Abstract: The invention presented here is an add-in part designed for the M4 and similar commercial AR-15 rifle variants or any other weapon using an adjustable multi position receiver extension based on the M4 pattern. Its purpose is to be installed in the longitudinal adjustment slot of the receiver extension tube limiting the buttstock's maximum extension travel to a preselected position.

Abstract: A recoil dampening assembly for a firearm that includes a bolt assembly and a stock that is linearly moveable with respect to the bolt assembly, includes a plurality of elastically deformable shock-absorbing members having a compression cavity defined therein, and a plurality of rigid spacers interspaced between the shock absorbing members. The plurality of shock absorbing members and rigid spacers are adapted to be placed between a bolt assembly of a firearm and a stock of a firearm. The plurality of shock-absorbing members and rigid spacers are adapted to dampen the recoil as transmitted from the bolt assembly to the stock when a charge that is in the firearm is ignited by allowing each shock absorbing member to at least partially compress within the compression zone.

Abstract: A reversing panel assembly utilizable in an aircraft for the carriage and deployment of stores is disclosed. The panel has two pivot axes. The first pivot axis extends through the center of the panel, and the second pivot axis is parallel to the first and extends through a distal portion of the panel. A first and second cam follower are mounted on the first and second pivot axes, respectively, at each end of the panel. The first cam follower is movable laterally along a first guide track which is substantially parallel to the surface of the aircraft. The first cam follower is movable between a first position and a second position on the first guide track. The first position is centrally located relative to the opening, and the second position is distally located relative to the opening.

Abstract: A ordnance ejector apparatus (10) for ejecting an ordnance from an aircraft includes a mechanical linkage comprising a forward bell crank (36) and a forward connecting link (46) and a rearward bell crank (50) and a rearward connecting link (60). A rail (24) releasably retains an ordnance (16) thereto and is pivotally connected at opposite ends (26, 28) to the forward connecting link (46) and the rearward connecting link (60). Two pyrotechnically operated pistons (78, 88) are disposed in end-to-end relation and act independently on the forward bell crank (36) and rearward bell crank (50). The rail (24) includes a plurality of ordnance retaining hooks (152) which are automatically actuated to release the ordnance (16) when the rail (24) is extended by the mechanical linkage. A mechanical hoist (108) is manually operated by a screw shaft (110) for manually extending the rail (24) to attach an ordnance (16) thereto.

Abstract: A ordnance ejector apparatus (10) for ejecting an ordnance from an aircraft includes a mechanical linkage comprising a forward bell crank (36) and a forward connecting link (46) and a rearward bell crank (50) and a rearward connecting link (60). A rail (24) releasably retains an ordnance (16) thereto and is pivotally connected at opposite ends (26, 28) to the forward connecting link (46) and the rearward connecting link (60). Two pyrotechnically operated pistons (78, 88) are disposed in end-to-end relation and act independently on the forward bell crank (36) and rearward bell crank (50). The rail (24) includes a plurality of ordnance retaining hooks (152) which are automatically actuated to release the ordnance (16) when the rail (24) is extended by the mechanical linkage. A mechanical hoist (108) is manually operated by a screw shaft (110) for manually extending the rail (24) to attach an ordnance (16) thereto.

Abstract: A rail-type airborne missile launcher having a main launcher body for fixed attachment to an aircraft, and a sub-rail removably attachable to the underside of the launcher body to carry a missile, is further provided with individual hook modules that can be attached to the underside of the launcher body, when the sub-rail is removed, at selected locations along the launcher body to carry a variety of stores. Such hook modules can each carry a separate respective store or they can be employed as an oppositely-facing pair at a selected distance apart to both carry a single store. In the former case, the hooks will be operable separately, such as by electromagnetic means, for separate release of the stores; but in the latter case both hooks will be arranged to release simultaneously.

Abstract: A flying body, such as a missile, is strapped to a carrier vehicle, such as an aircraft, by a strapping or locking mechanism mounted in a housing which also includes components for suspending and launching the flying body from launching rails forming part of the housing connected to the carrier aircraft. The strapping is accomplished with two strapping bridges which are pressed down onto the respective suspension block elements resting on the launching rail. The pressing down force is applied by a toggle lever arrangement, one of which is provided for each strapping bridge. The toggle lever arrangement cooperates with a respective spring arrangement which keeps the corresponding toggle levers in a strapping position until the spring arrangement is released through release pawls operated with a reverse magnet. A retaining mechanism which is effective between the release of the strapping mechanism and the actual launching after ignition of the propulsion system of the flying body, is made ready for launching.

Abstract: A stabilizing system for use in conjunction with a crane/boom in which an ject is held fast to a foam cushion within the system. A hook that forms part of the system grasps a sling holding the object and secures the object against the foam cushion. The object can be aligned by being rotated or tilted while held fast to the cushion. The object is prevented from swinging and swaying, thereby greatly reducing danger.

Abstract: A missile launcher and missile snubbing apparatus (32) includes a pair snubber blocks (34, 36) slideable along angled side edges of a wedge (38). The snubber blocks (34, 36) are biased by respective springs (48, 50) in a first direction, while the wedge (38) is biased in an opposite direction by a spring (84). A spring biased cam (86) is operative to move the wedge (38) in a direction to reduce the effective width of the snubber block assembly (32) so that a missle can be downloaded from the rear of the launcher (10). A spring clip (85) is engageable with a rod (43) attached to the block (38), and responsive to the action of the cam (86) for locking the wedge (38) in a first position. The spring clip (85) is shaped so as to be responsive to the downloading of the missile (12) for releasing the locked wedge (38).

Abstract: Device for ejecting a load slung under an aircraft, designed to impart to this load, at the moment of its release, kinematic values controlled as a function of the instantaneous flight parameters of the aircraft at this moment.A plurality of separate modules (1, 2A, 2B, 4, 10) makes it possible, on the one hand, to execute a longitudinal translational movement (d) of the load (3) to detach it from the members (5) attaching it to the aircraft and, on the other hand, to carry out an accurate adjustment of the angular ejection speed. One of the modules is an energy source (1), such as a bottle of compressed nitrogen. Two other modules are respectively a front fluid jack (2A) and a rear fluid jack (2B), both with a retractable telescopic piston which, when the pressurized gas is supplied to it by the source (1), exerts an ejection force on the load (3).The invention is used for the release of loads carried by aircraft.