Abstract: The present inventor recognized that children's interest in conventional water rockets can wane rapidly over time, particularly as children are drawn to other types of toys, such as video games. Accordingly, the present inventor devised, among other things, one or more exemplary water rocket systems or assemblies that include a removably mounted action figure. In some embodiments, the water rocket includes two hollow fuselage structures joined via a crossbar structure, with the action figure mounted to the crossbar structure.

Abstract: A radar reflector operating device for indicating an emergency position, capable of permitting a victim to indicate his location by means of a radar reflector even when he is dropped into seawater without a life jacket, easily actuating the radar reflector by pulling or pressing a switch even when low seawater temperature dulls a victim's consciousness and senses of fingers, arms, etc., maintaining an operation of the radar reflector due to safety means even without sustenance of power by a victim that applies power in a predetermined level to operate the radar reflector, allowing an appropriate reflection section and distant recognition by preventing the radar reflector with hydrodynamic wings from being lowered due to wind, etc., and securing a victim, who cannot swim, against dangerous environments by rendering him to use the radar reflector as a life buoy, holding the wings by hands to float on the sea.

Abstract: A system and method of detecting, processing, and selectively responding to radio frequency transmissions detected by at least one projectile deployed above a geographic area.

Abstract: A system and method of detecting, processing, and selectively responding to radio frequency transmissions detected by at least one projectile deployed above a geographic area.

Abstract: Parachute signaling rockets in which the parachute (18) is connected to the effect charge (14) in the form a plug connection (16). This plug connection (16) can be made automatically, so that there is no longer any need for the previous manual connection of the parachute (18) to the pyrotechnic effect charge (14) for the parachute signaling rocket according to the invention.

Abstract: Rapidly deployable restraining systems and methods for rendering personnel, nimals and other objects immobile includes an assembly of confinement devices housed in a dispersion package. Each confinement device has a propellent, a primer and an inflatable bag that is rapidly inflated by the propellent when fired by the primer. A detonator, located in the package, is discharged to open the package, disperse the confinement devices and cause the primers to be energized, thereby inflating the bags. The package is pre-emplaced in a target area or it is projected into the area via a fired projectile of which it is a part.

Abstract: The present invention is directed to an apparatus and method a flat-side model rocket. In the preferred embodiment, the model rocket is four-sided, and may be constructed by a user from wooden pieces that are pre-cut and pre-engraved with a sealed-CO.sub.2 laser. The model rocket of the present invention is compatible with existing model rocket engines, launching apparatuses, and parachute-type recovery apparatuses.

Abstract: A rocket-fired visual signalling apparatus and method includes a rocket, an elongated streamer having a first end portion connected to the rocket and a rocket launcher for launching the rocket so that the rocket pulls the streamer into the air such that when the rocket burns out, the streamer is spread out over the surrounding ground cover to facilitate visibility of the streamer.

Abstract: Rapidly deployable restraining systems and methods for rendering personnel, nimals and other objects immobile includes an assembly of confinement devices housed in a dispersion package. Each confinement device has a propellent, a primer and an inflatable bag that is rapidly inflated by the propellent when fired by the primer. A detonator, located in the package, is discharged to open the package, disperse the confinement devices and cause the primers to be energized, thereby inflating the bags. The package is pre-emplaced in a target area or it is projected into the area via a fired projectile of which it is a part.

Abstract: A missile includes, as viewed successively in flight direction, a booster, a folded drag chute in a parachute housing, a cruise engine and a warhead. The booster is detachable from the drag chute before the opening of the drag chute and the drag chute is detachable from the cruise engine upon the activation of said cruise engine. The drag chute is accommodated in a parachute housing that is closed toward the booster and is open toward the cruise engine to which the booster is connected via a positive locking releasable due to axial tensile force. A separating charge for detaching the booster from the parachute housing is arranged between the booster and the base of the parachute housing at the booster side. The booster is connected to the parachute housing via a mechanical parachute release mechanism for releasing the drag chute from the parachute housing with a delay in comparison to the ignition of the separating charge.

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: An IR decoy which includes an aerodynamic shell from which is deployable an aerodynamically shaped thin film, high temperature, high strength plastic bag. A first stage of a two stage gas generator initially deploys and inflates the bag while the second stage maintains the bag in its inflated condition and provides IR radiation within a desired wavelength band to which the plastic bag is substantially transparent.

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: Parachute ejection and recovery system for rockets which protects and permits recovery of the entire rocket after launch including means for cooling ejection gases, means for directing the cooler ejection gases for using in ejection, the nose cone and parachute therefrom during flight, and means for controlling descent of the rocket body, its nose cone and a parachute associated therewith.

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 article of submunition which is harnessed as a rotating load through the intermediary of a connecting device to the shroud lines of a parachute. The connecting device is designed as a torque or rotational moment-transmitting spreader arrangement for the radial spacing of the coupling of the shroud lines to a spin line carrying the load; whereby a coupling device is positioned between the connecting device and the spin line, in which the coupling device is constructed as a load-dependent slip coupling for the reduction of the torque which is transmitted from the spin line to the connecting device.

Abstract: The invention relates to a projectile including a cylindrical receiving chamber (4) delimited by an interior wall (3) for a braking parachute (17) which can be ejected by way of a piston (9) that is longitudinally displaceable in the projectile, with the piston (9) being chargeable by an ignitable pyrotechnic charge (10). The braking parachute (17) is encased in a longitudinally divided sleeve (18) one side of which is in engagement with the piston (9). In order to completely or partially recover the projectile and not to impede deployment of the braking parachute (17), it is provided that the rear of the receiving chamber (4) is sealed by a cover (23) which can be ejected by way of the piston (9), is equipped with a rotational imbalance (26) and is in engagement with the other side of the sleeve (18). The braking parachute (17) is fastened to the piston (9).

Abstract: A carrier projectile for aerodynamically braked submunition which can be ejected rearwardly from the tail end of the carrier projectile while contacting a cup-shaped base of the projectile. The carrier projectile has the inner edge of the fabric of a braking sail retained within the cup-shaped recess of the base of the projectile, with the outer edge of the fabric of the sail being equipped with centrifugal masses or flyweights mounted in proximity to the opening of the cup-shaped recess in the base. Provision is made to arrange the fabric of a radially outwardly tensionable braking sail in the already available recess in the base of the projectile, the braking sail being extended through the pulling action exerted thereon from the centrifugal flyweights.

Abstract: This invention relates to a small scale semi-submersible boat for naval combat comprising a hull of which a first, water-tight part is insubmersible and a second part is submersible.In the submersible part of the hull is accommodated at least one balloon or caisson serving as float which has a wall capable of being perforated and is inflated by means of a gas to enable the boat to float, the said boat also having a device for perforating the wall of the aforesaid balloon or caisson of a similar boat of an opponent, so as to damage the buoyancy of the opponent's boat.

Abstract: A pyrotechnic, aircraft carried bomb such as a smoke bomb, illumination b, flare bomb and the like. The bomb comprises detachable delay and nose sections and two main body sections separable from each other and each holding a pyrotechnic charge. The tail section houses a braking parachute which is deployed by the action of a time fuze upon release from the carrier aircraft. The tail and nose sections further house each a main parachute associated each with one of the main body sections. After a certain delay the deployed braking parachute starts an ignition train which causes ejection of the tail and front sections, deployment of the main parachutes, separation of the two main body sections from each other and ignition of the pyrotechnic charges therein. The two main body sections parachute down and reach the ground in soft landing with the pyrotechnic charges burning during the descent and, if desired, they may be arranged to continue to burn for a while after landing, e.g. in case of a smoke bomb.

Abstract: A system for transferring cargo at sea by helicopter includes an automatily activated self inflatable apparatus for reducing the velocity of the cargo if jettisoned or inadvertently dropped into the sea and for keeping the cargo afloat until retrieval may be accomplished. The cargo is lifted by a support sling attachable to a helicopter suspension cargo hook and simultaneously connected to a second sling in parallel to the helicopter through the rapidly deployable retardation and floatation device. Release of the support sling causes the cargo to drop and initiate deployment and inflation of the ribs of the parachute thereby retarding the cargo's descend and providing buoyancy for its floatation.

Abstract: A two stage parachute recovery system for use in recovering fuzes or other ensitive equipment from a projectile that has been launched from a gun barrel wherein explosive means are successively detonated by a timing mechanism and by centrifugal force imparted to the projectile respectively so as to deploy each of the said parachutes and to thereby recover the fuze before impact.

Abstract: A projectile having a payload, a first brake system and a second brake system at one side of the payload. A first explosive charge and a second explosive charge, separated from one another by a drive disk, are arranged at the other side of the payload and surrounded by a hollow projectile jacket.In order to render as simple as possible the construction of such projectile and in order to make available for the payload as large as possible part of the cross-section of the projectile, there is provided a latching or locking location at the projectile jacket for a container and the payload. The container and payload can remain in the projectile jacket as long as the initially effective brake system brakes the projectile. For slowly lowering the payload with the other brake system the payload leaves the latching location and thus the projectile jacket.

Abstract: An improved parachute recovery system for a gun fired projectile is discld. The projectile has a nose, a payload and a base section. The base section has a hollow cylindrical parachute cannister which is separated from the base section by rearward motion of an internal piston which is actuated by expulsion gas pressure initiated by a time fuze. The parachute cannister is thereby exposed and jettisoned to cause inflation of a parachute attached to the base section so that the parachute floats down in a nose-deployed projectile position for a soft landing and recovery. Also disclosed are alternative embodiments of a projectile base-deployed parachute recovery system.

Abstract: A gun fired, artillery projectile and parachute recovery system for fin-silized, non-spinning projectiles. It has a a cylindrical payload with several fins mounted at its rear end and a conical nose section attached on the front end. The nose section has a base attached to a hollow windshield by frangible shear pins. The windshield encloses a parachute housing containing a parachute assembly attached by a bridle line to the base at a base pin. A time fuze at the forward end of the windshield activates an expulsion charge capable of separating the windshield from the parachute housing. A deployment spring attached between the base and parachute housing at one side ejects the parachute assembly from a side of the parachute housing far away from the fins. Thus upon firing the projectile at an angle of from about 40.degree. to about 85.degree.