Abstract: An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.

Abstract: A rotary-wing aircraft includes a fuselage, and an external device. The fuselage is provided with a rotary wing. The external device is mounted on the outside of the fuselage. The external device includes a mounting device, a mass variation device, and a damper. The mounting device is fixed to the fuselage and disposed so as to project in a lateral direction of the fuselage. The mass variation device is mounted on the mounting device and has mass that varies as the mass variation device is used. The damper couples the fuselage to the mounting device and supports the mounting device. The damper includes a stiffness variable mechanism configured to change stiffness of the damper in response to variation in the mass of the mass variation device.

Abstract: A canister for storing and launching a self-propelled projectile comprises: a) an inner layer comprising an aluminum foil; b) a top layer consisting of an injected thermoplastic polymer; and c) optionally, a primer and/or a topcoat.

Abstract: A protection device for a rocket launcher includes a cover with a triplet of openings arranged in angularly equidistant positions so as to allow a passage of the rockets housed in two alternating triplets of rocket housings. An actuation means is designed to rotate the cover between a first position in which the triplet of openings is aligned with the first triplet of openings and a second position in which the triplet of openings is aligned with the second triplet of housings.

Abstract: A launch system and method for orbital or suborbital air-launch of a payload involving releasably coupling a launch vehicle with a towed aircraft via an articulatable carriage to form an air-launch assembly, towing the air-launch assembly via a tow aircraft and interconnected tow cable to a first altitude, releasing the air-launch assembly from tow at or above the first altitude, activating the towed aircraft propulsion system and initiating a pull-up and climb maneuver of the towed aircraft to a second altitude, articulating the articulatable carriage to shift the air-launch assembly from a stowed position to a deployed position with the launch vehicle spaced from the towed aircraft, releasing the launch vehicle from the articulatable carriage and thus from the towed aircraft, and activating the launch vehicle propulsion system for further altitude gain or to meet specific mission requirements.

Abstract: Deployable navigation beacons can be deployed from a vehicle, such as an unmanned aerial vehicle (UAV), in an event of a loss of position or orientation of the vehicle. After deployment of the navigation beacons, the vehicle may detect locations of the navigation beacon, which may define a surface that may include surface features. The vehicle may then perform control operations based on the resolved locations. For example, UAV may maneuver to land proximate to the navigation beacons after resolving locations of the navigation beacons as a continuous surface. The navigation beacons may output a visual signal (e.g., a light), a auditory signal (e.g., a sound), and/or a radio signal. In some embodiments, each navigation beacon may include a different or unique signal.

Abstract: An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.

Abstract: A multi-mission munition adapter for an aircraft may be configured to attach to a hardpoint and hold a plurality of munitions, such as missiles and bombs. A top of the multi-mission munition adapter may have suspension lugs configured to attach to a hardpoint on an aircraft. Sides of the multi-mission munition adapter may have one or more launcher attachment fittings configured to attach missile launchers. A bottom of the multi-mission munition adapter may have one or more munitions ejector hangers configured to attach air-to-ground munitions ejectors. The adapter may comprise an electrical system that permits an aircraft to communicate with and/or power all functions of the bomb rack, missile launchers, and the weapons employed.

Abstract: Systems, apparatus, and method for manufacturing are disclosed. In an aspect, the apparatus may be a cold-spray nozzle. The cold-spray nozzle may include a variable diameter convergent part. The cold-spray nozzle may also include a variable diameter divergent part. The variable diameter divergent part may form a diffuser. Additionally, The cold-spray nozzle may include a ring portion. The ring portion may couple the variable diameter convergent part and the variable diameter divergent part. Additionally, the ring portion may control the opening to the diffuser.

Abstract: Systems, devices, and methods including a launch control box; a multi-pack launcher (MPL) box; and a cable connecting the launch control box and the MPL box, where the cable comprises: an outer jacket, a shielded braid, a first wire, a second wire, a third wire, and a fourth wire, where the first wire and the second wire are shielded by the shielded braid, where the third wire and the fourth wire are outside of the shielded braid, and where the third wire and the fourth wire act as an antenna.

Abstract: A weapon launching tube structure, and in particular a torpedo launching tube structure, includes a tube inside which weapon guiding slides are mounted at regular intervals around the weapon. The slides are made from a single slide blank obtained by an extrusion process.

Abstract: A launcher for unmanned aerial vehicles (UAV), the launcher having a foldable UAV stowed within said launcher, the launcher includes, a launch tube configured as a UAV launcher and a UAV carrying case. The launcher further includes a pneumatic booster connected to said UAV for accelerating said UAV during launching phase. The launcher further includes a separation mechanism operated to permits separation of the booster from the UAV when the UAV leaves the launcher tube and to transfer the kinetic energy that is created from the pneumatic booster to the UAV in the launching phase. The UAV is propelled off of the launch tube by the booster that transmits thrust in the launch tube to the space below said booster. The UAV which is connected to the booster by the separation mechanism is pushed out of the launcher tube body and leaves the launch tube, the booster is separated from the UAV by the separation mechanism and the UAV is automatically deployed.

Abstract: A containment vessel for stowing a high energy density device therein includes a housing, a plurality of discs, and a separable collar. The housing includes a base, a sidewall enclosure extending upwardly from the base, the sidewall enclosure defining a housing cavity and an opening at a top end thereof, and a flange extending circumferentially outwardly from the sidewall enclosure. The separable collar has first, second, and third grooves on an inner circumference of the separable collar. The first groove is configured to receive the flange of the housing. The second and third grooves are configured to receive first and second of the plurality of discs.

Abstract: A ball tossing apparatus includes a support frame and a plurality of launch devices fixed to the support frame and arranged in a two-dimensional array. The launch devices include cylinders having a spring fixed therein, with a ball carrier fixed to the spring. The balls are retained in a loaded position (springs compressed) and then upon activation of the launch devices are launched vertically into the air to the sports player. In another embodiment, the launch devices include a rotating lever which is acted on by a biasing member to launch the ball vertically from the cylinder. A method for launching the balls includes the steps of loading the balls into a two dimensional array, and then launching the balls according to a launch sequence. An electronic control system for use with the ball tossing apparatus includes a launch module for launching the loaded balls in the plurality of launch devices according to a launch sequence.

Abstract: A gas gun launcher having a pump tube and a launch tube with a first end of the launch tube slidably inserted into a second end of the pump tube. A sliding seal is employed to retain the gas within the launch tube and the pump tube A launch tube alignment system is preferably automatic, again to enhance the accuracy of launches. And an embodiment of the gas gun launcher suitable for use in water such as an ocean or large lake preferably utilizes a neutrally buoyant launch tube and a neutrally buoyant pump tube. And a fast-closing muffler at the second end of the launch tube conserves the light gas utilized for launching a vehicle.

Abstract: The invention covers a missile canister (10) for accommodating a missile (20) along a longitudinal axis (L) of the canister. The canister comprises a plurality of generally planar longitudinal wall portions (14) connected together to form a tubular vessel having a polygonal cross-section. The interconnecting portions (16) between wall sections (14) are generally flexible so that when a missile (20) is launched the bending moment at the interconnecting portions (16) generated by the increase of pressure in the vessel is substantially less than the bending moment (10) generated at the wall portions (14). The interconnecting portions (16) allow relative angular deflection between adjacent wall portions (14) at respective interconnecting portions (16) when said missile (20) is launched.

Abstract: Recoil forces of a launched missile and the moment force imposed on the launch platform can be reduced by use of a recoil abatement element in communication with a launch tube. The recoil abatement element includes at least one nozzle configured to receive therethrough exhaust gasses from a missile when launched. The nozzle can be canted or otherwise configured to direct the exhaust gasses in a desired direction to thereby offset moment force imposed on the platform by the exhaust gasses.

Abstract: A float support member that comprises a base for mounting to an object, primary linkages rotatably coupled by a primary pin defining a primary movable pin point that moves both in a lateral direction and a transverse direction, and secondary linkages rotatably coupled to said primary linkages, respectively, by first and second secondary pins, respectively. The first and second secondary pins define first and second secondary movable pin points, respectively, that each move both in a lateral direction and a transverse direction. The first and second secondary linkages being rotatably coupled to the base by first and second stationary pins, respectively, defining first and second stationary pin points, respectively. The position of the primary movable pin point in both the lateral and transverse directions depends on the position of both of the first and second secondary moveable pin points in both the lateral and transverse directions and vice versa.

Abstract: Recoil forces of a launched missile and the moment force imposed on the launch platform can be reduced by use of a recoil abatement element in communication with a launch tube. The recoil abatement element includes at least one nozzle configured to receive therethrough exhaust gasses from a missile when launched. The nozzle can be canted or otherwise configured to direct the exhaust gasses in a desired direction to thereby offset moment force imposed on the platform by the exhaust gasses.

Abstract: Systems and methods for launching munitions are provided. In some embodiments, the system may include a launcher coupled to a vehicle and configured to retain a munition during transport by a vehicle and configured to route electrical signals from the vehicle to the munition. The system may also include a flexible, peel-away connector coupled to the launcher, the peel-away connector comprising an adhesive for coupling to at least a portion of the munition. The flexible, peel-away connector may be configured to route electrical signals from the launcher to the munition during transport and detach from the munition as the munition exits from the launcher during a launch.

Abstract: A waterborne munitions system is disclosed. The system includes a submersible munitions platform and a remote control module. The munitions platform has a plurality of canistered munitions, either waterborne, airborne, or both, which can be remotely launched via the remote control module.

Abstract: A system is provided for directing a flow of gas, including a launching mechanism, a plenum, a layer of meltable material, and an open-ended uptake component. The launching mechanism is adapted to expel rocket exhaust gas. The plenum includes an upper portion having at least one fire resistant breachable plug. The upper portion is adjacent to the launching mechanism. The layer of meltable material is disposed on the upper portion. The heat generated by the gas melts the layer of meltable material. The open-ended uptake component operatively connects to the plenum. The plug moves onto a lower portion of the plenum due to force generated by the gas onto the plug, and the gas flows through the plenum and the uptake component to vent said gas in a controlled manner.

Abstract: A system and method for providing a munitions launching system with dynamic shock isolation in which a spring plate skirt having an integral spring arrangement is provided between a munitions frame and a munitions extension, the spring plate skirt defining an opening that provides for the uninterrupted flow of expelled rocket gases, as well as underside access to the munitions frame.

Abstract: A system and method for rapid aiming and firing of weapons and defensive countermeasures against rocket-propelled grenades or other ballistic devices suitable for use on aircraft, ground vehicles, and ships.

Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

Abstract: A system and method for launching non-vertical launch munitions with a non-vertical launch trajectory from a launcher that is operationally coupled to a vertical launching system (VLS). The inventors of the present invention recognized that munitions that are unsuitable for vertical launches were unavailable for use with vertical launching systems, thus foreclosing important defense, attack, and cost-savings opportunities for VLS-equipped platforms. A VLS could be substantially more versatile if it accommodated munitions such as torpedoes, counter-measures, direct-fire munitions, point-and-shoot munitions, and a variety of other missiles and equipment. The launcher according to the present invention is also stowable in an upward orientation within a cell of the host vertical launching system.

Abstract: An apparatus for adapting a rocket-assisted artillery projectile of a first caliber for firing from a smooth bore tube of a second caliber may include an adapter for connecting to an aft end of the rocket-assisted artillery projectile. The adapter may include a main channel for receiving rocket exhaust, a plurality of sub-channels that lead from the main channel to an exterior of the adapter, and an ignition channel that leads from the main channel to an ignition delay disposed in the adapter. A tail boom may be fixed to an aft end of the adapter. The tail boom may include an opening in a fore end that communicates with the ignition delay in the adapter. Lifting surfaces, such as fins, may be attached to the tail boom.

Abstract: Systems and methods for launching munitions are provided. In some embodiments, a launcher configured to retain a munition during transport by a vehicle may comprise a first housing, circuitry, and a second housing. The first housing may define a tube configured to hold a munition for transportation. The circuitry may provide electrical communication with a munition present within the tube. The second housing may define a tube corresponding to the tube defined by the first housing. The second housing may be configured to mount to the first housing so that the tubes defined by the first housing and the second housing combine to house and launch a munition.

Abstract: The invention relates to an improved deformable downstream disc (56; 156; 256) to be fitted on the bottom of a container (15) for a missile (16) and including a stack of elastic blades (63) clamped between at least an upstream and a downstream thermal protection membrane and sealing membrane (70, 71, 72, 73), and maintained between an upstream bearing frame (61) and a downstream bearing frame (64), characterised in that the downstream bearing frame includes an inner edge (80) having an extension so as to provide the disc with an abutment means defining a position of maximum deformation of the elastic blades.

Abstract: Disclosed are a wing assembly including a wing movably accommodated in a launch tube, and a buffer unit detachably mounted to the wing to come in contact with the launch tube and configured to be separated from the wing after the wing comes out of an inner space of the launch tube, and an apparatus for launching a flying object having the same.

Abstract: A projectile propulsion system includes a launch tube, multiphase material, and a pressure barrier member. The launch tube has an interior cavity, the multiphase material disposed therein. The launch tube also has an opening to receive the multiphase material. The pressure barrier member seals the opening while the multiphase material is disposed in the interior cavity of the launch tube so as to allow the launch tube to be pressurized. When the pressure barrier member is broken, a shock wave allows the contents of the interior cavity, such as a projectile, to be expelled from the tube with a high velocity and force.

Abstract: A self-adjusting bumper comprising slidably adjustable upper and lower tapered nylon wedges for eliminating rattle space between objects and their containers. A tapered lower wedge comprises a dovetail guide rail and opposing guide pin rails; a tapered upper wedge comprises a corresponding dovetail guide path and opposing slots shaped for insertion and slidable adjustment of the guide pin rails. Opposing helical extension springs secured to the sides of the upper and lower wedges minimize friction forces between the wedges as they slidably move relative to one another. External surfaces of the wedges may be contoured to accommodate the shape of the object and/or its container.

Abstract: A device is provided to connect the ammunition and the magazine to each other not only in terms of design, but also in terms of function. The magazine and ammunition are combined to form sub-modules, wherein a plurality of sub-modules would then be comparable to the quantity of conventional ammunition in the launcher tube. The sub-modules are then assembled and locked. The individual sub-module contains, inter alia, rifling, by means of which, during firing, the ammunition/submunition is caused to rotate and is thereby stabilized.

Abstract: The illustrative embodiment of the present invention is a launch system that includes a missile canister cover that, in use, is attached to a missile canister. The cover is capable of being blown off of the canister before there is any contact between the nose of the missile and the cover and is further capable of withstanding a higher ambient pressure than internal canister pressure. These capabilities are achieved based on an attention to material mechanics and the prevailing geometry of the system.

Abstract: Embodiments of a canisterized interceptor and method to prevent the launch of a canisterized interceptor that may have been penetrated by small arms fire are generally described herein. In some embodiments, the canisterized interceptor includes a composite canister for housing an interceptor. The canister includes an embedded winding to provide a conductive path and comprises a conductor arranged within composite material of the canister. A maximum spacing may be provided between windings of the conductor and penetration of the canister may be indicated by an open or short circuit in the conductive path.

Abstract: Embodiments of a translating adjacent-blast shield and method of protecting external slots of a missile from a high-temperature, high-pressure gas plume of a missile that is launched from an adjacent or nearby launcher tube of a launcher are disclosed herein. The translating adjacent-blast shield may be provided circumferentially around each of the missiles in a launcher and may cover at least portions of external slots of the missiles. The translating adjacent-blast shield may translate along the missile during launch to expose the external slots and may remain on the missile after launch.

Abstract: A projectile propulsion system includes a launch tube, multiphase material, and a membrane. The launch tube has an interior cavity, the multiphase material disposed therein. The launch tube also has an opening to receive the multiphase material. The membrane seals the opening while the multiphase material is disposed in the interior cavity of the launch tube so as to allow the launch tube to be pressurized. When the membrane is broken, a supersonic wave thrusts the contents of the interior cavity, such as a projectile, outwards with a high velocity and force.

Abstract: A canard includes a first section and a second section. The first section is configured for the coupling of radial forces to a fuselage of an air vehicle, and the first section is coupled to the second section via a hinge somewhere along the radial extent of the canard. An edge of the first section near the hinge provides a load support for the air vehicle within a launch canister.

Abstract: Systems and methods for launching munitions are provided. In some embodiments, a launcher configured to retain a munition during transport by a vehicle may comprise a first housing, circuitry, and a second housing. The first housing may define a tube configured to hold a munition for transportation. The circuitry may provide electrical communication with a munition present within the tube. The second housing may define a tube corresponding to the tube defined by the first housing. The second housing may be configured to mount to the first housing so that the tubes defined by the first housing and the second housing combine to house and launch a munition.

Abstract: The invention relates to a missile container retaining structure (1a) for a missile launch device of the type comprising a plurality of cells for receiving a missile container (2) and at least one duct (3). The structure is constituted by metal plates (101, 104) which are pre-cut so as to comprise complementary elements which can be fitted one inside the other, the plates being assembled so that the complementary elements of two adjacent plates are fitted one inside the other.

Abstract: A scalable and distributable software architecture for use in conjunction with various different weapons control system and launch systems is disclosed. The architecture discards the proprietary and non-open protocols and services that characterize in favor of open source adaptive and middleware components. In the illustrative embodiment of the invention, the inventive architecture is implemented as a Launch Control Module that separates different layers of responsibility within a launch controller (e.g., LCU) and exposes its variation points.

Abstract: In a ground launcher, two or more housing-transportation-launch assemblies for respective missiles are placed one on top of the other and connected releasably and interchangeably to each other; each housing-transportation-launch assembly has a respective outer casing, which in turn has longitudinal end walls breakable from inside the casing, and a deflecting body for deflecting the exhaust gas of the engine of the missile; a guide and protection assembly being interposed between the casing and the missile to guide the missile in the set launch direction, and to protect the missile against shock or vibration.

Abstract: A countermass for use in a weapon to balance the forces arising when a launch able unit is launched from a launcher tube of the weapon. The countermass includes a first container enclosing a liquid. A countermass weapon includes a launcher tube open or openable in both ends. The launcher tube houses a launch able unit, a countermass including a first container enclosing a liquid, a pressure chamber, and a propellant charge that upon firing and combustion of the charge in cooperation with the pressure chamber and the countermass accelerates the launch able unit forwards in the tube at the same time as the countermass accelerates backwards in the tube. The first container is made of a non-rigid material. A second container is provided to cover or almost cover the first container. The second container is designed with damping characteristics.

Abstract: An inflatable restraint, and method of using the same, is used to provide support and shock isolation for missiles, torpedoes, missile canisters or the like in naval vessels. The inflatable restraint features a structural collar, at least one inflatable bladder and at least one interference member. The interference member is attached to the inside of the structural collar and the interference member is fully adjustable to ensure a snug fit during the loading of the missile, torpedo or missile canister into the structural collar. Once the missile, torpedo, missile canister or the like is properly inserted into the structural collar, the at least one inflatable bladder, which is also attached to the inside of the structural collar, is inflated to restrain the object. The pressure of the inflatable bladder may be regulated to provide variable spring constants and stiffness.

Abstract: A technique for launching a missile that avoids some of the costs and disadvantages for doing so in the prior art. In particular, the illustrative embodiment of the present invention uses an electromagnetic catapult to throw the missile clear of the launch platform—with sufficient velocity to attain aerodynamic flight—before the missile's engine is ignited.

Abstract: The present invention relates to a countermeasure system having a substantially vertical launch tube that is at least generally rotatable about a vertical reference axis that extends through and along a length of the launch tube. This rotation capability of the launch tube may be used to affect an aiming of an associated countermeasure cartridge at least generally disposed therein. One or both the launch tube and countermeasure cartridge of this countermeasure system are generally equipped with a rotation inhibitor for substantially preventing independent rotation of the countermeasure cartridge relative to the launch tube at least when the countermeasure cartridge is disposed within the launch tube. The present invention is also designed to enable the associated countermeasure cartridge to be pitched over to a predetermined pitch angle (relative to the reference axis of the launch tube) to affect a desired flight path after launch of the countermeasure cartridge.

Abstract: A lateral support device system of a canister-launched missile of the present invention is provided for eliminating the clearances between missile and the canister in 4 places by 90 degrees interval, and therefore no relative movement occurs between the missile and the canister. Therefore, the missile and the detent is free from shocks and vibrations that occurs during the handling, transportation and operation. In addition, when the missile is fired, those lateral lock become free with a little energy loss.

Abstract: A method for discharging countermeasures, a rocket launcher, and a dispenser arrangement. A space for one or more rockets in a rocket launcher is used as a carrier for a dispenser arrangement for countermeasures. The dispenser arrangement is designed with one or more cylindrical sections specially adapted to the rocket space in the rocket launcher. Equipment already adapted to aircraft can be used in supplementing the countermeasure equipment of the aircraft.

Abstract: A launch system for use as a standalone munition launcher or as a guest launcher within a main battery host launcher.