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: This device concerns missiles and in particular those made up of a payload stage in the form of a sub-munitions cargo-container and a propulsion stage. It is intended for the separation and aerodynamic braking of the propulsion stage at the end of its operation so that the sub-munitions can be released without the risk of hitting it. It includes attachment by fitting and locking by shear screws of the two parts of the missile, an inflatable bag arranged in an annular housing, a mobile piston used to separate the two parts of the missile, an initiatable gas generator driving the mobile piston then inflating the bag, means of initiating the gas generator consisting of a primer and firing pin and sensitive to a drop in pressure of the gases in the propulsion stage.

Abstract: This invention provides provides a separable nosecap for the forward end of a homing torpedo, the nosecap and torpedo comprising a missile that is launched into the atmosphere for a ballistic trajectory to a distant underwater target. The nosecap comprises a nosecap shell having a volume of rigid cushioning foam material within its interior space defining a cavity into which is mounted a pneumatic apparatus including a flexible inflatable sleeve for forcefully disengaging the nosecap from the torpedo after the missile has entered the water environment. The inflatable sleeve engages the forward end of the torpedo and, upon inflation and axial extension, the sleeve disengages the nosecap from its mounting to the torpedo such that a homing mechanism of the torpedo may guide it to the intended target.

Abstract: A munition release system for carrier weapons is disclosed. Mechanisms for disengaging and ejecting munitions from the carrier housing operate in response to a common gas generator. Disengagement from the housing is effected just prior to ejection. Use of a common gas source improves reliability, while coordinated disengagement and ejection minimizes forces exerted on the munitions.

Abstract: This invention provides a system and method for ejecting munitions from carrier weapon housings through the inflation of inflatable bags, without imparting excessive acceleration loads to the munitions. The current invention combines the features of a ballistically tailored propellant grain with control nozzles to provide hot gases to an inflatable bladder in a fashion that permits control and tailoring of the acceleration pulse.

Abstract: A rocket glider stabilization system wherein a releasable, granular, counterweight, or ballast material is provided in the forward end of a model rocket aircraft to offset the weight of a tail mounted rocket motor assembly. The counterweight ballast material is releasably maintained in a counterweight bay formed at the opposite end of the model glider fuselage from the rocket motor. A rocket body tube connects the rocket motor with the counterweight bay and, when the ejection charge of the rocket motor is ignited, the ejection charge pressure ruptures or opens a retaining structure to release the ballast and maintain the desired center of gravity for glide flight of the rocket back to the ground. At least one adjustable or fixed trim tab is employed on at least one of the flight surfaces to induce the desired glide path return for the model aircraft.

Abstract: Method and apparatus for automatically attaching a substantially U-shaped support stand to a fusee includes an annular indexable turntable provided with holders for receiving support stands at one workstation, and fusees in assembled relationship with the support stands at another workstation. The support stands are deformed from substantially straight shapes to substantially U-shapes as they are loaded into the holders on the turntable. The free ends of the support stand are subsequently inwardly curled prior to assembly with the fusees. The fusees are fed from a supply hopper, cleaned, and successively inserted into a holder on the turntable in assembled relationship with successively presented support stands.Subsequently, the turntable is indexed to additional workstations where predetermined lengths of polyfilament tape are successively applied to end portions of the fusees, and subsequently wrapped about the fusees and associated end portions of the support stand to securely join one to the other.

Abstract: A flare (1) for submarine use. The flare (1) is caused to be deployed from a submarine location where it will rise to the surface of the water because of its buoyant casing. A hydrostatic valve means (147) is provided within the casing and it opens when the flare is at or near the surface of the water to render said flare ready to project a flare composition (5) into the air. The hydrostatic valve means (147) is held inoperative by a latch mechanism (51) which is tripped as the flare is deployed from a firing tube at the submarine location. The flare composition (5) cannot be projected into the air until the flare (1) is within a range of vertical attitude determined by inclination means (13). The flare composition (5) cannot be projected into the air until the nose is above water. The flare (1) thus has a sensor (23) at its forward nose to determine that the nose is above the water.

Abstract: An emergency signalling device comprising an elongate shell to be fired into the air. The shell encloses a combustible propellant charge, combustible material for generating a visible smoke trail, combustible material for generating a visible spark trail, at least one explosive charge for generating an audible report, a multiplicity of radar chaff particles, and an explosive ejection charge for distributing the radar chaff particles from the shell once the shell has been propelled beyond a predetermined altitude. An ignitor wire is provided which is in contact with the propellant charge. The shell is enclosed in a barrel for storage and launching. The barrel has an external thumbstop to prevent recoil from pushing the barrel back through the hand of the operator. There is a bulkhead at the closed lower end of the barrel, on which are mounted electrical contacts connected to the ends of the ignitor wire.

Abstract: A pyrotechnic assembly has an outer container for a plurality of pyrotechnic elements, each of which has a propellant charge, to propel the element out of the container, and a pyrotechnic charge, for example for producing a radiation-blocking screen. The container may be used as a fixed launcher for the elements or may itself be a projectile or missile from which the elements are ejected in flight. A plurality of different pyrotechnic charges may be included in the element.

Abstract: It is important with a sabot projectile to reliably fasten the projectile core or body in the sabot tail. This should be achieved without the need for circumferential grooves in the projectile core or body for fastening such projectile core or body in the sabot tail. Furthermore, the projectile core or body should be fastened in the sabot tail without the aid of the sabot jacket. This is achieved in that an attachment or fastening sleeve of the sabot tail extends to the substantially conical-shaped tip of the projectile core or body and bears against this substantially conical-shaped tip in order to prevent the projectile core or body from falling out of the sabot tail.

Abstract: A missile having a kinetic energy warhead is disclosed comprising a two-tiered cutter element (12) of fragmenting material and a forward cutter ring (16). The arrangement is designed so that the forward cutter ring (16) penetrates the target outer skin while the two-tiered cutter element fragments and passes through the perforation made by the forward cutter ring.

Abstract: The controlled explosion projectile ejection system utilizes a source of combustible gas through a controllable input valve into a combustion chamber. Inside the combustion chamber is a sparking means. After the chamber is loaded or filled with gas, a spark control signal is applied to the sparking means and the gas ignites. At the output of the chamber is disposed a controllable output valve. In a simple embodiment, the output valve is simply a valve head biased against the output port of the chamber thereby inhibiting any gas flow from the chamber unless the pressure in the chamber exceeds the biasing force against the valve head. After ignition, the gas expands and the resulting pressure is much greater than the biasing force on the output valve head and the valve opens. Downstream of the output valve is a barrel with the projectile loaded therein. The expanding gas passes through the output valve and ejects the projectile from the barrel.

Abstract: An enabling device 24 for a gas generator 42 of a forced dispersion munitions dispenser 10 includes a housing 58 in which and formed a bore 60, an outlet lead 88 and a detonator opening 68 in which is positioned an electrically initiated detonator 70. A piston 62 is located in the bore 60 and has a disabled position and an enabled position. A safety groove 64 is formed in the outer surface of the piston 62, and a safety passage 72, a safety aperture 74, 75 and a transfer lead 86 are formed in the piston 62. A gas generator 42 containing a quantity of pyrotechnic material 84 is mounted on the housing 58. The gas generator 42 is provided with a safety outlet 46, 47 and an inlet lead 44.

Abstract: A gas generator is provided for ejecting projectiles from a container under utilization of a developing gas pressure in an expansion chamber, using alternating propellant explosive charges hoses and ignition charge hoses in a string. String branching can be provided for.

Abstract: A tandem arrangement of a flare and a booster rocket motor is held together by a hollow coupler having hinged spring-loaded wall segments resembling barrel staves that are released on launch to function as a braking device, similar to a drogue parachute. The coupler also contains the main parachute which is released when the rocket motor is separated from the flare. The spring loading on the coupler wall segments controls the parachute drag area as a function of air speed enabling a relatively constant deceleration rate to be realized during the transition from high speed to the final descent velocity.

Abstract: Device for producing a series of consecutive decoy clouds, in particular infrared decoy clouds which move progressively away from the actual target, in which several projectiles (A, B, C, D, E, F, G) are arranged within a thin walled discharge tube (1), each projectile is practically of identical construction and has a separate ignition disintegrator unit (10) for disintegrating it and for igniting and scattering the combustible charge (18) to form a decoy cloud, a separate ejection chamber (27) provided with a propellant charge cartridge (28) is provided on each projectile, each propellant charge cartridge (28) can be ignited via a separate electrically actuated ignition lead (5) by means of a command controlled ignition distributor unit (69) and each projectile has a separate percussion fuse (47) for the ignition disintegrator unit (10) which can be actuated by releasing its safety device (360 mechanically, its safety device (36) only being released after ignition of the propellant charge cartridge (28) wit

Abstract: The invention proposes the launching or re-entry pods, individually or in oups, from a launching platform, so directed as to precede the entering body throughout the atmospheric trajectory, and containing therein chaff material or bundles to be dispensed therefrom at programmed intervals whereby the chaff material is scattered over a larger area ahead of the entering body so that receiving radar will track the chaff material rather than the body, thus confusing during the atmospheric re-entry of the body.

Abstract: A firing mechanism for projectiles comprises a housing (42) having a bore (50) in which a firing pin (54) is slidably mounted under the influence of a spring (70). Leaf springs (72) formed in the housing wall hold the firing pin in a safety position until released by movement of a slider (82) caused by aerodynamic drag forces acting on deployable fins (96) or a parachute (92).

Abstract: An aerodynamic braking arrangement for projectile components which are to be salvaged, such as detonators, consisting of a drag parachute having a high air-resistance index and of cables which connect the projectile components with the parachute. The drag chute is formed as a brake basket which consists of two cup-shaped tops at the ends thereof constituted of metal or plastic material, which are separated from each other along the axial direction of the projectile through the intermediary of at least one space formed of metal or plastic material, wherein the cables are fastened to one of the tops.

Abstract: A system for multistage aerial dispersion of materials or substances in mte form to provide an aerial array of interspaced clouds or cloud-like patterns of such materials or substances. Although the materials or substances may be in the nature of fertilizers, pesticides, herbicides and the like, suitable for domestic applications, there is basically disclosed a system for military applications. In this latter regard, rapid multipositional aerial dispersion of decoy material, such as thin metallic strips, chaff, or the like, to deceive or confuse enemy radar is achieved by packaging the decoy material in a carrier missile structured to carry a plurality of separate frangible canisters or modules respectively containing the decoy material in the form of a myriad of such metallic strips or chaff.

Abstract: Electro-magnetic decoy-launcher ammunition has an external housing, which houses an impeller in its lower section and encloses a charge of electro-magnetic decoy material which can be ejected by a thrust device when the impeller is excited. The charge remains in its tubular transfer container, and the thrust device is mounted within the transfer container and comprises a semi-rigid disc actuated by a piston, fitted with a peripheral projection, which defines with the disc an annular housing for a split ring for taking up play and a felt washer ensuring that the device is fireproof.

Abstract: A tandem rocket launcher is provided by mounting plural rockets in an elongated launch tube with associated guide and launch equipment for each rocket. A conical shield is placed between the rockets which deflects exhaust gases generated by firing the forward rocket away from the rearward rocket. The shield is then removed by firing of the subsequent rocket or pivoting of two halves of the deflector away from the path of travel of the subsequent rocket.

Abstract: A signaling device to be launched underwater having a fuze body, a time dy element, an ejection charge and at least one carrier having a pyrotechnic composition attached to a parachute. The ejection charge is ignited by an electric squib which is detonated by voltage from a sea water battery. The battery is sealed from sea water until a valve opens to permit entry of water into the fuze body. An electronic deplay module is electrically connected between the sea water battery and squib to delay detonation of the ejection charge until the signaling device has assumed a stable vertical position at the water surface.

Abstract: A projectile (1) containing particles of interference material is fired pneumatically from a launching tube (2). Compressed air, which is supplied to the launching tube and acts on the rear face of the projectile during firing, is conducted both to a loading chamber (19) wherein the air pressure is maintained even after the projectile has left the firing tube, and also via the loading chamber to an expansion chamber (20) in which, after a specific time-lag corresponding with a certain launch height on the trajectory of the projectile, an over-pressure builds up which causes the expansion of the chamber to be initiated with simultaneous expulsion of the interference material from the projectile. The compressed air may also be conducted to the chamber (10) in the projectile wherein the interference material is accommodated, tightly packed, in order to enhance the dispersion thereof.