Abstract: A joint system including a support device with a plurality of radial extensions extending in at least a first direction from the support device, each individual radial extension of the plurality of radial extensions terminating at a distal engagement end and a receiving device separate from the support device with a notch area to receive the distal engagement ends of each radial extension of the plurality of radial extensions and a contact area upon which a length of the radial extensions of the plurality of radial extensions engage when the distal engagement end of each radial extension of the plurality of radial extensions are engaged within the notch area. At least one radial extension of the plurality of radial extensions is configured to be flexible between a first position to provide for at least one of assembly and disassembly of the support device to the receiving device and a second position when the support device and the receiving device are assembled. Another system and method are also disclosed.

Abstract: A deployment system for a spacecraft may include a fitting for coupling a deployable device to the spacecraft, and a moment bearing shear ball assembly. The moment bearing shear ball assembly may include a shear ball engaged within the fitting, and a moment collar mounted onto the shear ball. The moment collar may have a planar surface engaged with a planar surface of the fitting. A separation interface may be defined between at least one of (1) mating surfaces of the fitting and the shear ball and (2) mating surfaces of the fitting and the moment collar. Engagement of the shear ball within the fitting constrains shear forces in at least two axes and axial forces in at least a third axis. Engagement of the moment collar with the shear ball and the fitting constrains overturning moments of the shear ball about at least two axes, and axial forces in at least a third axis.

Abstract: A system for separating composites of a space launch vehicle, comprising non-pyrotechnic separating modules distributed between the composites to be separated and a device for activating the separation modules, which can generate the simultaneous activation of all of the separating modules. The activation device consists of a source of compressed gas, the outlet of which is connected to each separation module.

Abstract: The present invention is directed to a device for dispensing pyrophoric decoy particulates where the device is comprised of at least one payload vessel having a structural wall that forms a cavity for housing a plurality of pyrophoric particles. The structural wall has at least one opening to facilitate dispersal of the pyrophoric particles. The payload vessels are inserted inside a tubular sleeve and hermetically sealed inside the sleeve. Within the sleeve the at least one payload vessel is also in direct contact with an expulsion assembly that upon activation pushes the payload vessels and its pyrophoric contents out of the sleeve to react with the air.

Abstract: A novel dearmer enables EOD technicians to propel dearmer projectiles using conventional electric .50 caliber blank cartridges or conventional non-electric 12 gauge blank cartridges. The dearmer projectiles may render energetic threats safe without requiring an opposing force to offset the recoil. The conventional blank cartridge functions as a rocket motor that supplies gas to a converging/diverging nozzle. Alternatively, liquid is loaded into the dearmer (creating a liquid rocket effect) and the EOD projectile is propelled toward a target from the end of the dearmer opposite the liquid.

Abstract: An active tie rod for retaining and releasing appendages without shock is provided. The device comprises: a fixed base, a tie rod extending along an axis between two ends, a mechanism fastened to the base and temporarily retaining a first end of the tie rod, operating the mechanism to release the tie rod from the base, an end piece fastened to a second end of the tie rod, at least one appendage temporarily retained between the base and the end piece, a component disposed between the mechanism and the end piece, and an actuator of the component to modify a characteristic dimension of the component along the axis between two values, the component producing a tension in the tie rod for the first of the two values and the tension in the tie rod being reduced for a second of the two values.

Abstract: A novel dearmer enables EOD technicians to propel dearmer projectiles using conventional electric .50 caliber blank cartridges or conventional non-electric 12 gauge blank cartridges. The dearmer projectiles may render energetic threats safe without requiring an opposing force to offset the recoil. The conventional blank cartridge functions as a rocket motor that supplies gas to a converging/diverging nozzle. Alternatively, liquid is loaded into the dearmer (creating a liquid rocket effect) and the EOD projectile is propelled toward a target from the end of the dearmer opposite the liquid.

Abstract: The disclosure concerns a joint (1) for releasably connecting a first space craft element (2) to a second space craft element (3) comprising a first flange (4) on the first space craft element (2) and a second flange (5) on the second space craft element (3). The joint (1) comprises first shoe portions (6) and second shoe portions (13) formed as sectors of a solid of revolution, keeping the flanges (4, 5) together in a longitudinal direction, The shoe portions are positioned next to each other in a circumferential direction the reference to a longitudinal direction of the space crafts. The first shoe portions being arranged to, at a prevailing Coulomb friction, not allow self-locking and the second show portions are arranged to allow self-locking.

Abstract: A non-lethal naval vessel interdiction weapon is provided. The non-lethal naval vessel interdiction weapon includes a hydrodynamic hull, guidance and delivery systems housed in the hydrodynamic hull with the delivery system being controllable by the guidance system to drive a naval vessel impeding payload toward a target and a deployment system. The deployment system is configured to prepare the hydrodynamic hull for payload deployment and to deploy the naval vessel impeding payload toward the target following hull preparation.

Abstract: An apparatus for launching a payload includes a primary barrel, a primary projectile including a secondary barrel, and a secondary projectile including the payload. Prior to firing the apparatus to launch the payload, the primary projectile is contained within the primary barrel, and the secondary projectile is contained within the secondary barrel. Ignition, detonation, or expansion of a primary propellant within the primary barrel launches the primary projectile from the primary barrel. Ignition, detonation, or expansion of a secondary propellant within the secondary barrel launches the secondary projectile from the secondary barrel. The secondary projectile can further include a volume of a secondary explosive material; detonation of the secondary explosive material propels at least a portion of the payload away from a remainder of the secondary projectile. The payload can include cremation remains, DNA, or text, images, or other information.

Abstract: A missile or other flight vehicle has a stage separation mechanism for separating a downstream stage from an upstream portion of the missile. The mechanism includes one or more holes in fluid communication with a cavity between the upstream and downstream portions of the missile. The holes are located downstream of one or more shocks produced by one or more local variations in the outer surface shape of the missile. The one or more local variations in outer surface shapes produce the one or more shocks as the missile is flown at supersonic speeds. These shock(s) produce downstream pressure rises, and these pressure increases are communicated to the cavity by the hole(s). The increased pressure in the cavity provides a mechanism for separating the downstream stage from the upstream portion of the missile, after release of a mechanical coupling between the upstream portion and downstream stage.

Abstract: A separation system for separable elements of spacecraft and launchers includes an upper ring, a lower ring and a band with an inner channel which houses slidable clamps, which are applied against the upper ring and the lower ring that form the connection interface between the two separable elements. A device joins/separates the ends of the band, both the upper ring and the lower ring including an outer protruding element with a wedged section to be lodged in the clamps. The upper ring also has an inner protruding element with a wedged section that matches a channel shaped section in the lower ring, the lower ring also has an outer portion including the outer protruding element with a wedged section and the channel shaped section, the outer portion protruding from a main part of the lower ring and being spaced from it creating a groove.

Abstract: A missile or other flight vehicle has a stage separation mechanism for separating a downstream stage from an upstream portion of the missile. The mechanism includes one or more holes in fluid communication with a cavity between the upstream and downstream portions of the missile. The holes are located downstream of one or more shocks produced by one or more local variations in the outer surface shape of the missile. The one or more local variations in outer surface shapes produce the one or more shocks as the missile is flown at supersonic speeds. These shock(s) produce downstream pressure rises, and these pressure increases are communicated to the cavity by the hole(s). The increased pressure in the cavity provides a mechanism for separating the downstream stage from the upstream portion of the missile, after release of a mechanical coupling between the upstream portion and downstream stage.

Abstract: A thrust control valve equipped with: a valve element, in which a gas injection passage, through which an operating gas is injected, is formed, with a valve-seating surface being formed in the gas injection passage; and a valve stem, which is provided in the interior of the gas injection passage and has a seated surface that makes contact with the valve-seating surface. A guide surface which makes contact with the inner circumferential surface of the gas injection passage of the valve element is formed on the outer circumferential surface of the valve stem. The guide surface is formed downstream from the seated surface in the direction of flow of the operating gas. A V-groove through which the operating gas flows is formed at the tip of the valve stem, downstream from the seated surface in which the guide surface is formed.

Abstract: A drag reduction system, more specifically a forward mounted drag reduction system for use on an extended range artillery shell, includes a forward end comprising a fuse, an aft located base unit and located therebetween a shell body defining a cavity which comprises a payload, a forwardly located gas generator capable of generating a gas flow, and an ignition device to ignite the gas generator after the shell is launched.

Abstract: A cam-lock fastening system is designed to accommodate a tolerance stackup to fasten a pair of rigid structures. A spring allows some longitudinal motion of the pin that would not be accommodated by the rigid structures or metal cam-lock and pin. The spring-loaded pin is also suitably designed to produce a preloaded structural joint that is between specified minimum and maximum loads for any tolerance stackup that is within specification. The fastening of the structures requires no manual adjustment of the pin, and facilitates blind connection of a high-fidelity electrical connector. Further, the described cam-lock fastening system is designed for high performance applications requiring preload forces in the thousands of pounds per square inch.

Abstract: Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

Abstract: A despin device includes a central base installed in an outer rotational ring. The outer rotational ring includes a plurality of through-holes extending from an inner wall face thereof through an outer wall face thereof. Masses are symmetrically installed in ball grooves of the central base and the through-holes of the outer rotational ring. The masses are connected by a connecting line extending through a line cutter and tensioned by a tensioning device. Cables are wrapped around an outer periphery of the central base. Each cable includes an end attached to one of the masses. A plurality of release-hitch devices is provided. Each release-hitch device includes a hitch member fixed to the central base and a disengagement member releasably engaged with the hitch member and fixed to the other end of one of the cables.

Abstract: A low collateral damage, kinetic energy penetrator has multiple segments that are mechanically locked together by centrifugal force generated by penetrator spin. When the penetrator spin decreases below a minimum value, the segments separate and fall to the ground with non-lethal kinetic energy.

Abstract: This invention is a segmented missile that uses multiple circular linear shaped charge warheads deployed in tandem. Each warhead is capable of full-caliber holes and 5 to 15 charge diameters of penetration for each warhead, depending on the target material. The full-caliber hole capability allows for the warheads to travel down the hole made by the previous warhead. Each warhead is sequenced in its time of arrival at the bottom of the hole, allowing for a cumulative effect.

Abstract: A countermeasure system for intercepting an incoming weapon, such as a rocket propelled grenade (RPG), includes a launcher that is used to launch a countermeasure. A door covers and protects the countermeasure in an opening in the launcher prior to the launch of the countermeasure. The door is separated (pushed away) from launcher when the countermeasure is launched, for example being pushed out into a flight path of the countermeasure by the countermeasure itself. The door may be attached to the countermeasure, or may be a separate piece that flies away from both the countermeasure and the launcher after launch of the countermeasure. Pitch over motors or other orientation adjustment devices may be used to change the orientation of the countermeasure after launch. The countermeasure may be used to defeat the incoming weapon in any of a variety ways.

Abstract: A rocket is provided and includes booster stages at a rear of the nose cone, the booster stages being configured for propelling the nose cone in a propulsion direction and a divert control system housed entirely in the nose cone for controlling an orientation of the propulsion direction.

Abstract: A vessel, such as a rocket motor tube, comprised of an insert, and a joint that allows the insert to decouple from the vessel to relieve pressure when subjected to excessive temperatures and/or a predetermined temperature or temperature range.

Abstract: A propulsion system and method are described configured to exert a force upon a vehicle. The system includes a concentrated mass which may be discharged from the vehicle by a propellant typically via an ejection tube. The system is optimized so that the discharged concentrated-mass imparts a large impulse upon the vehicle. The system and method may be used to alter the momentum of vehicles for propulsion, attitude correction, vehicle separation and the like.

Abstract: A staged rocket apparatus includes first and second stages connected by a releasable connector. A plurality of pressurized gas struts are connected between the first and second stages and provide a separating force urging the first and second stages apart. The gas struts are held in a telescopingly collapsed first position by the releasable connector. The separating force is maintained at a minimum value so long as the releasable connector holds the struts in their first position. When the releasable connector is disconnected the separating force increases due to gas flow through a metering passage having a progressively increasing flow area from a high pressure chamber to a low pressure chamber.

Abstract: A component separation system for separating a load from an external structure according to various aspects of the present invention comprises a sleeve slidingly engaged with the external structure. The sleeve includes an opening and an interior. A locking mechanism, such as a ball or latch, is movably disposed through the sleeve opening between a locked position engaging the external structure and an unlocked position not engaging the external structure. A mover slidingly disposed within the hollow interior of the sleeve controls the movement of the locking mechanism through the opening. Energy excess beyond that required for unlocking the mechanism may provide a thrust to forcibly eject the load from the external structure.

Abstract: A scalable, inert munition data recorder cartridge. This inert cartridge allows users to record data from within a weapon system feed chute, breach, and extractor port. This cartridge is adaptable to any weapon system, packaging unit, environmental chamber, or other ammunition holding and storage device. Although the cartridge is designed to interface with a weapon and ammunition packaging based on its shape, it still functions as designed regardless of its location and application. This would allow the cartridge to be placed anywhere an actual live cartridge of ammunition could be placed.

Abstract: The presently disclosed device provides a method and means for ensuring that containers of all types and sizes are vented or purged to atmospheric or environmental conditions upon the interior or exterior of the container reaching a critical temperature pressure, or humidity. Specifically, the presently disclosed invention integrates shape memory polymer (SMP) based, thermally activated fasteners into the venting systems. The result is a venting system that increases munitions safety without compromising the venting effectiveness, structural integrity, or the required bullet/fragment impact resistance requirements of the system.

Abstract: The invention provides rupturing devices for mitigating the explosive reaction of a casing (121), hollow tubular body or container, particularly a munition, when it is subject to an external thermal hazard threat. The devices are based on the use of shape memory alloys. The device comprises an element of shape memory alloy (123) which is joined together by a connector (122) to form an annulus, which may be located on an exterior surface of a munitions casing (121) or launch such that upon heating through its transition temperature range will cause the annulus to contract radially inwardly, thereby rupturing the munition (121), allowing any build up of pressure to be released quickly. Advantageously, the connector (122) is. reversible such that the device will be capable of being retro-fitted or removed during normal servicing of the munition (121).

Abstract: The present disclosure generally relates a high strength, low weight, and low shock rocket body separating joint for the purpose of joining rocket bodies, and method of assembly thereof. The solution combines a radax joint, joined by fasteners, with a flattened bladder and inflation system coupled thereto. Upon activation of the inflation system, the bladder is pressurized and exerts a separating force between the members of the radax joint, overcoming the load carrying capability of the fasteners and breaking apart the radax joint.

Abstract: A vessel, such as a rocket motor tube, comprised of an insert, and a joint that allows the insert to decouple from the vessel to relieve pressure when subjected to excessive temperatures and/or a predetermined temperature or temperature range.

Abstract: Embodiments of separation apparatuses are generally described herein. Other embodiments may be described and claimed. In an embodiment, a separation apparatus is provided that is configured to be disposed between a first component and a second component associated with an aerospace vehicle. The separation apparatus comprises a sealed cavity filled with gas, and the separation apparatus is configured to expand based on a decrease in atmospheric pressure. This expansion is configured to separate the first component from the second component.

Abstract: A missile head has a shroud which forms its tip and which can be detached in its totality during flight from the fuselage of the missile. The missile head further has a rear part, which is connected to the fuselage, and a front nose, which can be disconnected from the rear part and forms the tip. A separating device separates the rear part from the fuselage and the nose from the rear part during flight. A physically small shroud can be achieved, and damage to the fuselage of the missile by separation of the shroud can be prevented, if the nose is split into at least two parts and the separating device is prepared to split the nose into these two parts during flight.

Abstract: A missile, a method of making a missile, and a clamp for making a missile, comprising providing two sections of a missile and joining the two sections with a clamp comprising a plurality of pieces for engaging a circumference of the two sections, each of the pieces comprising at least two grooves extending substantially the length of the piece, and at least two Nitinol rings placed one in each of the at least two grooves.

Abstract: Projectiles that include a propulsion system and a launch motor which are located on opposing sides of a payload and a method of directing a projectile toward a target are generally described herein. Placing the propulsion system and the launch motor on opposing sides of the payload may provide many potential advantages when designing the projectile. These design advantages may make it easier to create a projectile that includes more propellant and/or payload while still permitting the projectile to be stored within existing containers having a fixed size.

Abstract: The present disclosure generally relates a high strength, low weight, and low shock rocket body separating joint for the purpose of joining rocket bodies, and method of assembly thereof The solution combines a radax joint, joined by fasteners, with a flattened bladder and inflation system coupled thereto. Upon activation of the inflation system, the bladder is pressurized and exerts a separating force between the members of the radax joint, overcoming the load carrying capability of the fasteners and breaking apart the radax joint.

Abstract: A self-propelled munition having a munition rear body of circular cylindrical shape of diameter D1, along axis ZZ?. A propulsion system of the munition has a tubular casing of circular cross section, has an axis of revolution coincident with axis ZZ?, has an internal surface of diameter D1 able to slide over said munition rear body, and contains a pyrotechnic propulsion chamber. The munition includes a mechanical connection between the propulsion system and the munition using shear pins evenly distributed about axis ZZ?, a hardened mechanical connection having a ring groove around the munition rear body in a plane perpendicular to axis ZZ?, another ring groove on the internal surface of the propulsion system casing, a retaining ring inserted in the ring groove configured to expand into the other ring groove from diameter D1 to a diameter greater than diameter D1 to secure the propulsion system to the munition.

Abstract: A solid-fuel pellet thrust and control actuation system (PT-CAS) provides command authority for maneuvering flight vehicles over subsonic and supersonic speeds and within the atmosphere and exo-atmosphere. The PT-CAS includes a chamber or solid-fuel pellets that are ignited to expel gas through a throat. The expelled gas is directed at supersonic vehicle speeds in atmosphere to a cavity between an aero control surface and the airframe to pressurize the cavity and deploy the surface or at subsonic speeds in atmosphere or any speed in exo-atmosphere allowed to flow out a through-hole in the surface where the throat and through-hole provide a virtual converging/diverging nozzle to produce a supersonic divert thrust. A pellet and control actuation system (P-CAS) without the through-hole provides command authority at supersonic speeds in atmosphere.

Abstract: Methods and apparatus for a multiple part missile according to various aspects of the present invention may operate in conjunction with a first missile part having a first groove formed in a surface of the first missile part and a second missile part having a second groove. A snap ring may be configured to engage the first groove and the second groove.

Abstract: A separation device for separating parts along a seam includes a frangible structure and a pressure tube assembly within the frangible structure. The pressure tube assembly includes a pressure tube which contains an explosive detonation assembly/cord that can be initiated to expand the pressure tube, and break the frangible structure with a shock force. The pressure tube assembly also includes a explosive manifold that is recessed in the frangible structure, not protruding from an outer surface of the frangible structure. The explosive manifold receives the ends of the pressure tube, and includes a detonator for detonating the explosive detonation assembly/cord. The explosive manifold has circular-cross-section fittings for accepting a circular ends of the pressure tube. By not having any part of the pressure tube assembly protrude from the frangible structure, improved performance may be achieved. Having circular fittings also improves the seal between the pressure tube and the explosive manifold.

Abstract: A staged rocket apparatus includes first and second stages connected by a releasable connector. A plurality of pressurized gas struts are connected between the first and second stages and provide a separating force urging the first and second stages apart. The gas struts are held in a telescopingly collapsed first position by the releasable connector. The separating force is maintained at a minimum value so long as the releasable connector holds the struts in their first position. When the releasable connector is disconnected the separating force increases due to gas flow through a metering passage having a progressively increasing flow area from a high pressure chamber to a low pressure chamber.

Abstract: A munitions casing including an annulus of a shape memory alloy disposed around said casing where the shape memory alloy has been subjected to a combination of mechanical and thermal treatments so as to impart a memory, and a cutter located between the annulus and the casing wherein heating of the shape memory alloy to a predetermined temperature causes said annulus to contract radially inwardly and rupture the said munitions casing.

Abstract: A missile includes several subvehicles that are initially mechanically coupled to a missile main body, and a separation system for separating the subvehicles from the missile main body. The separation system has a single triggering mechanism to simultaneously provide energy to separate all of the subvehicles. This advantageously provides only a single shock to the system by actuating the system to separate the subvehicles. By limiting the shocks to the single shock of actuating the energy system and the shocks of the mechanical disengagement of the individual subvehicles, the disengagement system has improved performance. The subvehicles may be separated from the main body in radial directions substantially perpendicular to a central axis of the main body. This may provide for smoother disengagement, with less tipping, and may provide for greater, more uniform spacing between the disengaged subvehicles.

Abstract: Disclosed is a separation device of an ejector motor for a portable missile, capable of being separated from a missile without any additional separation devices after ejecting the missile. An ejection rocket motor and a separation device are integrally formed. Ejection is performed by a thrust generated while the ejection rocket motor is combusted, and separation is performed by cutting off shearing bolts with using a force generated from a separation cylinder when the combustion of the ejection rocket motor has been completed. This operation and configuration may minimize a weight and a space occupied by a general ejection and separation device in a missile system.

Abstract: Disclosed is a device for separating a propulsion system from a missile, the device including a locking unit configured to fix a propulsion system to a missile, a string disposed to cross a rear portion of the propulsion system to be broken by heat of the propulsion system, and an unlocking unit configured to unlock the missile by the broken string, whereby the number of additional components of an unlocking system can be reduced as many as possible so as to simplify the configuration of the apparatus, resulting in guaranteeing an enhanced performance of the missile, an easy assembly of the missile, and a reduction of a fabricating cost.

Abstract: A missile head has a shroud which forms its tip and which can be detached in its totality during flight from the fuselage of the missile. The missile head further has a rear part, which is connected to the fuselage, and a front nose, which can be disconnected from the rear part and forms the tip. A separating device separates the rear part from the fuselage and the nose from the rear part during flight. A physically small shroud can be achieved, and damage to the fuselage of the missile by separation of the shroud can be prevented, if the nose is split into at least two parts and the separating device is prepared to split the nose into these two parts during flight.

Abstract: A multi-stage vehicle separation system and method that facilitates an active separation on the booster by igniting a small quantity of propellant in the dead volume between the second stage rocket motor nozzle and the booster dome. In the most general embodiment, the invention includes a nozzle; a first fuel propellant disposed within the nozzle; a thermal barrier separating the first and second fuel propellant, an environmental seal protecting the second fuel propellant and an arrangement for activating the first fuel propellant. The nozzle is disposed in an upper stage of a two-stage vehicle. An arrangement such as a V-Band clamp is included for retaining the lower stage of the two-stage vehicle. Electronic commands release the lower stage and activate the first propellant in a timely manner to effectively separate the lower stage from the upper stage. The embedded propellant is activated with an arm fire device.

Abstract: A launcher and satellite connection-separation apparatus for launching and satellite vehicles has a band-clamp assembly of a band with an inner channel in which clamps are located in a sliding manner for application to rings interfacing between the vehicles, and a union-separation device on ends of the band for radially tightening the band and controlling opening of the band in first and second phases such that the ends of the band shift in contact with the rings for dissipating by friction elastic energy corresponding to the tightening of the band and separate from the rings until reaching a parking position.

Abstract: The disclosed system, device and method for providing a multi-mode munition generally includes a modular projectile assembly having an aft module suitably configured for mechanical and electrical engagement with a forward module. The aft module generally provides a common assembly for engagement with a variety of forward modules as well as engagement with cartridge casings of various calibers. Disclosed features and specifications may be suitably controlled, adapted or otherwise optionally modified to improve optimization of artillery projectiles for a specific role. Exemplary embodiments of the present invention generally provide munition cartridges that may be augmented in the field with the utilization of specialized forward modules.

Abstract: A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.