子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Fragmentation-beam tank projectile | US14360939 | 2012-08-09 | US09016204B2 | 2015-04-28 | Vladimir Alekseevich Odintsov |
| This invention relates to fragmentation-beam ammunition capable of simultaneous axial and circular field destruction.The objects of this invention are providing a variable configuration axial field of the fabricated destructive elements for the reliable destruction of different types of tank threatening targets and providing for the complete destruction of the fragmentation unit following explosive charge detonation in the projectile.The technical solution according to this invention, the projectile comprises an elongated explosive charge with a detonator in the form of a rotation body with a curvilinear generatrix located coaxially with the fragmentation unit wherein said detonator is electrically connected with the fuse and said fuse comprises a device (an adapter booster) for varying the time interval between the activation of both detonators depending on the setting, said detonators comprising safety devices. | ||||||
| 82 | TACTIcal MISSILE AND BALANCE WEIGHT FOR SAID MISSILE | US14384836 | 2013-03-18 | US20150041582A1 | 2015-02-12 | Patrick Barthelemy; Phillippe Dubois; Laurent Carton; Nicholas Sibillaud; Marc Ferrat; Frederic Paintendre |
| According to the invention, the balance weights of the missile are made from pellets whereof the particle size is at most equal to 1 mm which is enclosed in a closed package. | ||||||
| 83 | LAUNCH VEHICLES WITH RING-SHAPED EXTERNAL ELEMENTS, AND ASSOCIATED SYSTEMS AND METHODS | US13833985 | 2013-03-15 | US20140263841A1 | 2014-09-18 | Mark Featherstone; John Michael Sanders; Roger E. Ramsey; Eric David Wetzel |
| Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent. | ||||||
| 84 | Projectile navigation enhancement method | US12325352 | 2008-12-01 | US08519313B2 | 2013-08-27 | Chris E. Geswender; Paul Vesty; Charles Scarborough |
| A projectile, such as a missile, rolls during at least a portion of its flight, while retaining its roll reference to enable navigation during the rolling period of flight. The roll reference may be retained by using a sensor, such as magnetometer, to periodically check and correct the roll reference. Alternatively or in addition the missile may alternate roll directions, for example varying roll rate in a substantially sinusoidal function. By rolling the missile inaccuracies in an inertial measurement unit (IMU) of the missile may be ameliorated by being to a large extent canceled out by the changes in orientation of the missile as the missile rolls. This enables use of IMUs with lower accuracy than would otherwise be required to obtain accurate flight. Thus accurate flight may be accomplished with less costly IMUs, without sacrificing the ability to navigate. | ||||||
| 85 | Multi-caliber fuze kit and methods for same | US12469443 | 2009-05-20 | US08513581B2 | 2013-08-20 | Chris E. Geswender; Cesar Sanchez; Matthew A. Zamora |
| A multi-caliber fuze kit includes a fuze housing configured for coupling with multiple projectiles. One or more canards are moveably coupled with the fuze housing. The one or more canards are adjustable between two or more canard configurations. In a first canard configuration, the one or more canards are at a first canard angle relative to a bore sight of the fuze housing, and the first canard angle is configured for use with a first projectile. In a second canard configuration, the one or more canards are at a second canard angle relative to the bore sight of the fuze housing, and the second canard angle is configured for use with a second projectile. The first and second canard angles are different. In another example, in the first canard configuration the one or more canards include a first canard shape configured to provide a first specified trajectory with the first projectile. In the second canard configuration the one or more canards include a second canard shape configured to provide a second specified trajectory with the second projectile. The first canard shape and the second canard shape are different. | ||||||
| 86 | Drag effect trajectory enhanced projectile | US12784664 | 2010-05-21 | US08307766B2 | 2012-11-13 | PJ Marx |
| A projectile includes a cartridge and a hollow bullet. A propellant fills the cartridge and the hollow bullet to increase the velocity of the bullet when fired. The hollow bullet has a flattened leading end and an annular ring is secured to the flattened leading end in the center of the flat region. The flattened leading end and the annular ring move a center of pressure forwardly so that a center of pressure is forward of a center of gravity of the bullet when the bullet is in flight. In a second embodiment, a plurality of circumferentially spaced apart slits is formed in a trailing end of the hollow bullet, creating a plurality of circumferentially spaced apart fins that flare radially outwardly upon impact with a soft target. | ||||||
| 87 | Low lethality impact payload delivery sub-munitions and methods of manufacture | US12181432 | 2008-07-29 | US08020492B1 | 2011-09-20 | John A. Kapeles |
| A low lethality impact sub-munition and method of making same, the sub-munition including a closed compartment containing a concentration of payload material in close proximity to the forward end of the compartment and a charge of ballast material rearward of the payload material. At least the forward end of the compartment is sufficiently porous that at least some of the payload material will disperse through the forward end but not the ballast material upon impact of the sub-munition with a target. | ||||||
| 88 | WARHEAD | US12602460 | 2008-05-15 | US20100192797A1 | 2010-08-05 | Wolfgang Seidel; Michael Schwenzer |
| The invention relates to a warhead (10) for attacking particularly half-hard and/or soft targets, wherein the warhead comprises a splinter-forming casing (1) and an explosive material positioned in the casing (1). The warhead (10) further has a front plate (2) having a splinter formation, into which a distance sensor (3) is integrated. An igniter (5) for the explosive material and a stabilizing strap for adjusting perpendicular flight characteristics on the way to the target are located in the rear part of the warhead (10), wherein the initiation of the igniter (5) is determined by a property of the target to be attacked, namely, the parameter of a defined height from the target. | ||||||
| 89 | PROJECTILE NAVIGATION ENHANCEMENT METHOD | US12325352 | 2008-12-01 | US20100133374A1 | 2010-06-03 | Chris E. Geswender; Paul Vesty; Charles Scarborough |
| A projectile, such as a missile, rolls during at least a portion of its flight, while retaining its roll reference to enable navigation during the rolling period of flight. The roll reference may be retained by using a sensor, such as magnetometer, to periodically check and correct the roll reference. Alternatively or in addition the missile may alternate roll directions, for example varying roll rate in a substantially sinusoidal function. By rolling the missile inaccuracies in an inertial measurement unit (IMU) of the missile may be ameliorated by being to a large extent canceled out by the changes in orientation of the missile as the missile rolls. This enables use of IMUs with lower accuracy than would otherwise be required to obtain accurate flight. Thus accurate flight may be accomplished with less costly IMUs, without sacrificing the ability to navigate. | ||||||
| 90 | Ring airfoil style paintball and launcher | US11271052 | 2005-11-09 | US07500434B2 | 2009-03-10 | Abraham Flatau; Chester F. Vanek |
| A ring airfoil style paintball comprises a ring airfoil carrying a visible marking agent. The marking agent is located in one more compartments in a nose portion of a body of the ring airfoil, or within one or more containers located in those compartments. The nose portion of the body of the airfoil is configured to rupture upon impacting a target, releasing the marking agent into contact with the target. Cartridges comprising a sabot containing the ring airfoil style paintball are launched from a launcher. The launcher includes a magazine for sequentially delivering cartridges for launch. A stripper associated with the launcher strips the sabot from the ring airfoil paintball, and an ejector ejects the stripped sabot from the launcher. | ||||||
| 91 | Kinetic energy penetrator and method of using same | US11231679 | 2005-09-21 | US07437996B2 | 2008-10-21 | Mark A. Turner; William R. Greisser |
| A kinetic energy penetrator includes a plurality of penetrator segments, a penetrator segment sleeve for storing the plurality of penetrator segments, and means for moving the plurality of penetrator segments from the penetrator segment sleeve to locations substantially aligned along an axis of attack. A method includes storing a plurality of penetrator segments away from an axis of attack and moving the plurality of penetrator segments to locations substantially aligned along the axis of attack. A vehicle includes a body and a kinetic energy penetrator disposed in a forward portion of the vehicle. The kinetic energy penetrator includes a plurality of penetrator segments, a penetrator segment sleeve for storing the plurality of penetrator segments, and means for moving the plurality of penetrator segments from the penetrator segment sleeve to locations substantially aligned along an axis of attack. | ||||||
| 92 | Telescoped projectile | US11204575 | 2005-08-16 | US07380504B2 | 2008-06-03 | Richard Dryer |
| A projectile reconfigures in flight from a launch configuration, in which the center of gravity is aft of the center of pressure, to a flight configuration, in which the center of gravity is forward of the center of pressure. The projectile includes a forward portion and an aft portion, and the reconfiguration involves movement of at least part of one of the portions relative to the other portion. The projectile may have an overall substantially conical shape when in the launch configuration. The forward portion may include a substantially conical nose, and a cylindrical central body attached to the nose. In the launch configuration, at least part of the central body may be located within a hollow in a base of the aft portion. The base may be slidable relative to the central body. | ||||||
| 93 | Non-lethal ammunition projectile | US11652149 | 2007-01-11 | US07337725B2 | 2008-03-04 | Carlos Frederico Queiroz de Aguiar |
| The present invention relates to a projectile (1) for non-lethal ammunition of a body that is composed of a first portion (2) and a second portion (4). Said first portion (2) has a larger mass that the second portion (4), so as to increase the stability of the projectile (1). In addition, the projectile (1) has a strangulation (5) that connects the first portion (2) to the second portion, wherein the first portion (2) is formed by two rings (3), and the two rings (3) are interconnected by an annular groove (6), and wherein the end opposite the strangulation (50 of the second portion (4) has an annular base (7). | ||||||
| 94 | Ring airfoil style paintball and launcher | US11271052 | 2005-11-09 | US20060096492A1 | 2006-05-11 | Abraham Flatau; Chester Vanek |
| A ring airfoil style paintball comprises a ring airfoil carrying a visible marking agent. The marking agent is located in one more compartments in a nose portion of a body of the ring airfoil, or within one or more containers located in those compartments. The nose portion of the body of the airfoil is configured to rupture upon impacting a target, releasing the marking agent into contact with the target. Cartridges comprising a sabot containing the ring airfoil style paintball are launched from a launcher. The launcher includes a magazine for sequentially delivering cartridges for launch. A stripper associated with the launcher strips the sabot from the ring airfoil paintball, and an ejector ejects the stripped sabot from the launcher. | ||||||
| 95 | Penetrator and method for using same | US10251468 | 2002-09-20 | US06843179B2 | 2005-01-18 | David L. Hunn; Johnny E. Banks; Carlton B. Cowan |
| A penetrator includes a fore body comprising a pin and having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion comprising a material of lower density than that of the fore body and a plurality of outwardly extending fins for improving an aerodynamic stability of the projectile and defining a bore in which the pin is received for removably attaching the fore body thereto such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator. | ||||||
| 96 | Projectile for rapid fire gun | US10270812 | 2002-10-15 | US20040069173A1 | 2004-04-15 | Mark Key |
| An ammunition system for a rapid fire gun. The ammunition system includes a bullet having a tip that is stored in a retracted position and during flight is deployed to create an aerodynamic shape. Another aspect of the ammunition system is that the bullet has a cylindrical body having a first length in storage and a second longer length after ignition of the propellant. | ||||||
| 97 | Penetrator and method for using same | US10251423 | 2002-09-20 | US20040055501A1 | 2004-03-25 | David L. Hunn; Johnny E. Banks; Carlton B. Cowan |
| A penetrator includes a fore body having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion removably attached to the fore body such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator. A method of using a penetrator includes propelling the penetrator toward a first target, penetrating the first target with a fore body of the penetrator, and detaching a stabilizing portion of the penetrator from the fore body. The method further includes impacting the second target with the fore body. | ||||||
| 98 | Configurable aerial vehicle aerosurface | US09496138 | 2000-02-01 | US06286789B1 | 2001-09-11 | Ralph Shimovetz |
| A configurable aerial vehicle aerosurface is disclosed, The configurable aerial vehicle aerosurface includes first and second airfoil surfaces in sliding engagement. A plurality of apertures pass transversely through the airfoil surfaces and are disposed in such a relationship so as to define a first position wherein the apertures are in substantial alignment and a second position wherein the apertures are in substantial non-alignment. In this way, the configurable aerial vehicle aerosurface of the present invention can be configured from a first, low drag transport position, to a second, aerodynamic position to provide missile lift and control. | ||||||
| 99 | Method for autonomous guidance of a spin-stabilized artillery projectile and autonomously guided artillery projectile for realizing this method | US156042 | 1998-09-07 | US6135387A | 2000-10-24 | Wolfgang Seidel; Frank Guischard |
| A method for the autonomous guidance of a spin-stabilized artillery projectile (2; 25) toward a target (12). To ensure that an autonomously guided, spin-stabilized artillery projectile (2; 25) hits a target (12) with high precision, even at distances of .gtoreq.35 km, previously determined target data are transmitted to the projectile (2; 25) and stored therein before it is fired, and, following the firing of the projectile (2; 25), these stored data are compared with projectile position data, detected with the aid of a satellite navigational receiving station (23). The correction data resulting from this comparison are then used for the projectile (2; 25) guidance. Shortly before reaching the guidance phase, the velocity of the projectile is reduced by the use of spin-stabilized brakes and the projectile flight is changed for purposes of guidance from a spin-stabilized to a fin-stabilized flight state, wherein the projectile (2; 25) is then guided aerodynamically by means of rotating fins (9), arranged on the nose side, which can swing out, and wherein the spin-stabilized brakes function as lift surfaces once they are locked in place. | ||||||
| 100 | Anti tip-off device | US941930 | 1997-09-30 | US5902952A | 1999-05-11 | Thomas A. DelGuidice; Fred W. Watson, Jr. |
| An anti tip-off device for rocket rockets adapted for collapsible tube-inbe launchers is provided. The dual-diameter launch tube requires stabilization of the rocket within the larger diameter tube. The anti tip-off device has two segments which together form a hollow cylinder which fits over the nose section of a standard high explosive anti-armor rocket. A sliding surface is located around the circumference of the cylinder to provide support for the rocket during transit of the larger launch tube. The surface contact prevents the rocket from wobbling or tipping during the rocket's transit of the launch tube. Alternately, permanently-bonded stabilizer legs or a bonded ring may be attached to the rocket to match the diameter of the larger launch tube. The anti tip-off device may be fabricated using any material suited to the launcher and rocket combination, including lexan, teflon, nylon, wood, or aluminum. | ||||||
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