| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 102374000 | HAVING REACTION MOTOR | 52 |
| 20080245256 | Flying Object for Observing the Ground - The invention relates to a flying object ( | 10-09-2008 |
| 20080314278 | Penetration Assisting Kit Equipping A Bomb, In Particular Anti-Infrastructure, Penetrating Projectile Equipped With Such A Kit, And Method For Penetrating Into A Target - The present invention relates to a penetration assistance kit fitted to a bomb, notably an anti-infrastructure bomb. The kit includes launch tubes mechanically secured to the bomb. In each of the launch tubes is positioned a detonating projectile and its propulsive charge. A detonating projectile can be ejected from its tube by initiation of its propulsive charge. A system is provided for controlling the initiation of each propulsive charge prior to impact of the bomb with a target. The invention applies notably to the penetration of very thick walls made of non-metallic material such as concrete, for example. The invention also relates to a penetrating projectile equipped with such a kit and to a method of getting such a projectile to penetrate a target. | 12-25-2008 |
| 20110120336 | SABOT PROJECTILE - A sabot projectile with a subcaliber penetrator and a sabot, which has a propulsion element that acts on the rear end of the penetrator, a segmented, essentially cylindrical guide cage, which is connected to the front end of the propulsion element, and a segmented, disk-shaped metal guide element that extends radially inward in the front area of the guide cage and holds the penetrator. The disk-shaped guide element has a slightly convex contour in the direction of flight of the projectile and the material and the wall thickness of the guide element are chosen in such a way that convex area of the guide element is pushed back slightly when the sabot projectile is fired, so that the outer marginal area of the guide element rests against the inside wall of the gun barrel from which the sabot projectile is fired, and/or the inner marginal area of the guide element, which faces the penetrator, rests against the outer surface of the penetrator. | 05-26-2011 |
| 20110259230 | ELECTRODE IGNITION AND CONTROL OF ELECTRICALLY IGNITABLE MATERIALS - 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. | 10-27-2011 |
| 20110308417 | HIGH VELOCITY AMMUNITION ROUND - A sub-caliber bullet with an aerodynamic shape has long-range accuracy due to a high muzzle velocity and reduced time of flight to a target. The bullet has forward and aft portions and a mid-portion. The forward portion has a density in excess of 10/cm | 12-22-2011 |
| 20120006218 | REMOTE SETTING FOR ELECTRONIC SYSTEMS IN A PROJECTILE FOR CHAMBERED AMMUNITION - A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile. | 01-12-2012 |
| 20120079957 | PROJECTILE HAVING CASING THAT INCLUDES MULTIPLE FLACHETTES - Some embodiments pertain to a projectile that includes a propellant and a casing that encloses the propellant such that the casing acts as a reaction chamber during flight of the projectile. The casing includes a plurality of flechettes. When the projectile strikes (or is near) a target, a large internal sheer pressure forms within the casing. This sheer pressure causes the flechettes to sheer apart at the thinnest sections of the casing. Once the thin sections of the casing are sheered apart, the flechettes will be unconstrained such that the flechettes take individual flight paths. | 04-05-2012 |
| 20120152142 | Actuators for Gun-Fired Projectiles and Mortars - A method for providing actuation thrust to a projectile. The method including: providing two or more individual actuators movably disposed in a stack housing, each of the two or more individual actuators being separated by a separation layer; accelerating exhaust from the two or more individual actuators with an accelerating nozzle having at least a convergent section terminating at a throat; and maintaining a constant volume in the accelerating nozzle after actuation of each of the two or more individual actuators. | 06-21-2012 |
| 20120167794 | REMOTE SETTING FOR ELECTRONIC SYSTEMS IN A PROJECTILE FOR CHAMBERED AMMUNITION - A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile. | 07-05-2012 |
| 20120167795 | REMOTE SETTING FOR ELECTRONIC SYSTEMS IN A PROJECTILE FOR CHAMBERED AMMUNITION - A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile. | 07-05-2012 |
| 20120210901 | SELF-SPRUNG STABILIZATION FIN SYSTEM FOR GUN-LAUNCHED ARTILLERY PROJECTILES - A system and process for the aerodynamic stabilization of rocket-assisted artillery projectiles launched from smooth-bore cannons comprises multiple stabilization fins stowed circumferentially and held by a cap until muzzle exit. At muzzle exit, the cap separates and allows the fins to self-deploy using the energy stored within the fin material, which is either shape memory alloy or spring steel. The fins are then locked into place and serve to stabilize the projectile without interfering with the discharge of hot propelling gasses from the rocket nozzle. | 08-23-2012 |
| 20120210902 | MULTIPLE DIVERGING PROJECTILE SYSTEM - A system for firing multiple projectiles in a parallel or diverging manner is provided. The system can comprise tail-end portions of projectiles that add structure to a cartridge, provide for efficient combustion, allow projectiles to transition from a straight configuration in the cartridge to a splayed configuration in a chamber, and ensure complete evacuation of the chamber. The system can include a tail-end portion of a particular projectile with openings that distribute energy from combustion of an ignition charge, facilitating firing of multiple projectiles. A tail-end portion of a projectile can include a ball joint upon which the body portion of the projectile moves causing an angle between the body portion and the tail-end portion. A space can exist in the body portion adjacent to the ball joint to allow off-center shifting of the body portion with respect to the ball joint. | 08-23-2012 |
| 20120234195 | SURFACE SKIMMING MUNITION - A surface skimming munition comprises a hull, a traction propulsion motor positioned in the hull and having a combustion chamber for combustion of a propellant, at least one aft directed nozzle coupled to the hull at a position forward of a center of gravity of the hull and comprising an inlet section and an outlet section, the inlet section in fluid communication with the combustion chamber and the outlet section directing combustion gas received from the combustion chamber through the inlet section in the aft direction, and at least one stabilizing plane coupled to the hull and moveable between a stowed position and a deployed position. | 09-20-2012 |
| 20120234196 | Viscous Liquid Monopropellant - This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomised and then ignited. The atomisation step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidisers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion whilst doing so. | 09-20-2012 |
| 20130055918 | ENERGETIC COMPOSITIONS INCLUDING NITRATE ESTERS, METHODS OF FORMING SUCH ENERGETIC COMPOSITIONS, AND ARTICLES INCLUDING SUCH ENERGETIC COMPOSITIONS - Methods of forming energetic compositions include forming a premix comprising a nitrate ester, a polymer, and a stabilizer, and combining solids with the premix. Additional stabilizer may be added with the solids and may remain in a crystalline state. Some methods include dissolving a stabilizer in at least one of a plurality of nitrate esters. Energetic compositions include a continuous matrix and a stabilizer. The continuous matrix includes a nitrate ester and surrounds a solid energetic material. Some compositions include a first nitrate ester, a second nitrate ester having a decomposition rate lower than the first nitrate ester, and a stabilizer. An article includes a housing and an energetic composition in the housing. | 03-07-2013 |
| 20130112100 | Projectile and munition including projectile - A projectile (and munition including the projectile) and a method of assembling the same, includes a body having a cavity, a propellant disposed in the cavity and a base including an ignition flash column extending into the cavity containing the propellant and a nozzle formed so as to be openable and closeable. | 05-09-2013 |
| 20130112101 | BOMB FOR DEPLOYMENT FROM AN AIR VEHICLE - A bomb for deployment from an air vehicle includes a rocket motor ( | 05-09-2013 |
| 20140060370 | APPARATUS FOR DEPLOYING STOWED CONTROL SURFACES OF A PROJECTILE - An apparatus for deploying stowed control surfaces of a projectile is disclosed. The apparatus for deploying stowed control surfaces of a projectile includes a first and second hot gas generators, a first and second gas chambers, a piston wedge, a piston and a barrel. Initially, the first hot gas generator discharges a surge of hot gas into the first gas chamber. In response to the surge of hot gas being discharged into the first gas generator, the piston wedge displaces at least one of the control surfaces to break an environmental seal covering the projectile. After a predetermined amount of time has lapsed, the second hot gas generator discharges a surge of hot gas into the second gas chamber. The surge of hot gas displaces the piston and barrel for deploying the control surfaces completely. | 03-06-2014 |
| 20140116281 | FLYING OBJECT HAVING ONE BODY WINGS - Disclosed is a flying object in which a covering unit and a wing unit installed in a nozzle assembly are integrally formed to form a smooth outer surface of the flying object, thus minimizing drag, and the covering unit and the nozzle assembly are fastened by using a fastening member having one end fastened to a slit, thereby preventing the flying object from being damaged by thermal deformation. | 05-01-2014 |
| 20140182474 | FRAGMENTATION BODIES, WARHEADS INCLUDING FRAGMENTATION BODIES, AND RELATED ORDNANCE - A fragmentation body comprising a substantially monolithic structure comprising a metal material and comprising a major surface having an indentation pattern therein, and an opposing major surface having an opposing indentation pattern therein, the opposing indentation pattern being substantially aligned with the indentation pattern. A warhead and an article of ordnance are also described. | 07-03-2014 |
| 20140216290 | Projectile-Deployed Countermeasure System - Systems and methods described herein provide for the protection of personnel within vehicles and structures from rocket-propelled grenades and other incoming threats. According to one aspect of the disclosure provided herein, a countermeasure system includes an interceptor vehicle configured to stow and launch an expandable countermeasure. The countermeasure may have a flexible body with attached deployment mechanisms that expand the flexible body into the path of an incoming threat to capture the threat. | 08-07-2014 |
| 20150047526 | ELECTRODE IGNITION AND CONTROL OF ELECTRICALLY IGNITABLE MATERIALS - 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. | 02-19-2015 |
| 20160054109 | Self-Propelled Projectile Having a Fuel-Rich Propellant that Reacts with Water - A system for initiating and controlling a reaction between a metal and water is provided for use in propelling a rocket, torpedo, or other munition. A thermite charge having a quantity of reducing metal in excess of that required to react with the metal oxide is utilized to melt and/or vaporize the excess reducing metal. Water may be added to the munition immediately before use, or in the case of a torpedo, may be taken in from the surrounding water. The principles embodied by Bernoulli's equation may be used to regulate the intake of water for the reaction with the reducing metal. | 02-25-2016 |
| 102376000 | With cartridge means | 5 |
| 20100064925 | ROCKET MOTOR WITH PELLET AND BULK SOLID PROPELLANTS - There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle | 03-18-2010 |
| 20100251920 | CASING FOR INSENSITIVE MUNITIONS AND PROCESS FOR MAKING SAME - An insensitive munitions casing, such as a motor case, for housing a propellant charge is disclosed. The casing is formed by winding, wrapping or rolling a fiber, tape or sheet of material such that the casing has a plurality of reinforcing layers. At least some of the reinforcing layers have discontinuous interfaces. Other reinforcing layers may overlap the discontinuous interfaces. The reinforcing layers are coated with adhesive bonding material for adhering the reinforcing layer to itself and bonding the discontinuous interfaces. The adhesive bonding material has a bond-strength breakdown temperature which is below the auto-ignition temperature of the propellant charge. Once the bond strength breakdown temperature of the adhesive is reached, the bond fails at the discontinuous interface, thereby enabling release of propellant charge pressurization. | 10-07-2010 |
| 20110226149 | LESS-THAN-LETHAL AMMUNITION UTILIZING A SUSTAINER MOTOR - A weapon system and corresponding ammunition for causing less-than-lethal effects to a target employ a projectile fired from a rifle-mounted, rifle-operated or dedicated rifle-like device and configured for generating less-than-lethal effects to a human target. The projectile includes a rocket motor configured to mitigate velocity decay of the projectile. The rocket motor is preferably a sustainer motor for maintaining a roughly constant cruise velocity of the projectile. | 09-22-2011 |
| 20110252995 | CONTROLLED DECELERATION PROJECTILE - The present invention provides a controlled deceleration projectile, in particular, a projectile having a nose-mounted fuze thereon, which initiates an ignition/expulsion charge via an ignition shaft in the interior portion of the projectile body at a preset distance from target impact, resulting in inflation of the projectile body with propellant gases to a level sufficient to either expand same, rupturing of a rupture ring, or sliding of the hollow projectile body rearwards relative to the ignition shaft, so as to create an annular opening between the projectile body side wall and projectile body forward end. The payload, which is preferably non-lethal, is then ejected from this annular opening, the resulting forward velocity of the expelled payload and propellant gases producing a rearward thrust on the projectile, and a concomitant deceleration thereof. Additional means of reverse thrust are also provided, involving the expulsion of rear ballast or rocket thrust from rear chamber ports disposed within the projectile. | 10-20-2011 |
| 20120006219 | REMOTE SETTING FOR ELECTRONIC SYSTEMS IN A PROJECTILE FOR CHAMBERED AMMUNITION - A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile. | 01-12-2012 |
| 102377000 | Having separation means | 14 |
| 20090078145 | System and method for integrated stage separation - A multi-stage vehicle separation system and method that facilitates an active separation on the booster by igniting a small quantity of propellant in the dead volume between the second stage rocket motor nozzle and the booster dome. In the most general embodiment, the invention includes a nozzle; a first fuel propellant disposed within the nozzle; a thermal barrier separating the first and second fuel propellant, an environmental seal protecting the second fuel propellant and an arrangement for activating the first fuel propellant. The nozzle is disposed in an upper stage of a two-stage vehicle. An arrangement such as a V-Band clamp is included for retaining the lower stage of the two-stage vehicle. Electronic commands release the lower stage and activate the first propellant in a timely manner to effectively separate the lower stage from the upper stage. The embedded propellant is activated with an arm fire device. | 03-26-2009 |
| 20090308273 | ACTIVE VORTEX CONTROL SYSTEM (AVOCS) METHOD FOR ISOLATION OF SENSITIVE COMPONENTS FROM EXTERNAL ENVIRONMENTS - An active vortex control system (AVOCS) includes a set of primary injectors that inject gas into a cavity to generate a vortex in front of and possibly around components inside the cavity. The vortex interferes with an external flow field in an opening to the cavity to protect the components from the external environment. Sets of secondary injectors may inject gas at a reduced mass flow into the cavity to compensate for energy losses to maintain the coherence of the vortex. The AVOCS is well suited for use in windowless endo- and exo-atmospheric interceptors to protect the electro-optical imagers and optical components from Earth atmosphere. | 12-17-2009 |
| 20100050897 | MISSILE SEPARATION DEVICE - Disclosed is a device for separating a propulsion system from a missile, the device including a locking unit configured to fix a propulsion system to a missile, a string disposed to cross a rear portion of the propulsion system to be broken by heat of the propulsion system, and an unlocking unit configured to unlock the missile by the broken string, whereby the number of additional components of an unlocking system can be reduced as many as possible so as to simplify the configuration of the apparatus, resulting in guaranteeing an enhanced performance of the missile, an easy assembly of the missile, and a reduction of a fabricating cost. | 03-04-2010 |
| 20100206195 | ACTUATORS FOR GUN-FIRED PROJECTILES AND MORTARS - Projectiles are provided having a shell and; one or more actuators for providing thrust disposed inside of a wall of the shell; one or more ring portions forming at least a portion of the shell, the one or more ring portions having one or more actuators formed therein for providing thrust and/or one or more actuator stacks for providing thrust, the one or more actuator stacks each having two or more individual actuators for providing thrust. | 08-19-2010 |
| 20110192308 | MISSILE HEAD AND METHOD FOR SEPARATING A SHROUD FROM A FUSELAGE OF A MISSILE - A missile head has a shroud which forms its tip and which can be detached in its totality during flight from the fuselage of the missile. The missile head further has a rear part, which is connected to the fuselage, and a front nose, which can be disconnected from the rear part and forms the tip. A separating device separates the rear part from the fuselage and the nose from the rear part during flight. A physically small shroud can be achieved, and damage to the fuselage of the missile by separation of the shroud can be prevented, if the nose is split into at least two parts and the separating device is prepared to split the nose into these two parts during flight. | 08-11-2011 |
| 20120137916 | Device for Hardening a Mechanical Propulsion System Connection for a Mortar Round and Round Comprising Such a Connection - A self-propelled munition having a munition rear body of circular cylindrical shape of diameter D | 06-07-2012 |
| 20120145028 | PROJECTILE THAT INCLUDES PROPULSION SYSTEM AND LAUNCH MOTOR ON OPPOSING SIDES OF PAYLOAD AND METHOD - Projectiles that include a propulsion system and a launch motor which are located on opposing sides of a payload and a method of directing a projectile toward a target are generally described herein. Placing the propulsion system and the launch motor on opposing sides of the payload may provide many potential advantages when designing the projectile. These design advantages may make it easier to create a projectile that includes more propellant and/or payload while still permitting the projectile to be stored within existing containers having a fixed size. | 06-14-2012 |
| 102378000 | Explosive | 7 |
| 20110048267 | SEPARATION DEVICE OF EJECTOR MOTOR FOR PORTABLE MISSILE - Disclosed is a separation device of an ejector motor for a portable missile, capable of being separated from a missile without any additional separation devices after ejecting the missile. An ejection rocket motor and a separation device are integrally formed. Ejection is performed by a thrust generated while the ejection rocket motor is combusted, and separation is performed by cutting off shearing bolts with using a force generated from a separation cylinder when the combustion of the ejection rocket motor has been completed. This operation and configuration may minimize a weight and a space occupied by a general ejection and separation device in a missile system. | 03-03-2011 |
| 20120111218 | DEVICE FOR TEMPORARILY CONNECTING AND PYROTECHNICALLY SEPARATING TWO ASSEMBLIES - Temporary connection and pyrotechnic separation device with a longitudinal axis (X) comprising a pyrotechnic expansion tube ( | 05-10-2012 |
| 20120137917 | LOW SHOCK ROCKET BODY SEPARATION - The present disclosure generally relates a high strength, low weight, and low shock rocket body separating joint for the purpose of joining rocket bodies, and method of assembly thereof The solution combines a radax joint, joined by fasteners, with a flattened bladder and inflation system coupled thereto. Upon activation of the inflation system, the bladder is pressurized and exerts a separating force between the members of the radax joint, overcoming the load carrying capability of the fasteners and breaking apart the radax joint. | 06-07-2012 |
| 20130340644 | REVERSIBLE DETONATING PYROTECHNIC RUPTURE PIECE - According to the invention, this piece comprises: e base section piece ( | 12-26-2013 |
| 20140123867 | DETONATING PYROTECHNIC RUPTURE PIECE - An expansion tube of a detonating pyrotechnic rupture piece is open next to pre-established rupture zones and, inside said open expansion tube there is disposed a sealed bladder which contains a pyrotechnic fuse. | 05-08-2014 |
| 20160169647 | METHOD AND DEVICE FOR CONNECTING AND SEPARATING TWO ELEMENTS, WITH COMBINED CONNECTING AND SEPARATING MEANS | 06-16-2016 |
| 20180023933 | STAGE SEPARATION MECHANISM AND METHOD | 01-25-2018 |
| 102379000 | Having warhead fuse or arming means | 2 |
| 20110120337 | ARTILLERY PROJECTILE WITH SEPERATELY CONTROLLED BOOSTER ACTUATION AND FRAGMENT DISPERSION - An artillery projectile for firing from an artillery gun, mortar or artillery rocket launcher. The artillery projectile includes a body, a payload with a number of inert fragments located within the body, a booster motor associated with the body for accelerating the body with the payload to a penetration velocity, and an opening arrangement associated with the body and deployed for initiating release of the fragments. The artillery projectile further includes a control system causally associated with the booster motor and the opening arrangement. The control system is configured to generate a first command to actuate the booster motor and a second command to actuate the opening arrangement. | 05-26-2011 |
| 20140338554 | Projectile Launching Devices and Methods and Apparatus Using Same - A projectile launching device includes a reactive driver, a flyer housing, a flyer and a compressible buffer member. When detonated, the reactive driver will generate a detonation shock wave. The flyer housing defines a bore. The flyer is disposed in the bore and has a rear surface. The buffer member is interposed between the reactive driver and the flyer. The buffer member has a front surface in direct contact with the rear surface of the flyer. The buffer member is configured and arranged to: receive the detonation shock wave from the reactive driver; modify the detonation shock wave to generate a modified shock wave; and transmit the modified shock wave directly to the flyer to thereby propel the flyer away from the buffer member. | 11-20-2014 |
| 102380000 | Having propellent charge ignitor means | 7 |
| 20090044716 | Slow cook off rocket igniter - A gas generating propulsion system includes an igniter containing an igniter propellant and an auto igniter. A rocket motor is coupled to the igniter and has a housing containing a main propellant, a rocket motor throat and a nozzle. A release port extends through a portion of the rocket motor. This gas release port has a variable diameter through bore in fluid communication with the main propellant. In this way, the through bore has a variable area that forms an unobstructed open area with a cross-section effective to discharge gas generated by the main propellant such that a pressure increase within the housing remains below a safety value for the housing. | 02-19-2009 |
| 20090178585 | Projectile - A projectile ( | 07-16-2009 |
| 20100242772 | NON-CIRCULAR CROSS-SECTION MISSILE COMPONENTS, MISSILES INCORPORATING SAME, AND METHODS OF OPERATION - A missile component such as a rocket motor case, of an initial transverse cross-sectional shape flexible into another, different cross-section responsive to application of internal pressure from ignition of a propellant grain within the component. A missile launch assembly including at least one missile of a non-circular cross-section disposed within a segment of a partitioned circular launch tube. A multi-stage missile comprising at least a first stage and a second stage having rocket motor cases of non-circular transverse cross-section, the rocket motor case of at least one of the stages being deformable into another, different cross-section. A method of launching a missile including igniting a rocket motor of a component having a first cross-section, internally pressurizing the missile component substantially concurrently with motor ignition and flexing the component rocket motor into a second, different cross-sectional shape. | 09-30-2010 |
| 20110162549 | ACTUATORS FOR GUN-FIRED PROJECTILES AND MORTARS - An actuator stack is provided and having two or more individual actuators stacked in a longitudinal direction. Each of the two or more actuators having a solid detonation charge; a primer for igniting the detonation charge; and detonation wiring for powering the primer; and wherein at least one of the two or more individual actuators comprise an accelerating nozzle having at least a convergent section terminating at a throat. | 07-07-2011 |
| 20110179964 | ACTUATORS FOR GUN-FIRED PROJECTILES AND MORTARS - A ring portion including: a ring body; and one or more actuators formed therein for providing thrust to a projectile and configured for fastening to a shell of an airborne device to form a portion of the shell. The airborne device can be a projectile. | 07-28-2011 |
| 20110192309 | Projectile - A projectile ( | 08-11-2011 |
| 20120167796 | Integrated warhead rocket motor - An integrated warhead and rocket motor subassembly. The novel subassembly includes a warhead, a rocket motor, and a single bulkhead separating the warhead and the rocket motor. The bulkhead is adapted to handle both pressure loads from the rocket motor and missile carry loads transmitted through a hook and hangar assembly, which is bolted into the bulkhead. In an illustrative embodiment, the warhead includes an explosive fill surrounded by a material adapted to form a plurality of fragments upon detonation. In a preferred embodiment, the fragments are formed into small cubes that are 80 to 85 grain in weight, using a material having a density greater than 16 g/cc. | 07-05-2012 |
| 102381000 | Having pressurization or variable control means for the propellant | 1 |
| 20120012021 | GUN FIRED PROPELLANT SUPPORT ASSEMBLIES AND METHODS FOR SAME - A gun fired projectile includes a rocket motor housing including a pressure chamber and an exhaust nozzle. A plurality of propellant cells are positioned within the pressure chamber. The rocket motor propellant is mechanically supported during the severe gun fire event. This support may take several forms, each of which is discussed herein. The projectile further includes a support structure including one or more supports: wherein each of the one or more supports is engaged with the rocket motor housing. Each of the one or more supports is engaged with one propellant cell of the plurality of propellant cells, and each of the one or more supports suspends an individual propellant cell from the remainder of the plurality of propellant cells. All of these approaches provide the opportunity to tailor the performance of the rocket motor by combining a combination of propellant formulations and geometries to optimize the projectile performance. | 01-19-2012 |
