Abstract: An erection device and method for the marine hot launch of a rocket are provided. The erection device includes a launch vessel, a launch pad, an erection assembly, a guide member, a driving cylinder, a sliding member, and a connecting member. The sliding member cooperates with the guide member and is driven by the driving cylinder to move linearly. The connecting member has one end hinged to the erection assembly at a certain angle and the other end connected to the sliding member and is configured to move with the sliding member to drive the erection assembly to be erected on the launch pad. The erection device and method can achieve an effective erection of the rocket for marine hot launch with a desired erection effect and high stability.

Abstract: After deploying its payload, the final stage of a launch vehicle is maneuvered to couple the nosecone of the launch vehicle to the ‘rear’, or ‘engine-end’ of the final stage. The nosecone covers the engine of the final stage, to protect the engine and related components from the heat of re-entry and the impact of landing. Placing the nosecone over the engine and orienting the combination such that the nosecone ‘leads’ the final stage during re-entry, places the center of gravity of the combination ahead of the center of pressure in the direction of travel. Accordingly, the combination is inherently stable as it re-enters the atmosphere and falls to earth. Parachutes and directional devices are used to provide a controlled soft landing.

Abstract: A 1-to-N munitions adapter that includes a physical launcher interface, a physical munitions interface, and electronic control circuitry. The physical launcher interface is operable to connect the 1-to-N munitions adapter to a single munition launcher that is i) configured and arranged to carry and launch a single munition of a first type, and ii) integrated to an airborne platform. The physical munitions interface is operable to connect the 1-to-N munitions adapter to multiple munitions of a second type. The 1-N munitions adapter i) emulates a control interface of a single munition of the first type to the single munition launcher, in part by identifying the 1-to-N munitions adapter to the single munition launcher as a single munition of the first type, and ii) selectively controls the release of munitions of the second type while the airborne platform is in flight in response to signals received from the single munition launcher.

Abstract: An ammunition box with a rectangular molded thermoplastic material box body defining a rectangular storage space for ammunition. The box body opens to one side that can be closed with a flat rectangular molded thermoplastic material lid. The box body and the lid are provided with means for reinforcing and stabilizing the box body and the connection between the box body and the lid.

Abstract: A multiple missile carriage and launch guidance module comprising a plurality of missile launch rails that are each configured to carry and guide the launch of a missile and are carried on a common missile carriage wall in respective positions and orientations allowing for missile carriage and launch from the rails.

Abstract: A rocket launch tower is provided, including: a vertical support structure including two or more guide towers defining a vertical shaft between the two or more guide towers, each guide tower including one or more pulleys engaging one or more cables; a platform located within the vertical shaft and connected to the one or more cables; a drive mechanism that applies a force to the one or more cables to accelerate the platform along a trajectory within the vertical shaft; one or more sensors collecting data regarding the position of the platform along the trajectory within the vertical shaft and communicating the platform position data to a controller, the controller in communication with an acceleration control system including one or more brakes acting on the platform; wherein the controller causes the acceleration control system to actively correct the platform acceleration towards an intended platform acceleration.

Abstract: A cover for an empty rail missile launcher that can be used in flight. The cover is shaped to reflect radar signals transmitted by a radar transmitter away from the radar transmitter to reduce detectibility by radar. The cover may also be coated with radar absorbent material to reduce detectibility by radar. Hangers are used to mount the cover to the rail missile launcher. The cover is provided with a grounding mechanism to dissipate precipitation static. A restraint mechanism is provided to prevent the cover from inadvertently sliding off the rail missile launcher.

Abstract: A rocket launch tower is provided, including: a vertical support structure including two or more guide towers defining a vertical shaft between the two or more guide towers, each guide tower including one or more pulleys engaging one or more cables; a platform located within the vertical shaft and connected to the one or more cables; a drive mechanism that applies a force to the one or more cables to accelerate the platform along a trajectory within the vertical shaft; one or more sensors collecting data regarding the position of the platform along the trajectory within the vertical shaft and communicating the platform position data to a controller, the controller in communication with an acceleration control system including one or more brakes acting on the platform; wherein the controller causes the acceleration control system to actively correct the platform acceleration towards an intended platform acceleration.

Abstract: A multiple missile carriage and launch guidance module comprising a plurality of missile launch rails that are each configured to carry and guide the launch of a missile and are carried on a common missile carriage wall in respective positions and orientations allowing for missile carriage and launch from the rails.

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 selectively affecting a launch trajectory of a projectile from a canister includes means for selectively positioning the projectile with respect to the canister and a sabot operably associated with the projectile and the means for selectively positioning the projectile. A projectile launch system includes a canister, a projectile disposed in the canister, and means for selectively positioning the projectile with respect to the canister. A method for affecting a launch trajectory of a projectile includes providing a canister and a projectile disposed in the canister and adjusting a position of the projectile with respect to the canister.

Abstract: An apparatus for directing the launch of a projectile from a canister includes a pusher plate disposed in the canister, the pusher plate having a sliding, sealing engagement with the canister to define a closed volume, the projectile being disposed in the canister and resting on the pusher plate; and means for generating exhaust gas into the closed volume to urge the pusher plate and the projectile toward an opening of the canister. The apparatus further includes means for directing exhaust gas to affect the trajectory of the projectile.

Abstract: According to one embodiment, an apparatus comprises a frame portion made of metal and having a substantially elongated shape. The frame portion comprises one or more cavities situated in a longitudinal direction, and a composite material is disposed within the cavities to structurally reinforce the frame portion. The frame portion includes one or more missile guides situated in the longitudinal direction and configured to slidingly engage a weapon.

Abstract: Methods and apparatus for launching an effector according to various aspects of the present invention may include a fire control system. The fire control system may be responsive to a sensor, such as a radar, and may be connected to the effector, such as via a launcher. The file control system may be adapted to generate a fire control solution according to the data from the sensor, initiate a launch of the effector, and provide the fire control solution to the effector after initiating the 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: Device for launching missiles from a ship, includes at least one missile launch ramp, includes a ditch delimited by side walls of which at least two constitute bulwarks which extend around the periphery of the ship, the ditch being open above the exterior deck of the ship, in that the launch ramp is positioned in the ditch so it can be used to launch a missile over a lateral bulwark of the ditch extending around the periphery of the ship. It includes an element for discharging the missile propulsion gases including a duct opening onto an orifice in a lateral bulwark of the ditch extending around the periphery of the ship, and the lateral bulwarks of the ditch are of a height tailored to conceal the missiles in place on the ramp, for angles of incidence of between 0 and ?5° with respect to the deck of the ship.

Abstract: According to one embodiment, an apparatus comprises a frame portion made of metal and having a substantially elongated shape. The frame portion comprises one or more cavities situated in a longitudinal direction, and a composite material is disposed within the cavities to structurally reinforce the frame portion. The frame portion includes one or more missile guides situated in the longitudinal direction and configured to slidingly engage a weapon.

Abstract: An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times.

Abstract: An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times.

Abstract: Methods and apparatus for communications between a fire control system and an effector according to various aspects of the present invention may include a communications link. The communications link may be coupled to a launcher for the effector and the effector. The communications link is detachably coupled to at least one of the launcher and the effector. The communications link may be adapted to transmit a fire control solution to the effector after initiating the launch.

Abstract: An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times.

Abstract: A missile launching system including a launch rail for attachment to an aircraft and having a longitudinal slot, and at least two hangers for attachment to the missile at longitudinally spaced locations thereof and having a cross-section configured to be received in the longitudinal slot in the launch rail. The rearmost hanger includes two separable main parts, including a first main part for engagement with a respective lateral, first groove section of the slot, and a second main part configured to be attached to the missile and be slidably guided in a second groove section of the slot normal to the first groove section and opening towards the missile. The second main part includes laterally extending collars configured to interact in close proximity with respective rail sections facing the missile. The second main part is configured to separate from the first part when launching the missile.

Abstract: Device for launching missiles from a ship, includes at least one missile launch ramp, includes a ditch delimited by side walls of which at least two constitute bulwarks which extend around the periphery of the ship, the ditch being open above the exterior deck of the ship, in that the launch ramp is positioned in the ditch so it can be used to launch a missile over a lateral bulwark of the ditch extending around the periphery of the ship. It includes an element for discharging the missile propulsion gases including a duct opening onto an orifice in a lateral bulwark of the ditch extending around the periphery of the ship, and the lateral bulwarks of the ditch are of a height tailored to conceal the missiles in place on the ramp, for angles of incidence of between 0 and ?5° with respect to the deck of the ship.

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: This missile launcher is characterized in that the cells do not extend in rows parallel to an elongated chimney, but by surrounding a central chimney, providing a more compact and especially lighter arrangement with identical resistance conditions.

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: An apparatus for selectively affecting a launch trajectory of a projectile from a canister includes means for selectively positioning the projectile with respect to the canister and a sabot operably associated with the projectile and the means for selectively positioning the projectile. A projectile launch system includes a canister, a projectile disposed in the canister, and means for selectively positioning the projectile with respect to the canister. A method for affecting a launch trajectory of a projectile includes providing a canister and a projectile disposed in the canister and adjusting a position of the projectile with respect to the canister.

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 dynamic barrier system including a number of sensors that monitor a barrier area to determine specific types of objects approaching, within, or exiting the barrier area. Depending upon the type of object(s), the dynamic barrier system initiates an appropriate action, both lethal and non-lethal. The barrier system may advantageously deactivate after its intended period of operation eliminating difficult and/or dangerous removal.

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 missile launcher including a forward support for supporting a forward portion of a missile, and an aft support for supporting an aft portion of the missile where the forward support is arranged to swing clear of the aft portion of the missile during the initial period of its launching run where the forward support comprises a roll member being in the shape of a segment of a circle and pivoted at the circle center, wherein the perimeter of the roll member is arranged to make frictional contact to the missile fuselage in order to confer mechanical energy to the roll member to make the member to swing clear of the aft portion of the missile during the initial period of the missile's launching run.

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 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 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 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 missile launching system including a launch rail for attachment to an aircraft and having a longitudinal slot, and at least two hangers for attachment to the missile at longitudinally spaced locations thereof and having a cross-section configured to be received in the longitudinal slot in the launch rail. The rearmost hanger includes two separable main parts, including a first main part for engagement with a respective lateral, first groove section of the slot, and a second main part configured to be attached to the missile and be slidably guided in a second groove section of the slot normal to the first groove section and opening towards the missile. The second main part includes laterally extending collars configured to interact in close proximity with respective rail sections facing the missile. The second main part is configured to separate from the first part when launching the missile.

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: An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times.

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: This missile launcher is characterized in that the cells (12) do not extend in rows parallel to an elongated chimney, but by surrounding a central chimney, providing a more compact and especially lighter arrangement with identical resistance conditions.

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: 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: 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 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 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: A convertible multipurpose missile launcher includes a launch rail structure on the launcher body with a first-missile launch rail on the bottom side of the launcher body extending in a longitudinal direction. The first-missile launch rail is dimensioned for a first missile. A second-missile launch rail is positioned on the bottom side of the launcher body and extends in the longitudinal direction. The second-missile launch rail is dimensioned for a second missile different from the first missile. The second-missile launch rail includes a stationary second-missile forward launch rail segment, and a movable second-missile aft launch rail segment. The movable second-missile aft launch rail segment is slidable on the launcher body, and preferably on the first-missile launch rail, between a forward position and an aft position and may be locked in these positions.

Abstract: A launch canister for a missile, including an outer canister shell and a concentric inner liner. The inner liner augments the canister shell with structural load capability and bending inertia to enhance canister stiffness. The inner liner can be constructed from structural load carrying composite materials, and also acts as a thermal and ablative insulator to enable vertical plume venting away from the enveloped missile. A shock and vibration isolation layer can be laminated between the inner liner and canister shell.

Abstract: A canister for launching a missile having a cylindrical outer tube with a hemispherical head releaseably secured to its lower end connected through stiffeners to an inner tubular member to form a passage for the gases generated when the missile is fired. A restraint mechanism secures the missile to a base plate, which is itself mounted on shock absorbers, with a release mechanism responsive to the firing of the missile for disabling the restraint mechanism.