203results about "Missile propulsion" patented technology

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.

There is provided an active protection system and an active protection method preferably for airborne platforms. According to the embodiment of the invention, the active protection system is mounted onboard a platform for protecting the platform, and comprises a radar system configured for generating output data including threat output data corresponding to a velocity, a range, and an angle of the threat with respect to the platform in an airspace around the platform, the output data being useful for detecting, identifying and tracking of at least one threat approaching the platform; a countermeasure system capable of launching at least one non-fragmentation interceptor projectile in response to receiving a control command; and a control unit configured for receiving the output data from the radar system and for generating the control command and transmitting the control command to the at least one non-fragmentation interceptor projectile, thereby enabling countering the threat.

Apparatus for providing electrically initiated and/or controlled combustion of electrically ignitable propellants is provided. In one example, the apparatus includes a volume of electrically ignitable propellant (liquid and/or gas) capable of self sustaining combustion, and electrodes operable to ignite the propellant. The apparatus may further include a power supply and controller in electrical communication with the electrodes for supplying a potential across the electrodes to initiate combustion of the propellant and/or control the rate of combustion of the propellant. Various configurations and geometries of the propellant, electrodes, and apparatus are possible. In one example, the electrodes are supplied a direct current, which causes combustion of the propellant at the positive electrode. In another example, the electrodes are supplied an alternating current, which initiates combustion of the propellant at both electrodes.

A recoil-reducing weapon may include a housing and a receiver translatably disposed in the housing. A barrel may have one end fixed to the receiver and be translatable with respect to the housing. A spring stop may be fixed to the barrel forward of the housing and a spring may be disposed between the spring stop and a front of the housing. An operating group with a gear rack may be translatably disposed in the receiver. A longitudinal member may have one end fixed to the operating group. A counter-mass may have a second gear rack and an opening therein for receiving the longitudinal member. A second spring may be disposed around the longitudinal member. One end of the second spring may bear against the operating group and another end of the second spring may bear against the counter-mass. A pinion gear may be rotatably fixed to the receiver and operable to mesh with the gear rack and the second gear rack.

An electromagnetic launcher comprising, an electric power supply, a conductive, stationary guide operatively connected to the power supply and forming a flowpath for current from the power supply, and a non-conductive projectile disposed adjacent to the guide and which is accelerated along the guide when current flows through the guide. The guide includes a plurality of conductive rails disposed in spaced, substantially parallel relation to each other, a plurality of conductive rungs interconnecting the rails and disposed in spaced relation to each other along the rails, and normally-open switches operatively associated with the rungs for selectively permitting current flow through different ones of the rungs. The projectile includes a main body and a magnet supported by the main body such that the magnet faces the guide with a small gap therebetween. The switches are passively activated only when they are disposed within a magnetic field of the projectile, such that the switches are sequentially activated as the projectile moves along the guide and create an electromagnetic pushing Lorentz force which continuously accelerates the projectile along the guide substantially in a direction parallel to the guide.

The disrupter (16) includes an elongated hollow barrel (18) having a cylindrical inner chamber (20), a closed rear (26) end and an opened front end (22), the latter closed with a front frangible seal (38). A channel member (46) partly surrounds an intermediate portion of the barrel, and is securely attached thereto. A pair of recoil channels (76, 78) extend from the barrel inner chamber, radially outwardly and rearwardly through the barrel and the channel member, and are linked to rearwardly oriented recoil tubes (52, 54) which have opened rear end portions (60, 62) closed with rear frangible seals (64, 66). In use, a cartridge (90) including an explosive charge (88) is to be inserted in the barrel inner chamber at its rear end, and the barrel, recoil channels and recoil tubes (52, 54) are to be filled with water. The frangible seals (38, 64, 66) prevent the water from leaking out of the disrupter while it is positioned near a bomb to be deactivated. A trigger (36) is linked to the disrupter, and more particularly to the cartridge, to remotely detonate the explosive charge. Upon the explosive charge being detonated, a portion of the water is propelled and ejected at high velocity out through the barrel front end, rupturing the front frangible seal, to puncture the bomb outer shell and deactivate the bomb inner detonating components. Another portion of the water is redirected through the side recoil channels and recoil tubes, rupturing the rear frangible seals, to be ejected rearwardly out of the disrupter. The recoil created by the detonation of the explosive charge which ejects the water through the barrel front end, is at least partially counteracted by the water being laterally and rearwardly redirected to be ejected rearwardly out through the recoil tubes. The recoil tubes have at their rear ends (60, 62) transverse blades (73, 74) for wide angle dispersal of the fluid jet being ejected rearwardly.

A double-barreled bullpup pump-action shotgun has a frame with two forward-extending barrels arranged side-by-side, a pair of tube magazines, each positioned beneath a respective barrel, an action attached to the frame and operable to load ammunition from the tube magazines to the barrels, and a trigger assembly attached to the frame, the action being located at least in part behind the trigger assembly, and the trigger assembly including a trigger linkage to connect the trigger assembly to the action and to operate the hammers behind the bolts. The action may be a pump action. The trigger assembly may include a plurality of hammer trips, each having a sloped forward surface. The trigger assembly may include a plurality of sears having tails, and the sloped surfaces of the hammer trips may lift the tails of the sears during a portion of a complete cycle of the action.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

An electronically controlled multi-pulse ignitor ignites a cartridge used to launch a projectile. An electronics module is programmed with a temperature performance profile for the cartridge. A temperature sensor is coupled to supply current cartridge temperature data to the electronics module. A first event ignitor is coupled to the electronics module and initiates a ballistic cycle upon command from the electronics module. A translation mechanism, including a first charge coupled to the first event ignitor, moves the projectile forward to increase the free volume in the cartridge. A second event ignitor, coupled to receive a second event ignition signal from the electronics module, ignites the main propellant charge on receiving the second event ignition signal from the electronics module, where the timing of ignition of the second event ignitor is determined by the temperature performance profile and the current cartridge temperature data.

A vehicle for launching from a gas gun having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

A projectile deployment system includes an entangling projectile including a pair of pellets and a tether connecting the pellets. A projectile casing includes a pair of sockets, each socket sized to carry one of the pair of pellets and a selectively activatable pressure source, carried by the projectile casing. The pressure source is capable of expelling the entangling projectile from the projectile casing toward a subject. A launcher carries an activator operable to activate the pressure source to expel the entangling projectile from the projectile casing toward the subject. The projectile casing is removably engageable with the launcher to allow removal of the projectile casing from the launcher after expulsion of the entangling projectile from the projectile casing.

A linear induction generator for use in a weapon system comprising a matrix of coils, a matrix of magnets, a spindle assembly, a matrix of coils, and a dust cover there over. This generator is mounted onto a weapon receiver of the weapon system to generate raw electric current. The raw current is then rectified and delivered to either a battery or directly to the electronic devices.

A housing (1; 100, 104, 102) of a cartridge for a device for firing a projectile has separate first and second chambers (10, 12; 106, 114), each of which contains a respective charge (34, 36; 108, 110, 116, 120) of propellant material. Gas produced by the detonation of one of the charges exits the first chamber to propel the projectile, whilst gas from the detonation of the second charge exist rearwardly from the device so as to counteract recoil. A one way valve may also be provided to help to achieve a high pressure difference between the chambers, where the cartridge has a common igniter assembly.

One embodiment of a projectile propulsion method and apparatus comprising a combustion chamber means and valve means enabling cartridge-free projectile propulsion. The embodiment may be implemented with selective-fire and/or variable velocity projectiles. The embodiment employs liquid and/or gaseous propellants which can be injected into the device and combusted to provide the necessary pressures for propelling a projectile. Some variations and alternatives are described.

The launching of an unmanned projectile includes pre-packaging a barrel with a projectile, a pusher cup, and a gas generator. The gas generator generates gas to propel the projectile out of the barrel. A pressure chamber increases a pressure of the gas in the barrel. The pressure chamber comprises a front body portion connected to the gas generator; an aft body portion connected to the front body portion and the gas generator; and a vent sleeve positioned around the front body portion and adapted to provide an aperture through which the gas exits the barrel in order to control a level of gas pressure in the barrel. A triggering of the gas generator causes the pusher cup to push the projectile out of the barrel at a predetermined launch velocity in order to attain a predetermined self-propelled flight trajectory, wherein the triggering causes the pusher cup to exit the barrel.

The closure of a blowback operated weapon is augmented by a gas cylinder and piston. The piston is self centering.