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1. 发明申请

US20180245896A1 CAP-BASED HEAT-MITIGATING NOSE INSERT FOR A PROJECTILE AND A PROJECTILE CONTAINING THE SAME 审中-公开
公开(公告)号：US20180245896A1
公开(公告)日：2018-08-30
申请号：US15906440
申请日：2018-02-27
申请人： Sig Sauer, Inc.
发明人： Thomas J. Burczynski
IPC分类号： F42B10/38 , F42B12/78 , F42B12/34
CPC分类号： F42B10/38 , F42B12/34 , F42B12/78
摘要： Techniques and architecture are disclosed for a nose insert for use in a projectile. The nose insert includes a polymer nose element and a metal cap. The polymer nose element includes a rear shank portion and a tapered head portion. Disposed onto the tapered head portion of the polymer nose is the metal cap. The metal includes an outer curved portion that terminates at a forward end in a meplat. In some embodiments, the metal cap prevents deformation of the polymer nose element caused by high stagnation temperatures experienced by the projectile during flight. In some other embodiments, the metal cap includes a locking ridge. The locking ridge is disposed on an inner surface of the metal cap component and interfaces with an outer surface of the tapered head portion of the polymer nose element.

2. 发明授权

US09550586B2 Apparatus and methods for hypersonic stochastic switch 有权
标题翻译：用于超音速随机开关的装置和方法
公开(公告)号：US09550586B2
公开(公告)日：2017-01-24
申请号：US15083128
申请日：2016-03-28
申请人： Charl E. Janeke
发明人： Charl E. Janeke
IPC分类号： B64C1/38 , B64G1/62 , F25J3/02 , F25D3/10
CPC分类号： B64G1/62 , F25D3/10 , F25J3/029 , F42B10/38 , F42B10/46 , F42B12/02 , F42B15/34
摘要： An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The ensuing supercool/chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled & flashed into liquid air. By means of extension, liquid air may be rendered as a direct result of said supercooling throughout the hypersonic regime into space. Also described are the details of an isentropically expanded hypersonic stochastic switch (a singularity), which is mainly achieved via the addition of a high pressure supersonic isentropic expansion nozzle whereby a continuous flow continuum is transformed into a stochastic flux.
摘要翻译：一种用于减轻火箭或航空航天飞机以超音速飞行的冲击前沿同时从周围空气中蒸馏液体化学元素的装置和方法。因此，由于过冷而导致的随后的过冷/冷却空气可被压缩，再生地中冷并闪蒸成液体空气。通过延伸，可以将液体空气作为所有超冷却过程的直接结果，直到超音速状态进入空间。还描述了等速扩展的超音速随机开关（一个奇点）的细节，其主要通过添加高压超音速等熵膨胀喷嘴来实现，由此将连续流动连续体转化为随机通量。

3. 发明申请

US20160169644A1 METHOD FOR INCREASING THE RANGE OF SPIN-STABILIZED PROJECTILES, AND PROJECTILE OF SAID TYPE 审中-公开
标题翻译：增加旋转稳定项目范围的方法，以及类型的项目
公开(公告)号：US20160169644A1
公开(公告)日：2016-06-16
申请号：US14908488
申请日：2014-07-30
申请人： ALPHA VELORUM AG
发明人： Martin ZIEGLER
IPC分类号： F42B10/38
CPC分类号： F42B10/38
摘要： To increase the range of a spin-stabilized projectile which moves in a surrounding medium, the surrounding medium from a stagnant-water region of the projectile is, by means of a part of the rotational energy of the projectile, conveyed under the inflowing boundary layer at the outer surface of the projectile, and thus the speed gradient of the boundary layer in the vicinity of the wall is reduced. For this purpose, the outer surface has at least one encircling groove (9) which is connected by radial transverse ducts (10) to at least one longitudinal duct (11) in the interior of the projectile, which in turn is connected to an opening in the rear of the projectile.
摘要翻译：为了增加在周围介质中移动的自旋稳定的射弹的范围，来自射弹停滞水区域的周围介质通过射弹的旋转能量的一部分在流入边界层下传送在射弹的外表面，因此边界层在壁附近的速度梯度减小。为此，外表面具有至少一个环绕的凹槽（9），该凹槽（9）通过径向横向管道（10）连接到射弹内部的至少一个纵向导管（11），该纵向导管又连接到开口在后方的射弹。

4. 发明申请

US20150059721A1 ROTATING-FORCE ADJUSTING DEVICE FOR A TOY GUN 审中-公开
标题翻译：旋转力调节装置用于玩具枪
公开(公告)号：US20150059721A1
公开(公告)日：2015-03-05
申请号：US14144541
申请日：2013-12-30
申请人： KIEN WELL TOY INDUSTRIAL CO., LTD.
发明人： Shun-Chi Huang
IPC分类号： F41B7/08
CPC分类号： F41B7/08 , F41A1/06 , F41A21/12 , F41A21/16 , F41B11/62 , F41B11/89 , F42B10/38
摘要： A rotating-force adjusting device for a toy gun has a gun body, a mounting tube, a driven element and a driving element. The gun body has an outer shell and an inner barrel. The mounting tube is mounted around the inner barrel and has a pressing block. The driven element is mounted in the outer shell, is pressed against the mounting tube and has an extending wing. The extending wing is formed on and protrudes curvedly from an upper end of the driven element and has a protruding post above the pressing block. The driving element is movably mounted in the outer shell, is pressed against the extending wing and has a main body, a turning tab and a guiding groove.
摘要翻译：用于玩具枪的旋转力调节装置具有枪体，安装管，从动元件和驱动元件。枪体具有外壳和内筒。安装管安装在内筒周围并具有一个按压块。被驱动元件安装在外壳中，被压靠在安装管上并具有延伸翼。延伸翼形成在从动元件的上端部并且从被驱动元件的上端弯曲地突出，并且在压块上方具有突出的杆。驱动元件可移动地安装在外壳中，被压靠在延伸翼上，并具有主体，转动翼片和导向槽。

5. 发明授权

US08910576B2 Bomb for deployment from an air vehicle 有权
标题翻译：用于从空中飞行器部署的炸弹
公开(公告)号：US08910576B2
公开(公告)日：2014-12-16
申请号：US13575882
申请日：2012-06-28
申请人： Rodney Andrew Irvine
发明人： Rodney Andrew Irvine
IPC分类号： F02K9/10 , F02K9/12 , F02K9/18 , F02K9/22 , F02K9/95 , F42B15/00 , F42B15/10 , F42B10/38
CPC分类号： F02K9/10 , F02K9/12 , F02K9/18 , F02K9/22 , F02K9/95 , F42B10/38 , F42B15/10
摘要： A bomb for deployment from an air vehicle includes a rocket motor for propelling the bomb. The rocket motor includes propellant which at least partially defines a void downstream of an initial burning surface. As the propellant is burned the void will be exposed, increasing the surface area of the burning surface of the propellant to increase the thrust of the rocket motor.
摘要翻译：用于从空中飞行器部署的炸弹包括用于推进炸弹的火箭发动机。火箭发动机包括至少部分地限定初始燃烧表面下游的空隙的推进剂。随着推进剂燃烧，空隙将被暴露，增加推进剂燃烧表面的表面积，以增加火箭发动机的推力。

6. 发明申请

US20140251295A1 TWO-PHASE PROJECTILE 审中-公开
标题翻译：两相项目
公开(公告)号：US20140251295A1
公开(公告)日：2014-09-11
申请号：US13789514
申请日：2013-03-07
申请人： G. Wilson Flint , Michael Jones
发明人： G. Wilson Flint , Michael Jones
IPC分类号： F42B6/02 , F41B5/00 , F41B5/12 , F42B10/38
CPC分类号： F42B6/02 , F41B11/723 , F41B11/73 , F42B6/04 , F42B10/38 , F42B12/64
摘要： A device for transferring energy to propel a payload with added velocity after launch includes a first component having a mass (m1), and a second component having a mass (m2). As an assembly, the first and second components are positioned to establish a compression chamber between them that is dimensionally responsive to their relative movements. And, a payload is mounted on a selected component of the assembly. In operation, a driving force is exerted against one component of the assembly to propel the entire assembly along a predetermined flight path. Contemporaneously with this acceleration, the two components are moved toward each other. In turn, this compresses gas in the gas chamber to generate potential energy that is transferred as the gas expands to separate the payload from the assembly with added velocity.
摘要翻译：用于传送能量以在发射之后以附加速度推进有效载荷的装置包括具有质量（m1）的第一部件和具有质量（m2）的第二部件。作为组件，第一和第二部件被定位成在它们之间建立一个压缩室，其在尺寸上响应于它们的相对运动。并且，有效载荷被安装在组件的选定部件上。在操作中，驱动力被施加在组件的一个部件上以沿着预定的飞行路径推动整个组件。与此加速度同时，两个组件相互移动。反过来，这压缩了气体室中的气体，以产生随着气体膨胀而传递的势能，以便以附加的速度将有效载荷与组件分开。

7. 发明申请

US20140230684A1 CHARGED PROJECTILES AND RELATED ASSEMBLIES, SYSTEMS AND METHODS 有权
标题翻译：收费项目及相关组织，系统和方法
公开(公告)号：US20140230684A1
公开(公告)日：2014-08-21
申请号：US13789147
申请日：2013-03-07
申请人： Alliant Techsystems Inc.
发明人： Otto S. Krauss , John W. Westbrook, III
IPC分类号： F42B10/38 , F42B12/00
CPC分类号： F42B10/38 , F42B5/02 , F42B10/32 , F42B12/00 , F42B30/00
摘要： Charged projectile assemblies include a housing and an electronic assembly configured to produce an electric field about at least a portion of the housing of the projectile. Cartridge assemblies for use with firearms include charged projectiles. Methods of charging a projectile include forming an electric field about at least a portion of a projectile and extending the electric field at least partially between a forward portion of the projectile and an aft portion of the projectile.
摘要翻译：带电弹丸组件包括壳体和电子组件，其被配置为在射弹的壳体的至少一部分周围产生电场。与火器一起使用的墨盒组件包括带电弹丸。对弹丸进行充电的方法包括在射弹的至少一部分周围形成电场，并至少部分地在射弹的前部与射弹的后部之间延伸电场。

8. 发明授权

US08548650B1 Hierarchical closed-loop control system for aircraft, missiles and munitions 有权
标题翻译：用于飞机，导弹和弹药的分层闭环控制系统
公开(公告)号：US08548650B1
公开(公告)日：2013-10-01
申请号：US13455182
申请日：2012-04-25
申请人： Troy S. Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S. Prince , Richard Kolacinski , Mehul Patel
IPC分类号： B64C13/00 , F41G7/00 , G01C23/00
CPC分类号： G05D1/107 , F42B10/38 , F42B10/40 , F42B10/42 , F42B10/668 , F42B15/01
摘要： The present invention relates to a missile or munition with a hierarchical, modular, closed-loop flow control system, more particularly to aircraft or munition with flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.Various embodiments of the flow control system involve elements including flow sensors, active flow control devices or activatable flow effectors, and logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on the surfaces of a missile or munition. The active flow control device or activatable flow effectors create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.
摘要翻译：本发明涉及具有分级，模块化，闭环流量控制系统的导弹或弹药，更具体地涉及具有用于增强的空气动力学控制，机动性和稳定性的流量控制系统的飞机或弹药。本发明还涉及一种操作流量控制系统的方法。流量控制系统的各种实施例涉及包括流量传感器，主动流量控制装置或可激活流动效应器以及具有闭环控制架构的逻辑装置的元件。传感器用于估计或确定导弹或弹药表面的流动状况。主动流量控制装置或可激活流动效应器沿着导弹或飞行器的各种空气动力学表面在不同点处产生按需的流动干扰，优选微扰动，以实现期望的稳定性或机动性效果。逻辑器件嵌入了分层控制结构，允许在流表面进行快速，实时的控制。

9. 发明申请

US20120199691A1 PROJECTILE THAT INCLUDES AS NEEDED PRESSURE-RELIEVING WRAP-AROUND TAIL FINS 有权
标题翻译：包括需要压力消除缠绕尾灯的项目
公开(公告)号：US20120199691A1
公开(公告)日：2012-08-09
申请号：US12789068
申请日：2010-05-27
申请人： Chris E. Geswender , Mark E. Elkanick , Craig O. Shott
发明人： Chris E. Geswender , Mark E. Elkanick , Craig O. Shott
IPC分类号： F42B15/01
CPC分类号： F42B10/16 , F42B10/20 , F42B10/38
摘要： Some embodiments pertain to a projectile that includes a casing and a plurality of fins which are secured to the casing. Each of the fins is movable between a stowed position and a deployed position. The fins are typically in the stowed position during storage and launch, and move to the deployed position as soon as possible after launch. Each fin includes a first foil that has a first set of openings and a second foil that includes a second set of openings. The first sets of openings in the first foils are aligned with the second sets of openings in the second foils when each of the fins is in the stowed position. The first sets of openings in the first foils are not aligned with the second sets of openings in the second foils when each of the fins is in the deployed position.
摘要翻译：一些实施例涉及一种弹射器，其包括壳体和固定到壳体的多个翅片。每个翅片可在收起位置和展开位置之间移动。散热片通常在储存和发射期间处于收起位置，并且在发射后尽快移动到展开位置。每个翅片包括具有第一组开口的第一箔片和包括第二组开口的第二箔片。当每个翅片处于收起位置时，第一箔中的第一组开口与第二箔中的第二组开口对准。当每个翅片处于展开位置时，第一箔中的第一组开口不与第二箔中的第二组开口对齐。

10. 发明申请

US20110155016A1 Synchronized Spin Multi-Component Projectile 有权
标题翻译：同步自旋多组分弹丸
公开(公告)号：US20110155016A1
公开(公告)日：2011-06-30
申请号：US12784654
申请日：2010-05-21
申请人： PJ Marx
发明人： PJ Marx
IPC分类号： F42B14/02 , F42B12/00
CPC分类号： F42B10/26 , F42B10/38 , F42B12/34 , F42B14/02
摘要： A projectile includes a leading part formed by a tip and a tip base that form a first annular shoulder where they meet. A trailing part of the projectile is formed by a base having a frusto-conical trailing end and a cylindrical leading end of truncate extent that forms a tail drive. A second annular shoulder is formed where a cylindrical rod meets the tail drive. A flat trailing end of the tip base and a flat leading end of the cylindrical rod abut one another when the projectile is assembled. A cylindrical interface has a leading extent abutting the first annular shoulder and a trailing end abutting the second annular shoulder. The tail drive and the trailing extent of the cylindrical interface are the only parts of the projectile that engage gun barrel rifling when the projectile is positioned in a gun barrel.
摘要翻译：抛射体包括由尖端和尖端基部形成的引导部分，其形成第一环形肩部，在那里它们相遇。抛射体的尾部由具有截头圆锥形后端和形成尾部驱动的截头范围的圆柱形前端的基部形成。形成第二环形肩部，其中圆柱形杆与尾部驱动器相交。当组装抛射体时，尖端基部的平坦的后端和圆柱形杆的平坦的前端彼此邻接。圆柱形接口具有与第一环形肩部相邻的引导程度和邻接第二环形肩部的后端。当弹丸放置在枪管中时，尾部驱动器和圆柱形接口的尾部范围是射弹的唯一部分，可以与枪筒枪膛接合。

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