Abstract: An apparatus is disclosed for stage separation and thrust termination in a multi-stage missile having an upper stage detachably connected to a lower stage rocket motor. The apparatus includes a piston located at the forward end of the lower stage rocket motor in fluid communication with the motor's combustion chamber. The piston is configured with a plurality of venting passages, and capable of deployment from a stowed position, in which the venting passages are sealed, to an extended position, in which the venting passages are unsealed. The venting passages are preferably configured to vent the combustion chamber at an angle to the upper stage, providing the lower stage rocket motor with a component of thrust away from the upper stage after detachment without damaging the upper stage. In a preferred embodiment, means for detaching the upper stage includes attachment bolts connecting the stages and explosive detachment charges configured to shear the bolts.

Abstract: A bullet stop and containment chamber for stopping the forward momentum of projectiles traveling in a generally horizontal zone of projectile travel. The bullet enters the wide end of a channel having plates which guide the bullet into a narrow opening which leads into a containment chamber. The containment chamber has a series of plates arranged with increasing angles of incidence such that the sequential impacts are increasingly direct. There are also side plates on the chamber which combine with the other structure to confine bullets, fragments and particulate matter to the chamber until inertial momentum is arrested and the bullet drops out of an egress.

Abstract: A missile defense system generates a change in density in the air path of a missile. The density change is created by a high-pressure water system which can be generated by a water jet or a body of water explosively created from a water surface. When operating against a waterborne missile, the density of the water medium is changed. The change in density creates an effective barrier against an incoming missile.

Abstract: A device for storing a missile 8 includes at least one adjustable and spring-loaded support point 11, 31 and at least two fixed support points 12 and 32 each are present in a launcher tube in the front and in the rear. The front support points 11, 12 act on support pins 10 arranged on the jacket of the missile 8, and the rear support points 12, 32 act on sliding ribs 35 arranged on supports 33 for wings 34 that can be folded out, wherein all support points are supported on frames 3 and 4 of a launching container 1.

Abstract: A rigid thermal sleeve 5 mountable over at least part of a gun barrel 3 in such a way that it is symmetrical about a longitudinal plane A--A to provide a reduced thermal image and radar cross section. The sleeve 5 comprises thermally insulating material 13 between an inner skin 15 and an outer skin 17. The outer skin 17 is arranged to have two mutually convergent planar faces 7,9, each one of which makes up at least 15% of the outer surface of the sleeve 5 and which have a mutual line of convergence extending externally and longitudinally of the sleeve 5.

Abstract: The present invention falls within the sector of infrared or electrogmagnetic decoys for protecting light aircraft or helicopters. It relates more particularly to pyrotechnic cartridges and to ammuniton comprising racks receiving the cartridges. This invention makes it possible, for the same volume of ammunition, to have a larger number of shots and to carry out the loading of the ammunition simply and quickly. The cartridge (1), consists of a sole (2) fixed to a case (3), in which are accommodated a plurality of assemblies (11) comprising pyrotechnical ejection charges (6), pyromechanical assemblies (7), ignition charges (8), effective charges (9) and the caps (10). The case (3) is provided with a plurality of receptacles and comprises at its base either a blocking device (4) or a gasket which is seated in a groove (41).

Abstract: A gas propelled line deployment system includes a launch tube, and a bullshaped projectile. The launch tube has a closed end with a gas port formed therein and an open end having a plurality of radially extending threaded apertures. The projectile has two spaced, circumferential grooves adjacent the blunt end thereof, with an O-ring mounted in one of the grooves. The projectile is slidably received in the launch tube with the blunt end adjacent the open end of the tube, i.e. the rounded end facing the close end, so that O-ring forms a gas tight seal adjacent the open tube end. Nylon retainer screws are threadedly received in the threaded apertures so that they engage within the other circumferential groove in the projectile. The line to be deployed is attached to an elastic band which is attached to the blunt end of the projectile. A carbon dioxide gas canister communicates with the gas port to introduce a pressurized gas flow into the tube.

Abstract: A missile launching system (18) for launching a missile (20) includes an automatically telescoping launch tube (22, 24) and a rest raining system (40, 42). The telescoping launch tube (22, 24) lengthens the period of guided travel of the missile (20) during launch, to improve its accuracy. The launch tube system has an outer case (24), and an inner launch tube (22) internally dimensioned to receive the missile (20) therein and externally dimensioned to slide within the outer case (24) from a rearward position to a forward position. The restraining system (40, 42) holds the missile (20) and inner launch tube (22) at the proper locations before and during firing, and includes a releasable holdback (40) for the inner launch tube (22) at the rearward position and a releasable holdback for the missile (20) at a preselected position within the inner launch tube (22).

Abstract: A method of separating from one another subcombat units transported by a rotationally-stabilized carrier body to a predetermined target area. The method comprises the steps of:ejecting the subcombat units and a plurality of masses or bodies from the carrier body;utilizing rotational energy from the rotationally-stabilized carrier body to generate axially directed separation forces in the masses or bodies, the separation forces acting concentrically in relation to a common center axis of the carrier body; andseparating the subcombat units from one another so that they spread out and each cover a predetermined portion of a target area by utilizing the separation forces in the masses or bodies to cause the separation of the subcombat units after their ejection from the carrier body.

Abstract: A firearm safety device including a tube assembly which is insertable through the barrel and/or and through a portion of the cartridge chamber. A stop assembly is disposed in the tube assembly. The stop assembly has a locking position and an unlocking position. In the locking position, a portion of the stop assembly extends a distance from an outer peripheral surface of the tube assembly for engaging a portion of the firearm and preventing removal of the tube assembly from the barrel and the cartridge chamber. A plunger is disposed in the tube assembly. One end of the plunger is engageable with the stop assembly for moving the stop assembly to the unlocked position. A blocking device is disposed in the tube assembly for preventing the plunger from engaging the stop assembly and moving the stop assembly to the unlocked position.

Abstract: A weapons system that fires projectiles of 20 to 500 millimeters or larger in diameter using a compression-ignition combustion of common fuel oils in conjunction with pre-compressed air as the firing force, in which automatic breech loading occurs during resetting, to enable a continuous, automatic rapid fire. Fuel pumped at a high pressure enters a combustion chamber, previously filled with high pressure air from an external compressor, where an extremely rapid combustion occurs, resulting in compression of the air in a charge chamber. A control valve then opens, allowing compressed air from the charge chamber, where high pressure fuel is then injected and instantly vaporized and combusted to propel a projectile through a barrel. A loading ram concurrently engraves the next round into a breech block chamber. In the resetting process, the valve reseats, air from an external compressor enters the combustion chamber via a check valve, and the combustion chamber is vented to the atmosphere.

Abstract: A cylindrical alongated extender element (20,60,72,80) of various incremental lengths has a bore (22) and a first end portion formed with a sleeve portion (24) and threaded portion (26) adapted to be received in the choke receiving seat (14) formed in the bore of a shotgun barrel. A sight (46) is mounted on a rib (40, 68, 76) which is coextensive in length with the extender elements to provide an improved sight picture. The extender elements are adapted for use with a single barrel gun or a double barrel over-and-under and side-by-side arrangements. With the over-and-under arrangement a rib assembly having a single tubular portion mounting the rib is mounted on an adaptor seat of one of the extender elements and with the side-by-side arrangement a rib assembly has first and second tubular portions mounting the rib and received on adaptor seats of two extender elements. The extender elements can optionally, in turn, be provided with choke receiving seats.

Abstract: A composite core for a hollow gas turbine engine blade is constructed by forming a first core part determinative of the cavity size of the trailing edge blade portion from a first ceramic material and joined to a second core part determinative of the blade cavity for the blade body portion which is formed from a second ceramic material. The first and second ceramic materials can be chosen to have appropriate characteristics grain sizes, flowability, leachability, and/or reactivity characteristics taking into consideration the different dimensional restrictions imposed by the desired blade product. A tongue is formed on the adjoining edge surface of the trailing edge core part, and the trailing edge core part is then inserted into a second die and the body core part is formed, including a complementary groove member which is formed around the tongue member on the trailing edge core part. The joined trailing edge and body core parts can then be sintered to form a composite casting core.

Abstract: The joint construction comprises a coupling ring slidably received in a motor tube connected to the front end of the military rocket motor. The coupling ring is formed with longitudinal slots alternating with flexible fingers having locking projections engageable with a locking channel and an adjacent locking flange within the tube. An adapter ring is connected to the warhead by first screw threads and is adapted to be connected to the coupling ring by second screw threads including external threads on the adapter ring and internal threads in the coupling ring. The adapter ring has a reduced tapered end portion for receiving a wedging tapered expansion ring made of a eutectic metal alloy having a low melting point. As the second screw threads are engaged, the expansion ring flexes the fingers outwardly by a wedging action and causes the projections to interlock with the channel and the flange.

Abstract: A stream of hydrocarbon fuel is catalytically decomposed to produce hydrogen and lower molecular weight fuel fragments, which may separated by molecular size. The hydrogen and low molecular weight fuel fragments are introduced along with a stream of nondecomposed hydrocarbon fuel into the combustor of a high speed propulsion unit. The method results in a wider combustor operating range, with higher combustion rates and increased flame stability, achieved through more rapid diffusional mixing. The process effectively extends the operating limits of gas turbines, and especially ramjet and scramjet combustors.

Abstract: The invention relates to an igniter mechanism for a pyrotechnical gas generator of a vehicle occupant restraining system in which either an impact member or the gas generator for actuating the belt tensioning action is pretensioned by at least one spring so that the spring loads the impact member in a first direction against a stop. In addition the spring counteracts movement of the impact member in a second direction as a result of the forces of inertia acting on acceleration of the vehicle by means of a force which grows until a center position is reached. Force conversion means are provided to convert a torque generated by said spring into an axial force applied to said impact member.

Abstract: A firearm safety cartridge lodges a projectile in the breech end of the barrel of the firearm to prevent live ammunition from being inserted into the firing chamber of the firearm.

Abstract: A separation device (23a-23d) comprises a frangible joint (24a-24d) comprising joinder flanges (27a, 27b) interconnected by walls (126a, 126b, 226a, 226b, 326a, 326b, 426a, 426b) having fracture grooves (28a, 28b) and defining a channel (36a-36c) therein. Within the channel (36a-36c) is disposed an expansion member (10, 10a, 10b) containing a detonation charge (16) and having expansion regions (34a-34c, 134a, 134b) that expand upon detonation of the charge (16). The expansion region bears against walls at the junctions (32a, 32b, 32b', 132a, 132b, 232a, 232b) thereof with joinder flanges (27a, 27b) to provide separation thrust as well as causing frangible joint (24a-24d) to fracture at fracture grooves (28a, 28b).

Abstract: A fractionable trigger lock that prevents accidental discharge of a firearm. The device comprises two side guards which fit within the trigger guard of a firearm and are held together by a spindle with a fractionable connection. When in place, the trigger may not be engaged. To gain access to the trigger, a force must be exerted to the spindle in order to sever the connections between the spindle and side guard, thus releasing the trigger lock from the trigger.

Abstract: An automatic cannon, especially for cylindrical, telescoped shells, comprises a receiver in which is rotatably mounted an interconnected gun barrel and barrel extension or rotor. The rotor is connected to a power source, which may be an external source, for being driven at a relatively uniform rotational velocity for firing. A chamber having two laterally spaced apart, feed through, shell-holding cavities, is radially slidably mounted in a centrally located, transverse rotor aperture. Three cooperative camming means, responsive to rotor rotation, cause shell feeding, firing and ejection. Shell camming means simultaneously transport shells from an associated feeder into the chamber cavities and fired shell casings from the chamber cavities to a receiver ejection port.