Abstract: A bonding apparatus for bonding a driving circuit to a display panel includes: a bonding stage unit on which the display panel is supported in bonding the driving circuit to the display panel; a head unit located above the bonding stage unit and with which ultrasonic waves are applied to the driving circuit to couple the driving circuit with a bonding area of the display panel supported on the bonding stage unit; and a protrusion disposed at an edge portion of the bonding stage unit, the edge portion corresponding to an end of the display panel at which the bonding area is disposed.

Abstract: A launch tube of a flying object has a tube, a plurality of rails and a plurality of guides. The tube is configured to store the flying object. The rails are fixed on an inner wall of the tube and configured to contact the flying object. The guides are on the inner wall of the tube. One of the guides is configured to contact the flying object, and evacuate from a region of movement of the flying object, when the flying object moves to leave the one of the guides.

Abstract: A color shifting heat transfer label includes a carrier and a color design layer on the carrier. The color design layer is formulated from an ink having a color shifting effect. The color design layer is configured to separate from the carrier to define a color shifting feature that is adhered to a target object upon application of heat and pressure. The color shifting feature is adhered to the target object to define a plane defined by the color shifting feature such that the color shifting feature exhibits a first color when viewed from an angle of about 90 degrees relative to the plane defined by the color shifting feature and a second color, different from the first color when viewed from an angle of about 45 degrees or less relative to the plane defined by the color shifting feature.

Abstract: A bonding apparatus for bonding a driving circuit to a display panel includes: a bonding stage unit on which the display panel is supported in bonding the driving circuit to the display panel; a head unit located above the bonding stage unit and with which ultrasonic waves are applied to the driving circuit to couple the driving circuit with a bonding area of the display panel supported on the bonding stage unit; and a protrusion disposed at an edge portion of the bonding stage unit, the edge portion corresponding to an end of the display panel at which the bonding area is disposed.

Abstract: A multifunctional pod for an aircraft has at least two separate regions. At least one first region of the pod is provided for receiving fuel. A second region of the pod includes at least one receiving device for releasably attaching at least one additional load. The additional load can be releasably attached to the receiving device via a loading opening on the side of the pod facing away from the aircraft.

Abstract: The application relates to a missile launch rail device including: a missile launch rail and a latch for attaching and releasing a missile situated on the missile launch rail, a latch pin inserted through both two latch pin holes and two rail pin holes positioned approximately halfway between the cam end and the spring end and a pin retainer securely mounted to the missile launch rail, the pin retainer including a latch pin catch which holds the latch pin in place to restrict radial pressure by the pin on inside surfaces of the two latch holes and inside surfaces of the two rail pin holes from pressure created by the missile on the latch, thus substantially preventing premature disabling of the missile launch rail and the latch by wear on the latch holes and the rail pin holes.

Abstract: Restraint release devices, systems and methods may enable actuation of a release function without using chemically energetic or thermally sensitive devices, and may employ an electromagnetic (EM) force to mechanically separate components of a fastener. A pulsed power system having a capacitive discharge circuit may be used to supply an electric current pulse to generate the EM force. The EM force can be applied to a retaining wire that surrounds and holds intact a segmented fastener. The EM force may cause the retaining wire to increase in length, thereby relaxing its hold on the segmented fastener and allowing the segments to separate and release the restraint mechanism. Restraint mechanisms using such EM restraint release devices, systems and methods may not need periodic recertification or replacement of energetics and may not have a risk of cook-off resulting from heat soak of thermally sensitive devices during operational and fault scenarios.

Abstract: A system that provides wireless power transfer between a weapon and a platform. A method for loading, testing, targeting, and launching a weapon.

Abstract: The invention relates to a support member for supporting a shell into the barrel of a breech-loading weapon, and a method. The support member (6) comprises means for fastening a support element (8) to at least one fin (5) belonging to the tail end (4) of a shell (1). The means comprise at least one fastening piece (10), which comprises: at least one first fastening surface (14a), which may be arranged substantially parallel with a side of the fin (5), and which fastening piece (10) may be supported to the support element (8); at least one second fastening surface (14b), which second fastening surface (14b) is movably arranged so that the second fastening surface (14b) is movable in relation to the first fastening surface (14a) in a direction transverse to the longitudinal axis (L) of the shell (1); and means for pressing the fastening surfaces (14a, 14b) against the sides of the fin (5) arranged between them so as to provide friction locking between the fastening piece (10) and the fin (5).

Abstract: In an embodiment of methods and apparatus for a control surface restraint and release system comprises a restraint apparatus detachably coupled to the control surface, a guidance rail slidably engaging the restraint apparatus, and a stopping mechanism coupled to the guidance rail and configured to stop a movement of the restraint apparatus.

Abstract: A system that provides wireless power transfer between a weapon and a platform. A method for loading, testing, targeting, and launching a weapon.

Abstract: The present invention relates to launching system, more particularly relates to mobile launching system for missiles. The mobile missile launch system comprising a vehicle (14) having a chassis structure adapted to carry the launch system; a mounting frame (16) comprising predetermined truss framework mounted onto the chassis structure; plurality of sliding mechanisms mounted at rear end of the mounting frame (16); plurality of canisters (43) mounted onto said beam (22) and plurality of missiles (11) ensconced within the canisters (43); plurality of containers (42) enclosing said canisters (43) and are connected to the saddles (32, 34) for linear movement; plurality of resting units (27) abutting to rear end of the canisters (43) and are adapted to move linearly to transfer reaction forces from said missiles (11) to ground.

Abstract: The invention efficiently and effectively secures and releases a rail-launched missile. An asymmetrical secure-release wheel (70) is defined by several surfaces which extend radially outward from a pivot hole (70K). The surfaces include a wheel unlatch surface (70H), a wheel notch stop surface (70D), a wheel detent surface (70G), a clockwise stop surface (70C) and a counterclockwise stop surface (70B). The wheel (70) is rotatable within a wheel housing (72). When a missile is loaded onto the launch rail, the middle shoe of the missile engages the detent surface (70G) of the wheel. During missile launch, the plume of the missile moves a trigger (110) which pulls a connecting rod (52) aft which results in a wheel lock (78) being disengaged from the detent surface (70G). A microswitch (56) provides a signal indicating whether the wheel (70) is in a latched or unlatched state.

Abstract: The invention efficiently and effectively secures and releases a rail-launched missile. An asymmetrical secure-release wheel (70) is defined by several surfaces which extend radially outward from a pivot hole (70K). The surfaces include a wheel unlatch surface (70H), a wheel notch stop surface (70D), a wheel detent surface (70G), a clockwise stop surface (70C) and a counterclockwise stop surface (70B). The wheel (70) is rotatable within a wheel housing (72). When a missile is loaded onto the launch rail, the middle shoe of the missile engages the detent surface (70G) of the wheel. During missile launch, the plume of the missile moves a trigger (110) which pulls a connecting rod (52) aft which results in a wheel lock (78) being disengaged from the detent surface (70G). A microswitch (56) provides a signal indicating whether the wheel (70) is in a latched or unlatched state.

Abstract: A restraint for immobilizing a projectile with respect to its launch system is disclosed. When electromagnetic force is applied to the restraint, the restraint releases the projectile, thereby enabling its launch.

Abstract: In an embodiment of methods and apparatus for a control surface restraint and release system comprises a restraint apparatus detachably coupled to the control surface, a guidance rail slidably engaging the restraint apparatus, and a stopping mechanism coupled to the guidance rail and configured to stop a movement of the restraint apparatus.

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: A restraint for immobilizing a projectile with respect to its launch system is disclosed. When electromagnetic force is applied to the restraint, the restraint releases the projectile, thereby enabling its launch.

Abstract: A mobile projectile launcher is disclosed having a tiltable launching platform for supporting a plurality of canisters in each of which projectiles to be launched are stored and fired, a support plate pivotally connected to a horizontal cargo bed, and at least one linear actuator by which the support plate is swingable from a closed position substantially perpendicular to the cargo bed to an open position substantially parallel to the cargo bed. The support plate is made of a material that is resistant to the projectile plume following launching and is sufficiently sturdy to support a technician during the loading of projectiles when set in an open position, yet is adapted to protect and hide the loaded canisters when set in a closed position.

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 missile launch and guidance apparatus of a rail-shoe launching type is disclosed. In a missile adapted to be launched while moving along a rail of a launch tube, a missile launch and guidance apparatus comprises: a bushing inserted into a missile body; a shoe, one end of which is inserted into the bushing, and the other end of which is in contact with the rail; and a spring inserted between the bushing and the shoe so as to provide a separation force to the shoe against the bushing. By separating the shoe from the missile in a lateral direction of the missile launching direction by an elastic force of the spring after launching the missile, the missile launch and guidance apparatus can keep constant the gap between the missile and the launch tube rail irrespective of the behavior of the missile taking place in a launching process, and the drag and weight of the missile launched from the launch tube is reduced to thereby exhibit the maximum flight performance.

Abstract: A restraint for immobilizing a projectile with respect to its launch system is disclosed. When electromagnetic force is applied to the restraint, the restraint releases the projectile, thereby enabling its launch.

Abstract: A passively-actuated apparatus for providing shock-absorption between a missile and a missile canister prior to missile launch, and for moving out of the path of a missile during missile launch. The apparatus comprises a snubber coupled to a passive actuator that drives a snubber from a position wherein the snubber is engaged with a missile to a position wherein the snubber is cleared from the path of any portion of the missile during launch. The actuator is purely mechanical in nature, and is passively-actuated by the motion of the missile itself as the missile begins launch.

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: A device is provided for holding and releasing a missile within a canister. The device includes a housing attached to the canister, a latch mechanism extending from the housing into the canister, a tension applier disposed in the housing to restrain the missile in the canister, a release mechanism disposed on the housing, an interface mechanism and a compression applier. The tension applier forces the latch mechanism against the housing to withdraw from the missile. The interface mechanism initially couples the release mechanism and the tension applier. The compression applier anchors to the interface mechanism and forces the latch mechanism against the housing to engage the missile and counteract said tension applier. On command, the release mechanism disengages from the housing to release the compression applier from the interface mechanism. This action enables the tension applier to withdraw the latch mechanism from the missile.

Abstract: A cold-gas munitions launch system is disclosed. In the illustrative embodiment, the system includes a munitions canister, a gas generator, and a sled. The sled supports a munition. The gas generator is located in the aft end of the munitions canister. When ignited, the gas generator produces gas, which drives the sled forward. As the sled reaches the end of the canister, the munition is launched by its own inertia, at a velocity that is within the range of about 3 to 9 g. After the munition clears the canister and travels at least about 150 feet from it, the munition's booster is ignited.

Abstract: The illustrative embodiment of the present invention is a munitions launch system. The launch system comprises a canister and a cold launch system. In the illustrative embodiment, the cold launch system comprises a sled and a release system. In the illustrative embodiment, the release system includes a sled release mechanism, which releasably secures the sled to the munitions canister, and a munitions release mechanism, which releasably secures a munition to the sled. Actuation of the sled release mechanism releases the sled for movement within the canister. After the sled moves some minimal distance under applied force, the munitions release mechanism “automatically” actuates, releasing the munition from the sled so that the munition can be ejected from the canister.

Abstract: The illustrative embodiment of the present invention is a munitions launch system. The launch system comprises a canister and a cold launch system. In the illustrative embodiment, the cold launch system comprises a sled and a release system. In the illustrative embodiment, the release system includes a sled release mechanism, which releasably secures the sled to the munitions canister, and a munitions release mechanism, which releasably secures a munition to the sled. Actuation of the sled release mechanism releases the sled for movement within the canister. After the sled moves some minimal distance under applied force, the munitions release mechanism “automatically” actuates, releasing the munition from the sled so that the munition can be ejected from the canister.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead having destructive elements. The weapon also includes a folding lug switch assembly that provides a mechanism to attach the weapon to a delivery vehicle and is configured to close after launching from the delivery vehicle, thereby satisfying a criterion to arm the warhead. The weapon still further includes a guidance section including an antenna configured to receive mission data before launching from the delivery vehicle and further configured to receive instructions after launching from the delivery vehicle to guide the weapon to a target.

Abstract: A launch tube system has two concentric sleeves. An inner sleeve having holes formed therethrough defines a launch tube, and an outer sleeve surrounds the inner sleeve and is spaced apart therefrom. One or more flexible bladders are disposed between the inner outer sleeves. When filled with fluid, the flexible bladder(s) expands and extends into and through the holes and into confines of the inner sleeve to thereby form shock isolation for a projectile housed in the inner sleeve.

Abstract: A launcher includes a plurality of launch tubes for stowing and launching a plurality of air vehicles. A central air manifold is operatively connected to an air storage tank; a first launch tube air manifold is operatively connected to a first group of the launch tubes and operatively connected to the central air manifold. The first launch tube air manifold has a separate port corresponding to each launch tube of the first group of launch tubes. A release valve mechanism is removably mounted in one of the ports of the first launch tube air manifold, the release valve mechanism controlling the passage of launch air between the first launch tube air manifold and the launch tube corresponding to the port in which the release valve mechanism is mounted. A plug is removably mounted in each of the ports not occupied by the release valve mechanism.

Abstract: A pressure-released brake assembly restrains a projectile in a launch tube prior to launch and automatically releases the projectile at launch. A brake assembly housing defines cavities that extend substantially radially out from the projectile when the housing is attached thereto. A brake pad adjoins the housing and has holes formed therethrough with each hole being aligned with one of the housing's cavities. Means are provided for positioning a loose-fitting pin partially in each of the brake pad's holes and partially in a correspondingly aligned housing cavity. When a launch pressure is generated in the projectile's launch tube, the launch pressure acts on each pin via the holes in the brake pad. The launch pressure causes the positioning means to fail and drives each pin out of engagement with the brake pad to effectively uncouple the brake pad from the housing.

Abstract: A pressure-released brake assembly restrains a projectile in a launch tube prior to launch and automatically releases the projectile at launch. A brake assembly housing defines cavities that extend substantially radially out from the projectile when the housing is attached thereto. A brake pad adjoins the housing and has holes formed therethrough with each hole being aligned with one of the housing's cavities. Means are provided for positioning a loose-fitting pin partially in each of the brake pad's holes and partially in a correspondingly aligned housing cavity. When a launch pressure is generated in the projectile's launch tube, the launch pressure acts on each pin via the holes in the brake pad. The launch pressure causes the positioning means to fail and drives each pin out of engagement with the brake pad to effectively uncouple the brake pad from the housing.

Abstract: A launch capsule assembly having a buoyant main body for a payload of a missile or other unmanned vehicle. The main body includes a plurality of lobes contributing to its interior. The lobes project perpendicular to and away from the longitudinal axis of the main body with the interior of each projecting lobe sized to accommodate at least one projecting fin of the payload. The top of the main body removably attaches to a top cap projecting hydrodynamically from the main body. The bottom of the main body removably attaches to a bottom cap machined to have a matching cross-section to the main body of the capsule.

Abstract: The invention relates to a container for propellant charge modules to be loaded into a weapon using conveyance means. It comprises protection means insulating said modules from the conveyance means, constituted by a rigid tubular body, a sheath intended to receive the modules and means to block the modules in the sheath. The sheath is made of a deformable material. The blocking means ensure the deformation of the sheath to immobilize the modules. Application to charge module conveyance.

Abstract: A method of launching a missile in a given direction is described comprising the steps of: i) storing a missile in a housing ii) ejecting the missile from the housing while imparting a tumbling motion to the missile, the direction of tumble being selected to decrease the angle between the longitudinal axis of the missile and the given direction and iii) firing the missile and steering it to the given direction. By such a method a missile launcher is provided which is capable of firing a missile at any azimuth angle of between 0 and 360°, within 0.1 second of receiving a signal to launch. The missile may be launched by a single ejector piston at the base of the missile acting in a direction off-set from the longitudinal axis of the missile.

Abstract: The passive dynamically disconnecting arm features an arm having two ends wherein attached to the first end is a housing having both a plunger and an electrical connector providing positive engagement force during shock or vibration. The second end of the arm features a trunnion and torsion spring. The arm features a slot wherein a rod is placed inside operatively coupled to both the plunger and trunnion. When an object is attached to the electrical connector, the spring-loaded plunger compresses preventing the rod from moving and causing the second end of the rod to couple with a divot within the trunnion. When the object moves a predetermined distance, the spring-loaded plunger decouples from the rod and the electrical connector detaches from the object. The arm, by means of a torsion spring attached to the arm's second end, translates and rotates out of the object's path without striking the object.

Abstract: The product includes a self-propelled aerial pyrotechnic device and an upright launch tube for the device. The device is closely confined within the launch tube so as to be maintained in an essentially truly vertical orientation in preparation for launch. The device itself comprises a body containing pyrotechnic display material and an engine that serves to propel the body when ignited. A stabilizing base, preferably integrally molded from synthetic resinous material, is attached to the lower end of the body and is in the nature of a framework having a plurality of symmetrically disposed, long legs interconnected at various locations by strut structure. The engine is received within a socket at the upper end of the stabilizing base and is adhered to interior surfaces of the legs to provide a secure connection between the body and the base.

Abstract: A launch vehicle mounting system for use in launching either of first and second launch vehicles having different booster diameters is disclosed. In one embodiment, the launch vehicle mounting system includes a mounting frame and a plurality of arms pivotally interconnectable to the mounting frame for supporting either of the first and second launch vehicles positionable thereon. In particular, the launch vehicle mounting system of the present invention is adapted to support either the first or the second launch vehicle as the arms are at least radially adjustable relative to the mounting frame to at least first and second radial positions corresponding to the booster diameters of the first and second launch vehicles.

Abstract: An apparatus for restraining and releasing a missile using a rigid sphere is disclosed.