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公开(公告)号：US10677574B2
公开(公告)日：2020-06-09
申请号：US15583536
申请日：2017-05-01
摘要： The present disclosure provides a projectile with a self-contained internal chamber. Reaction of propellant inside the internal chamber can generate high pressure and the resultant exhaust gases can be used for projectile linear acceleration, rotational acceleration or other purposes. Torque can be produced by exhausting the pressure via radially placed, tangential nozzles or other outlets and can be configured to induce sufficient projectile spin to stabilize the projectile without the need for barrel rifling. The internal chamber may be separate or integral to the projectile itself. The projectile may include two or more chambers or compartments internal to the chambers. The disclosed projectile allows for higher pressures in the internal chamber than in the barrel and greater flexibility on pressure manipulation in the barrel and the projectile, allowing for a more efficient propellant combustion and manipulation of projectile characteristics such as muzzle and rotational speeds.
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公开(公告)号：US10591263B2
公开(公告)日：2020-03-17
申请号：US15852968
申请日：2017-12-22
申请人： James F. Brown
发明人： James F. Brown , Thomas Ott
IPC分类号： F42B10/28 , F42B10/02 , B33Y80/00 , B22F5/10 , B22F3/105 , B22F3/10 , F42B14/06 , F42B10/26 , B33Y10/00 , F42B33/00 , F42B10/22 , B22F5/00 , F42B30/02 , F42B10/24 , F42B10/30 , F42B15/00 , F42B12/74 , B22F5/04 , C22C32/00 , B33Y70/00 , B22F1/00
摘要： A method of making a projectile apparatus is provided that includes making one or components of the apparatus using an additive manufacture technique such as 3-D printing or laser-aided additive manufacture. The projectile apparatus can have a projectile, a propellant, and one or more optional components such as a wading, a sabot, and an intermediary device. The projectile can be fired through a barrel having a smooth bore. Additive manufacture methods can be used that involve forming components from superalloys having nanoparticles incorporated therein. The projectile apparatus can convert gas pressure or gas velocity into a high rate of projectile spin. The projectile has long-range accuracy due to a high or sustainable velocity and high rate of spin.
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公开(公告)号：US10094643B2
公开(公告)日：2018-10-09
申请号：US14897227
申请日：2014-07-01
发明人： Benjamin Levy , Shmuel Goldberg
摘要： The presently disclosed subject matter includes a method, apparatus and computer storage device for reducing dispersion of a rocket caused by jet-stream misalignment, the rocket comprising a rocket engine. Information indicative of a division of total operation time of the rocket engine into a first time period and a second time period is obtained; wherein an impulse which is generated during the first time period is at least approximately the same as an impulse generated during the second time period; a period of time which equals to the first time period starting from time of activation of the rocket engine is measured; upon termination of the period of time, the rocket is rotated around the rocket's longitudinal axis; and the angle of rotation measured; and the rotation is stopped once a 180° rotation is completed.
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公开(公告)号：US09593922B2
公开(公告)日：2017-03-14
申请号：US13828314
申请日：2013-03-14
摘要： A projectile having a fin deployment system disposed about its circumference. The fins are initially contained by a fin cover that is removed by aerodynamic force. The fins are then rotated around a rotational axis parallel to and offset from the central axial axis of the projectile body by the centrifugal forces created by the rotation of the projectile as the projectile passes through a barrel of a gun system or tube launcher. The fin deployment system can also have locking systems that lock the fins in the deployed position and prevent the fins from rotating back into the retracted position after deployment.
摘要翻译： 具有围绕其圆周布置的翅片展开系统的抛射体。 翅片最初由翅片盖包含，其通过空气动力力去除。 然后，当弹丸穿过枪系统或管发射器的枪管时，通过由弹丸的旋转产生的离心力，翅片绕着平行于射弹体的中心轴线的旋转轴线旋转。 翅片展开系统还可以具有将翅片锁定在展开位置的锁定系统，并且防止翅片在展开之后回到缩回位置。
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公开(公告)号：US5996502A
公开(公告)日：1999-12-07
申请号：US863399
申请日：1997-05-27
摘要： An aerodynamically stable, kinematic flare having an enhanced plume signature is disclosed. The flare includes a housing with a flare illuminant disposed within the housing. A primary nozzle is configured in the aft wall of the housing. Four secondary nozzles are configured in the aft end of the side wall of the housing and are positioned aft of the center of gravity of the flare. At least two of the secondary nozzles comprise off-center nozzles having a longitudinal axis which does not extend through the longitudinal axis of the flare. A shroud is attached to the housing and deploys to an extended position upon combustion of the illuminant. The shroud is configured with holes which correspond in size and position to each of the secondary nozzles when the shroud is in its extended position. The primary and secondary nozzles are sized and positioned to spin stabilize the flare during combustion of the illuminant.
摘要翻译： 公开了具有增强的羽流签名的空气动力学稳定的运动火炬。 火炬包括具有设置在壳体内的耀斑光源的壳体。 主喷嘴配置在壳体的后壁上。 四个二次喷嘴构造在壳体的侧壁的后端，并且位于火炬重心的后方。 至少两个次级喷嘴包括偏心中心喷嘴，其具有不延伸穿过火炬的纵向轴线的纵向轴线。 护罩附接到壳体并且在发光体燃烧时展开到延伸位置。 当护罩处于其延伸位置时，护罩被配置有在尺寸和位置上对应于每个次级喷嘴的孔。 主喷嘴和次喷嘴的尺寸和位置可以在发光体的燃烧期间旋转稳定火炬。
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公开(公告)号：US4232843A
公开(公告)日：1980-11-11
申请号：US891924
申请日：1978-03-30
申请人： Michael N. Clark , Donald L. Smith
发明人： Michael N. Clark , Donald L. Smith
CPC分类号： F02K9/974 , F42B10/16 , F42B10/30 , Y10S239/19
摘要： A lightweight, relatively inexpensive rocket nozzle assembly which is heat resistant, ablative and electrically insulating. The body of the nozzle is molded in fibre reinforced thermosetting resin integrally with a forward metallic retaining ring, a rear metallic fin supporting ring and an electrical contact ring. A graphite throat insert is also provided and helical vanes are integrally molded into the rear portion of the nozzle to effect rotary motion of the exhaust gases. Wrap around fins are secured externally of the nozzle and provided with a retainer ring-shear pin assembly to hold the fins in the closed position for transport, and spring means to deploy the fins after firing and shearing of the shear pins.
摘要翻译： 轻质，相对便宜的火箭喷嘴组件，其耐热，烧蚀和电绝缘。 喷嘴的主体与前金属保持环，后金属片支撑环和电接触环一体模制在纤维增强热固性树脂中。 还提供石墨喉部插入件，并且螺旋叶片一体地模制在喷嘴的后部中以实现废气的旋转运动。 翅片周围被固定在喷嘴的外部，并设置有保持器环 - 剪切销组件，以将翅片保持在关闭位置以进行运输;以及弹簧装置，用于在切割和剪切剪切销之后展开翅片。
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公开(公告)号：US3843075A
公开(公告)日：1974-10-22
申请号：US36901773
申请日：1973-06-11
发明人： WEBER T , YOKOMIZO C
摘要： A control system which adjusts the angle of fins on an aerodynamic body proportional to fluid displaced by sensing masses subjected to centrifugal forces generated by the spin of the body. The displaced fluid controls the rotation of one or more fins and is interconnected between sensing masses to provide for synchronized and uniform movement within the system.
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公开(公告)号：US3690596A
公开(公告)日：1972-09-12
申请号：US3690596D
申请日：1969-05-02
申请人： US AIR FORCE
发明人： DURRAN DONALD A , PLATUS DANIEL H
CPC分类号： F42B10/30
摘要： A spin control system for a reentry vehicle has a plurality of fins located around the periphery of the vehicle. The fins are rotated by a mass which moves under the action of centrifugal force to move a pair of pins in cam slots located on the fin support shafts to thereby rotate the fins to decrease the cant angle from a preset value at zero roll.
摘要翻译： 用于再入式车辆的旋转控制系统具有位于车辆周边周围的多个翅片。 翼片由离心力作用下移动的质量块旋转，以使位于翅片支撑轴上的凸轮槽中的一对销移动，从而使翅片旋转，从而将倾斜角度从零卷起的预设值减小。
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公开(公告)号：US3333790A
公开(公告)日：1967-08-01
申请号：US41667964
申请日：1964-12-02
申请人： GEN DYNAMICS CORP
发明人： DURAND JR CHARLES C
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