Abstract: An aircraft emergency parachute deployment system (AEPDS) is disclosed. The AEPDS includes a parachute assembly coupled with an aircraft, a ballistic rocket assembly coupled to a top portion of the parachute assembly by a lanyard, an actuator for initiating launch of the ballistic rocket; and a control module configured to receive aircraft orientation measurements and controlling launch of the rocket when the spatial orientation the aircraft is within a pre-selected range of values.

Abstract: The present disclosure provides a propulsion system with a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system.

Abstract: The present disclosure provides a throwing device with a launcher and a propulsion system. The propulsion system comprises a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system. The launcher comprises: a tube for containing the propulsion system; and a trigger for triggering the ignition cartridge. A screw hole is in center of a bottom of the first chamber; nozzles are located around the screw hole; and a collar with a hole fixed in the bottom of the first chamber, wherein the ignition cartridge is fixed in the screw hole by the collar. The ignition cartridge comprises an explosive primer, and the launcher further comprises a firing pin triggered by the trigger to hit the explosive primer.

Abstract: A parachute device is provided for a divisible shell that includes an active body and a shell base. The parachute device includes two parachutes, a first, main parachute connected to the active body by parachute lines and a second parachute connected to the shell base.

Abstract: A shock mitigation assembly for a penetrating explosive weapon having a first explosive charge and a second explosive charge includes an electronic circuit card having an electronic circuit formed therein, a weight attached to the circuit card to form a circuit card subassembly, a housing enclosing the subassembly, and a hyperelastic material between the housing and the subassembly for internal shock mitigation. The hyperelastic material has a modulus of elasticity that remains elastic characteristics with shock, temperature, or a combination of shock and temperature. The housing may include a casing and a cover with corresponding features that mate with one another and prevent separation of the cover from the casing. The casing also may have an external spiral flange that overlaps an internal spiral flange of a support for the casing, with a hyperelastic material between the casing and support for external shock mitigation.

Abstract: An orbital debris interception vehicle includes a satellite bus and a debris interception module releasably coupled to the satellite bus. The debris interception module includes a debris impact pad, such as a pancake-shaped Whipple shield. A plurality of such vehicles can be deployed into an equatorial orbit and maneuvered to intercept orbital debris as it passes through the equatorial plane. In particular, the satellite bus can release the debris interception module before an intercept and reconnect to it after the intercept.

Abstract: The invention relates to the protection of spacecraft from debris and to de-orbiting devices of the atmospheric drag type, and to debris sweeping apparatus for the removal of debris from the space environment. The debris shielding apparatus for a spacecraft has a shield unit including a shielding surface for impeding incident debris. The shield unit is attached to the spacecraft body and has a drive mechanism for positioning the shield unit in relation to the spacecraft body. The drive mechanism is capable of moving the shield unit between a stowed first position and a deployed second position. In the deployed second position the plane of the shielding surface is at an angle to the spacecraft body.

Abstract: An orbital debris interception vehicle includes a satellite bus and a debris interception module releasably coupled to the satellite bus. The debris interception module includes a debris impact pad, such as a pancake-shaped Whipple shield. A plurality of such vehicles can be deployed into an equatorial orbit and maneuvered to intercept orbital debris as it passes through the equatorial plane. In particular, the satellite bus can release the debris interception module before an intercept and reconnect to it after the intercept.

Abstract: A system and method for deployment of a material or desirable product is included. A desirable product can include a combination of a pyrophoric material with a material adapted to be sublimated by pyrophoric effect and produce a desired effect such as, for example, type of dye configured to be an obscurant material with a desired effect after sublimation could be a visual obscurant, electromagnetic obscurant, or some type of pesticide. A system for deploying and storing the material could include a housing configured to seal the combination of dye and pyrophoric materials from the presence of oxygen so that the pyrophoric material does not react until selectively exposed to a gas. A selection and mix of the pyrophoric material with the material, e.g., dye can be accomplished in such a way that the reaction between the pyrophoric material and oxygen is not substantially impeded.

Abstract: The decoy method, of the type in which: an ejectable on-board decoy provided with a decoy charge (13) is enclosed inside a streamlined cylindrical body (9) mounted ejectably on the aircraft (1); the streamlined cylindrical body (9) containing the decoy is ejected parallel to the aerodynamic stream of the aircraft; the decoy charge (13) is removed from the streamlined cylindrical body (9) while keeping the decoy charge attached to said body; and the decoy charge removed from the body is operated to render it active.

Abstract: A pyrotechnically powered actuator having a bellows that provides a force and stroke upon initiation is disclosed. The actuator includes a housing body with a first end and a second end. The bellows is coupled to the first end of the housing body. A cover is coupled to the second end of the housing body. An initiator is located within the housing body and includes a pyrotechnic material and a bridge element. The housing body, the bellows, and the cover define a hermetically sealed chamber. The bellows is compact, lightweight, and can withstand internal and external pressure at least as high as 3,000 psi. An exemplary embodiment includes a housing body that provides a compartment for adding supplemental pyrotechnic material. Further exemplary embodiments of the actuator include a chip initiator that requires less than 1 amp to function in less than 10 milliseconds.

Abstract: The invention generally relates to a method of using a pod to rapidly deploy defensive countermeasures from a wide variety of manned aircraft. The method includes using a configurable pod for dispensing different types of infrared countermeasure (IRCM) devices and different types of radio frequency countermeasure (RFCM) devices at a rapid rate. The primary purpose of this method is to rapidly dispense IRCMs and RFCMs is to protect the host aircraft while ingress and egress maneuvers are performed in a hostile area. A secondary use of the method is for use in defending commercial aircraft from missile threats.

Abstract: A pyrotechnically powered actuator having a bellows that provides a force and stroke upon initiation is disclosed. The actuator includes a housing body with a first end and a second end. The bellows is coupled to the first end of the housing body. A cover is coupled to the second end of the housing body. An initiator is located within the housing body and includes a pyrotechnic material and a bridge element. The housing body, the bellows, and the cover define a hermetically sealed chamber. The bellows is compact, lightweight, and can withstand internal and external pressure at least as high as 3,000 psi. An exemplary embodiment includes a housing body that provides a compartment for adding supplemental pyrotechnic material. Further exemplary embodiments of the actuator include a chip initiator that requires less than 1 amp to function in less than 10 milliseconds.

Abstract: The invention generally relates to a pod based countermeasure dispensing system for external mounting on wide variety of manned aircraft. The pod based system is readily configurable for dispensing different types of infrared countermeasure (IRCM) devices and different types of radio frequency countermeasure (RFCM) devices at a rapid rate. The primary use of the rapidly dispensed IRCMs and RFCMs is to protect the host aircraft while ingress and egress maneuvers are performed in a hostile area. A secondary use of the pod based countermeasure dispensing system is for use in defending commercial aircraft from missile threats.

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: A method and an arrangement for discharging countermeasures from a carrier craft in the form of an aircraft or equivalent. The countermeasures are intended to be spread initially in the form of unit packs that, after they have left the carrier craft, are to screen the same from missiles approaching is guided by built-in sensors, or other threats. It is especially characteristic of the invention that the unit countermeasure packs are spread from the carrier transversely to the lying direction of the carrier craft.

Abstract: The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare disposed toward the rear of the projectile. The flare has petals that deploy from a first, stowed position to a second, deployed position upon the occurrence of the event. In the stowed position, the petals are aligned with the air stream, in order to minimize drag. In the deployed position, the petals project into the air stream in such a way as to move the lift center rearward. A slide ring within the flare has sufficient inertia that it shifts aft in response to an acceleration that occurs when the attached body and the projectile are separated from one another. The slide ring is linked to the petals in such a way that the petals are deployed by the displacement of the slide ring. Detents lock the slide ring in its displaced position.

Abstract: A flare apparatus including a shell case, an explosive assembly carried by the shell case, a flare cup located in the shell case and spaced apart from the first end of the shell case and having a closed end surface away from the first end of the shell case which is convex, a flare composition located in the interior space defined by the flare cup and a plug located in the interior chamber defined by the shell case and being in close proximity to the flare cup. The present flares are straightforward in construction, easy and inexpensive to produce and provide substantial performance benefits and substantial shipping/transporting benefits. In particular, the present flares are safer to ship/transport relative to conventional flares and can be shipped/transported under less restrictive conditions.

Abstract: Aerial training flare or flare simulator comprising a polymeric case, a begradable polymeric candle housing, and a candle comprising a pyrotechnic illuminant and an environmentally friendly, fast-burning ignition composition. An expulsion cartridge ejects the candle and the candle housing while the case is retained on the launching aircraft. The only major component of the flare which falls to earth is the partially melted candle housing, which is biodegradable and thus reduces requirements for environmental cleanup.

Abstract: A covert, i.e., no visible light emitted, multispectral day/night target marker is disclosed. The marker emits a signature detectable in the electromagnetic spectrum including visible, near infrared, middle and longwave infrared, and radar regions. The marker is particularly useful for marking of target areas so that they can be easily detected from the ground or the air. The visible spectrum is marked by a white or colored pyrotechnic smoke generant. The near infrared region is marked by near infrared emitting photodiodes encased in a hardened polymeric molding compound. These diodes are only visible through night vision devices (image intensifiers). The middle through the far infrared regions are marked by the heat generated from the combustion of the pyrotechnic smoke generant. The smoke generant is housed in a canister having a highly emissive surface. The radar region is marked using radar chaff. The target marker is configured for use with conventional mortar or rocket delivered flare systems.

Abstract: A pyrotechnic device for launching at least one projectile includes, in a longitudinal launcher tube closed at the rear by a rear wall, a closure member expelled when subjected to a longitudinal force exceeding a predetermined threshold and retaining at least one projectile on opposite sides of which are a front chamber and a rear chamber in which an impulse cartridge builds up a gas pressure simultaneously. In this way a plurality of projectiles can be fired sequentially by means of a single impulse cartridge.

Abstract: A smoke screen shell is provided having a rapidly burning decoy charge that generates a spontaneous fog and a slowly burning camouflage charge that generates a lasting fog. The decoy charge and camouflage charge are fired from a canister sleeve by an ejection charge. Upon firing, pressure from the ejection charge is communicated through a channel to a relief chamber positioned between the decoy charge and the camouflage charge. This results in an accelleration difference, causing a separation and slightly different trajectories, the decoy component accelerating at a higher rate. The decoy charge takes effect in the air prior to the camouflage charge. The collocation of the spontaneous fog and of the lasting fog essentially occurs in the target. The decoy charge and the camouflage charge land within a proximity at a target area such that a collocation occurs between the spontaneous fog and of the delayed lasting fog. The ignition and relief chambers, the channel therebetween, the charges, etc.

Abstract: The invention relates to a pyrotechnical head of the type comprising an elongate envelope, a pyrotechnical composition contained in the envelope, and dispersal means for dispersing said pyrotechnical composition. The dispersal means include longitudinal detonating fuses adapted to split the envelope longitudinally, and a transverse detonating fuse adapted to split the envelope transversely.

Abstract: The invention is a compressed gas rocket apparatus for deployment of emergency parachutes, rescue lines and similar payloads. A pressurized vessel is equipped with a stopping or sealing mechanism which, when removed or punctured, causes the pressure vessel to be launched. A drag line connected to the vessel pulls the payload away from the launch point, in the direction of the pressure vessel travel.

Abstract: A parachute deployment system for use with an illuminating flare warhead propelled by a rocket motor. The system employs a compact two-stage parachute system which includes a main parachute arranged within a main parachute cover and a drogue parachute arranged within a drogue chute cover. The main parachute pack and the drogue parachute are configured to be positioned in a side-by-side, detached relationship within the warhead. An extraction line separably connects the drogue parachute pack to the rocket motor and a support line connects the drogue parachute pack to the main parachute pack such that upon separation of the rocket motor from the warhead, the drogue parachute pack is extracted from the warhead prior to extraction of the main parachute pack. Upon deployment of the drogue parachute, the drogue parachute cover remains attached to the extraction line and acts as a deflector, inducing radial forces which act upon the rocket motor to prevent it from colliding into the warhead.

Abstract: A combustible ignition system for use in an illuminating flare warhead. The ignition system includes a pickup charge positioned contiguous the separation charge of the ignition initiator. The pickup charge is positioned such that the firing of the separation charge triggers combustion of the pickup charge. The pickup charge extends to a combustible train which comprises a continuous thin-layer explosive composition positioned within a plastic tubing. The firing of the pickup charge creates sufficient shock that the combustible train is detonated. The combustible train extends along the flare casing adjacent the parachute system and the illuminant. At the head end of the warhead, the explosive train connects to an output charge. The explosive shock of the explosive train is sufficient to detonate the output charge. The output charge transfers the combustion to a BKNO.sub.3 pellet basket within the illuminant igniter of the warhead.

Abstract: A deceleration device for a submunition unit includes a cartridge releasably attached to the submunition unit. A releasable package including at least one pocket is disposed in the cartridge and is connected to the cartridge by a packaging line. An auxiliary parachute and a rotation parachute are disposed in the cartridge, with at least the rotation parachute being accommodated in the at least one pocket of the releasable package and the auxiliary parachute being disposed in a pocket separate from the at least one pocket. The auxiliary parachute is connected to the cartridge and the rotation parachute is connected to the submunition unit. A deployment mechanism causes the auxiliary parachute to be deployed in advance of the rotation parachute after the cartridge is released from the submunition unit and the rotation parachute to be deployed after the cartridge is decelerated by the auxiliary parachute for decelerating the submunition unit.

Abstract: A nosecone/fairing for reducing the aerodynamic drag of an underwing mounted chaff and flare dispenser has the shape of a flattened paraboloid and covers only the generally square front of the chaff and flare dispenser. The nosecone/fairing is made of fiberglass and attaches to the chaff and flare dispenser by mounting holes in the nosecone/fairing located to align with preexisting holes in the unmodified chaff and flare dispenser.

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: Illuminating flare has an igniter in which a two-part inertial mass is gud for relative aftward movement from a safe position to an armed position under launching forces. One part of the mass undergoes relative forward movement to an ignition position under parachute-opening, deceleration forces while the other part of the mass is restrained from moving as far forward as the first part. This separation of the parts of the mass releases locking balls to unlock a firing pin, which stabs a primer and initiates ignition of the flare. The primer is contained in a rotor, and as the mass traverses from the safe position to the armed position it rotates and the rotor rotates with the mass. In the safe position the primer is out of communication with an ignition passage through which ignition of the illuminant composition occurs. Rotation of the rotor as the mass traverses to the armed position places the primer in communication with the ignition passage where it remains until activated by the firing pin.

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: An exercise firing projectile containing a plurality of pyrotechnic fragmentation devices are expelled from the projectile casing above the target area by an ejection charge, and delay tubes of the fragmentation devices are ignited at the same time by this charge through a central igniter tube contained within the projectile. The active charge of the devices consist of a grainy composite with quick reaction time.

Abstract: An army mortar shell having two sections linked to one another by linkages liable to shear and located to the rear of the sealing band, and where the head of such shell is equipped with a time fuse and inside the shell there are two interlinked chambers containing the charge which is released into the air when said two chambers are separated from one another due to the effect of a cartridge located inside the foremost chamber.

Abstract: A tether line is connected between a rocket launched flare and the canopy of a supporting parachute to cause the parachute to collapse and fall to the earth along with the burned out flare upon release of the single support cable.

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 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: A separating arrangement between multipart constructional elements, including an expansion chamber for at least one pyrotechnic charge which is bounded by the piston surface of a displacement or sliding piston. The separating arrangement has at least one gas passageway which communicates with the expansion chamber, through the intermediary of which a separating piston can be subjected to pressure. The combustion gas pressure of the pyrotechnic charges acts within the expansion chamber against different piston surfaces and thereby, in a constructively predeterminable manner, effects different successive piston movements, as a result of which the sequence of the individual separating operations which can be carried out in different directions predeterminably in a definite manner and functionally-dependent.

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: Located below an aircraft is a support rod (1) provided with female engagement members (10). Standard missile launcher modules are provided on their flat upper wall with counterpart male engagement members (20). The engagement members (10 and 20) cooperate in the manner of dovetails and for each module location, they are separated from each other according to the same geometric progression along the support rod (1) and the upper wall of the module (2). A device comprising a cam (27) and lever (273) makes it possible to ensure at the same time the translation necessary for locking of the dovetail, as well as the making of contact between the electrical connector members.

Abstract: An explosively separable casing including a cylindrical afterbody and a circular cover for one end of the afterbody is disclosed. The afterbody has a cylindrical tongue extending longitudinally from one end which is matingly received in a corresponding groove in the cover. The groove is sized to provide a pocket between the end of the tongue and the remainder of the groove so that an explosive can be located therein. A seal is also provided between the tongue and the groove for sealing the pocket from the atmosphere. A frangible holding device is utilized to hold the cover to the afterbody. When the explosive is ignited, the increase in pressure in the pocket causes the cover to be accelerated away from the afterbody.

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: Within a cylindrical container or canister, closed at both ends by a respective cover member, there is located a flare or illuminating rocket. For firing the flare rocket it is sufficient to remove the rear cover and by pulling at a tear line there is activated a tear ignition device or fuze. The ignited flare rocket then pierces the front cover member. This front cover member preferably possesses a ring-shaped or annular reference fracture location which subdivides the cover member into a disk-shaped inner portion and a ring-shaped outer portion.

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.