adjacent the peripheral edge of the side wall portion of the container. Exhaust gases are conducted to the chamber such that movement of the platform within the container supporting the rocket takes place.

Abstract: A modular launching system is disclosed that reduces the reinforcement needs of mating a launching system to a ship, while at the same time reduces stress concentration and foundation movements created by the modular launching system launching launchable devices.

Abstract: Provided is a compact, low-cost, lightweight, man-packable weapon system for engaging static and slowly maneuvering targets. In one embodiment, it may incorporate in its own backpack a compact launcher and multiple compact missiles, each weighing less than five pounds, for carry on a soldier's back. The missile itself uses a strapped-down acquisition and tracking sensor electrically connected to a simplified guidance system interfaced with an aero-control section capable of altering the flight path of the missile to a target. A solid-propellant rocket motor provides sufficient power to propel the missile at a predetermined limited speed and over a pre-determined limited distance that enables the proper operation of the simplified guidance system. A method for deploying a man-packable weapon system is disclosed also.

Abstract: A device for weight counterbalance of compensating equilibrators of a TOW weapons system substituted in place of a launch tube. A ballast weight rest on a platform and further includes a centering element, with support and bracing structure, so that the device is releasably coupled to an existing missile launch tube interface of the TOW.