902results about "Rocket launchers" patented technology

An unmanned aerial vehicle (UAV) system provides for UAV deployment and remote, unattended operation with reduced logistics requirements. The system includes a launcher that can include one or more launch tubes, each launch tube configured to house a UAV in a canister and one or more gas generators operatively connected to each canister and configured to push the UAV out of the launch tube by releasing gas into the canister. A controller for activating the gas generators can sequentially, and with a predetermined time delay, expel the UAV with a desired velocity and acceleration. The system further includes a UAV recovery device, a power supply, a security subsystem, a command and control subsystem and a communications subsystem. Command, control and communications can be provided between a remote station and the UAV.

A fast acting active protection system for military vehicles defeats RPG (rocket propelled grenade) threats fired from close ranges. The system minimizes the hazard to troops and civilians nearby. The system uses a plurality of passive sensors to locate the threat and initialize the system. A low cost radar or laser tracker is used as the means to determine range, velocity, and (if required) angular position of the threat. The countermunition used may be one of several choices, with the requisites being that the countermunition provides fast response with low inertia, and is able to damage or destroy the detected threat. A multi-barrel recoilless gun is the weapon of choice. A launching device is used to deploy and aim the countermunition and the tracking means. On board software and electronics are used to control the system.

A system and method for the conversion of fuel tanks, detachably mountable on the exterior of an aerial vehicle, into high volume, high capacity, diverse functionality and aerodynamically efficient airborne stores is disclosed. A conventional external fuel drop tank is modified such that the exterior shape of the tank is substantially retained while the interior of the tank is suitable restructured to allow for the introduction of diverse airborne stores, associated airborne store mounting means, control and monitoring means and support means therein, which replace the fuel store. The airborne store is suitably interfaced to the stores control and management system of the aerial vehicle. The airborne store is integrated into a new external stores configuration The enhanced airborne store will have aerodynamic characteristics substantially similar to the original external fuel tank while its payload capacity is substantially improved.

An air-launched aircraft includes deployable wings, elevons, and vertical fins that deploy from a fuselage during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and / or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The aircraft may be employed at a low cost for any of a wide variety of functions, such as surveillance, or as a decoy. The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.

In one embodiment there is provided a radar signature and induced aerodynamic drag minimizing, externally mountable, internally configurable pod structure optimized for internal placement of one or more deployable stores through configuration and optimal kinematic operation of a pod door assembly. The pod structure has an externally mountable pod housing, a predetermined pod housing cross-sectional configuration optimized to provide a configurable interior volume accommodating multiple different store configurations, and a predetermined pod housing configuration having a cross-sectional configuration optimized to minimize a radar signature and an induced aerodynamic drag. The pod structure further has a pod door assembly integral with the pod housing and having a plurality of pod doors and one or more seal door mechanism assemblies. The pod structure is optimized in kinematic operational combination of the pod doors and seal door mechanism assemblies controlling ejection launch envelopes.

A system and method for the conversion of fuel tanks, detachably mountable on the exterior of an aerial vehicle, into high volume, high capacity, diverse functionality and aerodynamically efficient airborne stores is disclosed. A conventional external fuel drop tank is modified such that the exterior shape of the tank is substantially retained while the interior of the tank is suitable restructured to allow for the introduction of diverse airborne stores, associated airborne store mounting means, control and monitoring means and support means therein, which replace the fuel store. The airborne store is suitably interfaced to the stores control and management system of the aerial vehicle. The airborne store is integrated into a new external stores configuration The enhanced airborne store will have aerodynamic characteristics substantially similar to the original external fuel tank while its payload capacity is substantially improved.

Launching payloads at high velocity uses high-pressure gas or combustion products for propulsion, with injection of high pressure gas at intervals along the path behind the payload projectile as it accelerates along the barrel of the launcher. An inner barrel has an interior diameter equal to the projectile diameter or sabot containing the projectile. An outer casing surrounds the inner barrel. Structures at intervals attach the outer casing and the inner barrel. An axial gas containment chamber (AGC) stores high pressure gas between the inner barrel wall, the outer casing wall, and enclosure bulkheads. Pressure-activated valves along the barrel sequentially release the high pressure gas contained in the AGC in to the barrel to create a continuously refreshed high energy pressure heads behind the projectile as it moves down the barrel. A frangible cover at the exit end of the barrel allows the barrel to be evacuated prior to launch. The launcher is rapidly recyclable. The valves close automatically after the projectile has exited the barrel, allowing a new projectile to be introduced into the breech and the AGC to be recharged with high-pressure gas.

A method of launching a catapult, a catapult and a locking device for a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) can be provided with a high acceleration by directing a launching force (F1) generated by a launching device thereto. The carriage (4) can be held at a launching position (6) by means of the locking device (9). The catapult further comprises a takeoff damper (34) that generates a damping force (F2) having a direction opposite relative to the launching force. Accordingly, the takeoff damper (34) restricts the acceleration of the carriage (4) at the initial launching moments.

In a method and apparatus for controlling the deployment of a towline connecting a mooring craft to an ejected object comprising the steps of monitoring velocity to determine when a point for optimum braking has been achieved and then engaging a brake system to retard deployment of the towline, a DC motor augments and controls the brake system. The DC motor further controls the retrieval of the object. A cutter mechanism uses a first blade to grip the towing cable to maintain tension thereon as a second blade cuts the cable. A spring biased boom in combination with spring biased fins on the ejected object rapidly deploys the object from its storage housing. A locking mechanism secures the deployment mechanism in a stable locked position upon the object reaching its fully extended position.

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.

An unmanned aerial surveillance and reconnaissance system are disclosed wherein an unmanned aerial vehicle is launchable from a launch tube, for instance, the bore of an existing weapons system mounted on a mobile vehicle, such as a weapon barrel of a tank or armored combat vehicle and which the launch may be remotely initiated from the protected armored compartment of the mobile vehicle.

A launch system is provided in which an unmanned aerial vehicle is secured to a platform in a watertight tube adapted to be launched from a submerged platform. Once launched, side panels on the tube are jettisoned and a flotation device is deployed to bring the tube to the surface. The flotation device maintains the tube in a vertical position when rising to and at the surface. After surfacing, a top-sealing cap of the tube is opened. A lifting mechanism within the tube raises the vertically oriented platform assembly up within the tube. Guide rails maintain the vertical orientation of the assembly during lifting. At the topmost point of travel, the assembly is raised clear of the tube and is disengaged from the guide rails, allowing the assembly to pivot about its attachment to the lifting mechanism and assume an orientation favorable for launching the UAV.

An anti-tank guided missile (ATGM) weapon system with an overhead mounted, electrically driven, remote controlled weapon station that supports a tube-launched optically-tracked wire-guided (TOW) missile launcher and a machine gun, typically the caliber .50 M2, on a single traversing and elevating platform. Above-deck assemblies include the TOW and gun cradle, a dual pod missile launcher, the Improved Target Acquisition System (ITAS), target acquisition subsystem (TAS), elevation and traverse motors and gear transmissions and drive electronics, and an ammunition case. Below-deck assemblies include the ATGM weapon system control handles, biocular display, control panel, ITAS fire control system (FCS), ITAS battery power source (BPS), slip-ring, and gunner's seat. Electrical cables connecting the two assemblies penetrate the vehicle deck directly below the weapon System.

A stealth weapon module (10) including a weapon support cage (11) and a weapon (12), with the weapon module (10) able to be stowed beneath a retractable hard roof (15). The roof (15) is raised and lowered by a hydraulic motor (16), and includes a stabilizing cloth (15b) that keeps the roof (15), made of interconnected slats (15a), from pulling apart or otherwise changing shape as it is raised and lowered, even at rates of travel of several inches per second. The weapon module (10), with any of various different roof designs including the retractable hard roof (15), can be incorporated into either a transportable shell (20), able to be moved from one application to another, or can be built into (and so specially adapted to) a structure, such as the back / cab of a sports utility vehicle.

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.

A weapon interface system, and methods of operating the same. The weapon interface system is coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system. The weapon interface system includes a translation interface configured to provide an interface between the electrical interconnection system and an inductive power and data circuit. The weapon interface system also includes a weapon coupler, coupled to the translation interface, configured to provide an inductive coupling to the weapon system to provide mission information thereto.

The invention relates to an integrated impact composite film cover, belonging to the missile emit technique. Wherein, said film cover uses glass fiber and epoxy resin as main raw materials, while the inner surface is adhered with aluminum foil as the electromagnetic shield layer; it is characterized in that: form outer to inner, it comprises a frame (1), a weal section (2), and main body (3), while the main body (3) is layered by the method that [(0degree90degree)(+- 45degree)(0degree90degree)(+-45degree)] with isotropy plates, to form the same periphery strength, and it is adhered to the frame (1); the adhering part is the weak section (2); the upper and lower surface of said adhering part are adhered with cloth or cloth bar to strengthen the weak section (2). The invention can adjust the strength of weak section via adjusting the layer number and width, to meet the demand of different pressures. The invention has simple structure and simple process.

An umbilical cable for delivering electrical signals between an aircraft and a smart weapon carried by the aircraft. The umbilical cable includes cabling comprising a plurality of conductive wires, a first connector provided on one end of the cabling and configured to connect to the aircraft, and a second connector provided on the other end of the cabling and configured to connect to the smart weapon. The umbilical cable further includes an interface circuit electrically coupled between the first connector and the second connector via the plurality of conductive wires. The interface circuit is configured to receive via the first connector a non-standard combination of signals comprising at least one of data signals, control signals and power signals not receivable directly by the smart weapon to carry out operations. Moreover, the interface circuit is configured to convert the non-standard combination of signals to a set of signals receivable by the smart weapon to carry out operations, and to provide the set of receivable signals to the smart weapon via the second connector.

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.

An umbilical cable for delivering electrical signals between an aircraft and a smart weapon carried by the aircraft. The umbilical cable includes cabling comprising a plurality of conductive wires, a first connector provided on one end of the cabling and configured to connect to the aircraft, and a second connector provided on the other end of the cabling and configured to connect to the smart weapon. The umbilical cable further includes an interface circuit electrically coupled between the first connector and the second connector via the plurality of conductive wires. The interface circuit is configured to receive via the first connector a non-standard combination of signals comprising at least one of data signals, control signals and power signals not receivable directly by the smart weapon to carry out operations. Moreover, the interface circuit is configured to convert the non-standard combination of signals to a set of signals receivable by the smart weapon to carry out operations, and to provide the set of receivable signals to the smart weapon via the second connector.

A sea-launched and recovered unmanned aircraft is disclosed. The aircraft is jet-powered and has features and systems to maintain watertight integrity such that it may be released from a submerged submarine or dropped into a body of water by a ship or an aircraft. The aircraft is buoyant and remains at or near the water surface before its rockets are ignited. The rockets propel the air vehicle out of the sea and accelerate it to flying speed at which time a jet engine is started and the rockets are jettisoned. The air vehicle performs its mission independently or in conjunction with other ones of the air vehicles. The air vehicle then returns to an assigned splashdown point at sea via, for example, an engine-off “whip-stall” maneuver. A submarine or ship may retrieve the air vehicle and readies it for another mission.

An underwater launch system includes a launch tube frangibly sealed at its forward end. At launch time, pressure equalization means introduces water at depth pressure into the launch tube between its frangibly sealed ends. A rotary electromagnetic pump coupled to the launch tube receives water at depth and expels the water at a higher pressure. The higher pressure water is coupled to the aft end of the launch tube.

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.

A distributed ground sensor threat detection system, which is an automated missile warning system designed to provide reliable, timely and accurate missile location information of shoulder-launched SAMs within the volume under surveillance by a network of sensors. Remote sensor nodes position in proximity to an airport runway monitor the area between the nodes to locate threat missiles. Detection information from each remote sensor node is sent to a central processing node which processes the information to determine if a threat missile is launched against a commercial aircraft.

The invention discloses a solid-liquid power sounding rocket land launching sequential control system which comprises a main control computer, a ground sequential control system and a rocket-mounted single chip computer control system, wherein the main control computer sends a control command to the ground, sequential control of a rocket-mounted engine igniter is achieved through the ground sequential control system which is further used for conducting the sequential control on a rocket-mounted engine liquid path valve and the rocket-mounted single chip computer control system, and meanwhile opening and closing condition information of the rocket-mounted engine igniter and the liquid path valve is obtained and sent to the main control computer. The sequential control of a rocket-mounted engine pressurized valve is achieved by the rocket-mounted single chip computer control system, and meanwhile the closing and opening condition information of the rocket-mounted engine pressurized valve is obtained and sent to the main control computer through the ground sequential control system. The solid-liquid power sounding rocket land launching sequential control system has the advantages of solving the key problems of matching the solid-liquid power sounding rocket ground sequential control with a rocket-mounted sequential control circuit and meeting millisecond level requirements of launching sequential errors.

A launcher system and method for an unmanned aerial vehicle (UAV), wherein the launcher system comprises a barrel comprising a prepackaged internal pusher cup configured behind the UAV housed within the barrel; an expansion chamber operatively connected around the barrel, wherein the barrel extends out of a first end of the expansion chamber; a muzzle adapter operatively connected to a second end of the expansion chamber, wherein the first end of the expansion chamber is positioned opposite to the second end of the expansion chamber; a rifle slip-fitted to the muzzle adapter; and a stand operatively connected to the expansion chamber, wherein a triggering of the rifle causes the internal pusher cup to push the UAV out of the barrel at a predetermined launch velocity in order to attain a predetermined self-propelled flight trajectory.