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1. 发明授权

US12123688B2 Penetrator, use of a penetrator, and projectile 有权
公开(公告)号：US12123688B2
公开(公告)日：2024-10-22
申请号：US18163468
申请日：2023-02-02
申请人： Rheinmetall Waffe Munition GmbH
发明人： Ulrich Keller , Konstantin Arzt , Michael Gowin , Martin Berg , Jan-Erik Melskotte
IPC分类号： F42B14/06 , F42B10/04 , F42B12/06
CPC分类号： F42B12/06 , F42B10/04 , F42B14/06
摘要： The invention relates to a penetrator (1) for a projectile having a tail unit, in particular a subcaliber kinetic energy projectile, comprising a main body (10), the main body (10) having at least one partial region (12, 12′, 12″) with longitudinal recesses (20, 20, 20″).

2. 发明申请

US20220236040A1 Archery Vane 有权
公开(公告)号：US20220236040A1
公开(公告)日：2022-07-28
申请号：US17581396
申请日：2022-01-21
申请人： Kyle Davidson
发明人： Kyle Davidson
IPC分类号： F42B6/06 , F42B10/04
摘要： An aerodynamic element (often referred to as a vane or fletching) that is operatively coupled to the nock end (the back) of an arrow that adds significant stability associated with vanes of similar height (referred to as “high profile” in the archery community) without the noise (amplitude and frequency) commonly associated with such vanes while also providing low drag characteristics. The vane has an initial front or leading edge at a shallow initial angle relative to the axis of the arrow. When the vane is mounted at an angle (known as offset or helical) to the axis of the arrow, this front shallow initial angle (and area under it) is utilized as a vortex generator. This vortex mixes and therefore helps balance velocities in the lower pressure, large aft area which is initiated at a point along the leading edge that increases to a steeper angle relative to the initial angle. The top of the vane is parallel to the axis of the arrow for stability as well as sound advantages. The back edge of the vane then angles down at a steep angle in a straight line to help with noise as well as control airflow.

3. 发明申请

US20220107163A1 AMMUNITION CARTRIDGE 有权
公开(公告)号：US20220107163A1
公开(公告)日：2022-04-07
申请号：US17474877
申请日：2021-09-14
申请人： Albert Gaide
发明人： Albert Gaide
IPC分类号： F42B5/16 , F42B5/10 , F42B5/285 , F42B10/04 , F42C19/08
摘要： Ammunition cartridge comprising a rigid casing including a tubular sleeve and a base closing an end of the casing, a projectile mounted at another end of the casing, a propellant charge contained inside the casing, and an ignition device. The ignition device comprises an ignition charge arranged to ignite the propellant charge at a point of ignition distal from the base and proximal the projectile.

4. 发明授权

US09372055B2 Passive control fin stops for air launched boosted (two stage) high speed vehicles 有权
标题翻译：被动控制翅片停止，用于空中升压（两级）高速车辆
公开(公告)号：US09372055B2
公开(公告)日：2016-06-21
申请号：US14170143
申请日：2014-01-31
申请人： The Boeing Company
发明人： Ben YoungSon Won , Marvin Luke , Daniel Madrid Ortega , Creed E. Blevins
IPC分类号： F42B10/06 , F42B10/04 , F42B10/64
CPC分类号： F42B10/06 , F42B10/04 , F42B10/64 , Y10T29/49826
摘要： A temporary control fin stop system employs a housing coupled to a vehicle. At least one tang is coupled to the housing and positioned to engage a trailing edge of a fin. The tang is ablatively erodible at a predetermined temperature induced by a flight profile of the vehicle to allow unconstrained motion of the fin.
摘要翻译：临时控制翅片止动系统采用耦合到车辆的壳体。至少一个脚连接到壳体并且定位成接合翅片的后缘。在由车辆的飞行剖面引起的预定温度下，脚可以被腐蚀，以允许翅片的无约束运动。

5. 发明申请

US20050056723A1 FIXED CANARD 2-D GUIDANCE OF ARTILLERY PROJECTILES 有权
标题翻译：固定的CANARD二维指南的ARTILLERY PROJECTILES
公开(公告)号：US20050056723A1
公开(公告)日：2005-03-17
申请号：US10664223
申请日：2003-09-17
申请人： John Clancy , Thomas Bybee , William Friedrich
发明人： John Clancy , Thomas Bybee , William Friedrich
IPC分类号： F42B10/04 , F42B10/64 , F42B10/00 , F41G7/00 , F41G9/00
CPC分类号： F42B10/04 , F42B10/64
摘要： Applicants have invented a guidance system for guiding a projectile, the projectile having a body portion capable of being spun in a first direction and a nose portion connected to the body portion by a spin control coupling, the nose portion being capable of being spun in a second direction. The nose portion including first and second aerodynamic surfaces fixedly attached to the nose portion and configured and arranged to cause the nose portion to spin in a second direction during projectile flight. The nose portion including third and fourth aerodynamic surfaces fixedly attached to the nose portion, which are configured and arranged such that when the nose portion is spinning the third and fourth aerodynamic surfaces have no net effect on projectile flight, but when the nose portion is despun using the spin control coupling, the third and fourth aerodynamic surfaces induce both a moment and a lateral force to the nose, causing the projectile flight path to change.
摘要翻译：申请人已经发明了一种用于引导射弹的引导系统，所述射弹具有能够沿着第一方向旋转的主体部分和通过旋转控制联接件连接到主体部分的鼻部，所述鼻部能够以第二个方向鼻部包括固定地附接到鼻部部分的第一和第二空气动力学表面，并且被构造和布置成使得在射弹飞行期间鼻部部分沿第二方向旋转。鼻部包括固定在鼻部上的第三和第四空气动力学表面，其被构造和布置成使得当鼻部旋转时，第三和第四空气动力学表面对抛射体飞行没有净效应，但是当鼻部部分被去除时使用旋转控制联轴器，第三和第四空气动力学表面引起了鼻子的瞬间和横向力，导致射弹飞行路径改变。

6. 发明授权

US5328130A Stabilizer for a cannon projectile 失效
标题翻译：大炮射弹的稳定器
公开(公告)号：US5328130A
公开(公告)日：1994-07-12
申请号：US32
申请日：1993-01-04
申请人： Stewart Gilman , Anthony Farina
发明人： Stewart Gilman , Anthony Farina
IPC分类号： F42B20060101 , F42B10/04 , F42B10/26
CPC分类号： F42B10/26 , F42B10/04
摘要： A cylindrical device connected to the nose of a projectile for imparting n to the projectile fired from a non-rifled bore of a cannon. The device has at least two coaxial, adjacent, and integrally connected cylindrical segments of different diameter. The segment having the larger diameter is positioned most rearwardly of the projectile, relative to the nose of the projectile, and the periphery of this segment has circumferentially spaced angled slots for catching air moving past the projectile to spin the projectile. The segment with the smaller diameter attaches the cylindrical device to the aft end of the nose of the projectile and directs the flow of air to and through the angled slots of the segment having the larger diameter.
摘要翻译：连接到射弹的鼻子的圆柱形装置，用于从炮的非膛孔射出的射弹旋转。该装置具有不同直径的至少两个同轴，相邻和一体连接的圆柱形段。具有较大直径的段相对于射弹的鼻部位于抛射体的最后面，并且该段的周边具有周向间隔开的成角度的狭槽，用于捕捉通过射弹移动的空气以旋转射弹。具有较小直径的段将圆柱形装置附接到射弹的鼻部的后端，并将空气流引导并穿过具有较大直径的段的成角度的槽。

7. 发明授权

US4327884A Advanced air-to-surface weapon 失效
标题翻译：先进的空对地武器
公开(公告)号：US4327884A
公开(公告)日：1982-05-04
申请号：US114533
申请日：1980-01-23
申请人： William S. Lawhorn
发明人： William S. Lawhorn
IPC分类号： F42B10/04 , F42B15/10 , F41G7/00 , F42B15/02 , F42B15/16
CPC分类号： F42B15/105 , F42B10/04
摘要： An unconventional advanced air-to-surface weapon of monowing configuration, and having a symmetrical, high lift fuselage of lenticular (i.e., biconvex or oblate) cross section, with a width-to-thickness fineness of approximately 2.5. The longitudinal profile is modified Sears-Haack in two dimensions, truncated at the base for a rocket nozzle. The weapon comprises a nose portion modular forebody, a weapon payload portion modular midbody, and an aft boattail modular portion which are combined into one unit that is selectively separable into its modular components when used. A variation of this weapon is also taught which features a semi-lenticular fuselage cross section (i.e., one flat side) and a width-to-thickness fineness of approximately 2.1.
摘要翻译：一种非常规的先进的空对地武器，具有一个对称的，具有大约2.5的宽度 - 厚度细长度的透镜（即双凸面或扁圆形）横截面的对称的高升力机身。纵向轮廓是二维的Sears-Haack修改，在基座处用于火箭喷嘴。该武器包括鼻部模块式前身，武器有效载荷部分模块化中体，以及尾部模糊部分，它们组合成一个单元，当使用时可选择性地分离到其模块化组件中。还教导了这种武器的变型，其特征在于具有半透镜的机身横截面（即，一个平坦侧面）以及宽度至厚度细度为大约2.1。

8. 发明授权

US3939773A Spin-stabilized projectiles 失效
标题翻译：旋转稳定的射弹
公开(公告)号：US3939773A
公开(公告)日：1976-02-24
申请号：US448565
申请日：1974-03-06
申请人： Dennis H. Jenkins , Luis Palacio
发明人： Dennis H. Jenkins , Luis Palacio
IPC分类号： F42B10/04 , F42B13/00
CPC分类号： F42B10/04
摘要： A gun-fired spin-stabilized projectile of good aerodynamic shape (i.e. with a long forward tapering section) is centered in the gun barrel at its forward end by means of a series of circumferentially spaced apart permanently fixed radially extending projections, and at its rearward end, by means of either the maximum diameter of the projectile body or by means of a driving band mounted on a rear portion of the body. In the latter case, the maximum diameter of the projectile body is slightly less than the diameter lands of the gun and the driving band is constructed in such a manner as to be separated from the body after firing by centrifugal force and air drag.
摘要翻译：具有良好空气动力学形状（即，具有长向前锥形部分）的喷枪式自旋稳定的射弹在其前端处通过一系列周向间隔开的永久固定的径向延伸的突起在其枪管中心并且在其后方通过射弹体的最大直径或通过安装在身体的后部上的驱动带来结束。在后一种情况下，射弹体的最大直径略小于枪口的直径，并且驱动带的构造方式是在通过离心力和空气阻力击发之后与身体分离。

9. 发明授权

US11988491B1 Projectile and caseless cartridge 有权
公开(公告)号：US11988491B1
公开(公告)日：2024-05-21
申请号：US17389215
申请日：2021-07-29
申请人： Revolutionary Rounds L.L.C.
发明人： Richard L. Eckstein, Jr. , Linda H. Eckstein , Lucas R. Hayhurst
IPC分类号： F42B5/18 , F42B5/184 , F42B10/04
CPC分类号： F42B5/182 , F42B5/184 , F42B10/04
摘要： A caseless cartridge with a projectile, a propellant, and an ignition source. The ignition source is configured to ignite the propellant in response to an activation of the firearm. The propellant is molded around the projectile and is configured to propel the projectile from the firearm upon ignition. When the firearm is activated, the propellant is consumed, and the projectile and the ignition source are discharged from the firearm. The projectile has a bullet, an ignition housing, and a shaft. The bullet is positioned on a leading end of the projectile, while the ignition housing is positioned on a trailing end opposite the leading end. The shaft extends between the projectile and the ignition housing. The projectile may also have a plurality of fins to stabilize the projectile during flight and a plurality of ignition ports. The ignition source may ignite the propellant through the plurality of ignition ports.

10. 发明公开

US20230204332A1 PENETRATOR, USE OF A PENETRATOR, AND PROJECTILE 审中-公开
公开(公告)号：US20230204332A1
公开(公告)日：2023-06-29
申请号：US18163468
申请日：2023-02-02
申请人： Rheinmetall Waffe Munition GmbH
发明人： Ulrich KELLER , Konstantin Arzt , Michael Gowin , Martin Berg , Jan-Erik Melskotte
IPC分类号： F42B12/06 , F42B10/04 , F42B14/06
CPC分类号： F42B12/06 , F42B10/04 , F42B14/06
摘要： The invention relates to a penetrator (1) for a projectile having a tail unit, in particular a subcaliber kinetic energy projectile, comprising a main body (10), the main body (10) having at least one partial region (12, 12′, 12″) with longitudinal recesses (20, 20′, 20″).

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