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1. 发明公开

US20230417522A1 Passive Cavity Deflation for Impacting Bodies after Water Entry 审中-公开
公开(公告)号：US20230417522A1
公开(公告)日：2023-12-28
申请号：US17947030
申请日：2022-09-16
申请人： Areti Kiara , Tadd T. Truscott , Nathan Speirs , Rafsan Rabbi , Emma Fraley , Kelli Hendrickson
发明人： Areti Kiara , Tadd T. Truscott , Nathan Speirs , Rafsan Rabbi , Emma Fraley , Kelli Hendrickson
IPC分类号： F42B10/46 , F42B99/00 , F42B19/28 , F42B19/12
CPC分类号： F42B10/46 , F42B19/125 , F42B19/28 , F42B99/00
摘要： A device is disclosed for deflating a gas cavity about a projectile formed upon entry of the projectile into a liquid. The device can include a wall coupleable with a body operable as a projectile and defining an exterior and an interior space. The wall can be oriented toward a trailing end relative to a leading end defined by the body. The device can also include at least one inlet to facilitate gas flow from the exterior to the interior space. An outlet can facilitate gas flow from the interior space to the exterior and can be oriented toward the trailing end relative to the at least one inlet. Upon entry of the body and the wall into a liquid and formation of a gas cavity about a portion of the body and the wall, the at least one inlet can be located within the gas cavity and the outlet can be located outside the gas cavity, such that gas flows from the exterior through the at least one inlet to the interior space, and from the interior space through the outlet to the exterior to deflate the gas cavity.

2. 发明授权

US11815342B2 Method for making precision rifle ammunition with more uniform external ballistic performance and enhanced terminal ballistic performance 有权
公开(公告)号：US11815342B2
公开(公告)日：2023-11-14
申请号：US17892892
申请日：2022-08-22
申请人： SUPERIOR SHOOTINGS SYSTEMS, INC
发明人： G. David Tubb
IPC分类号： F42B5/02 , F42B10/44 , F42B10/46 , F42B12/74 , F42B12/76
CPC分类号： F42B5/025 , F42B10/44 , F42B10/46 , F42B12/74 , F42B12/76
摘要： A method for making an improved projectile 360, 460 by defining a discontinuity, groove or trough in a distal ogive section of the projectile to provide an external ballistic. effect uniforming surface feature (e.g., nose ring groove 369, 469) which makes an unsupported gap in the ogive profile that beneficially affects the flow of air over the front half of the ogive. The improved bullet's external surface discontinuity feature (369 or 469) creates effects in the flowfield that dominate any dynamic effects from bullet-to bullet manufacturing inconsistency and resultant differences in dynamic behavior.

3. 发明公开

US20230243629A1 CAVITATION CORE OF A FIREARM PROJECTILE 审中-公开
公开(公告)号：US20230243629A1
公开(公告)日：2023-08-03
申请号：US17638282
申请日：2020-06-30
申请人： Andrey Albertovich POLOVNEV
发明人： Andrey Albertovich POLOVNEV
IPC分类号： F42B10/46 , F42B10/08
CPC分类号： F42B10/46 , F42B10/08
摘要： The invention relates to firearm projectiles, primarily for destroying underwater targets in the case of underwater or air-to-water fire. A cavitation core of a firearm projectile results in an increase in target destruction efficiency by virtue of approximating the contour (R) of the cavitation core to the contour of the cavity (W) in the water, increasing the mass of the core and allowing loss of cavitation stability and rolling in a non-uniform (heterogeneous) and compressible water-containing medium.

4. 发明申请

US20180323489A1 Truss Reinforced Radome Crown Structure Shock Absorbing And Recoiling Sysytem 审中-公开
公开(公告)号：US20180323489A1
公开(公告)日：2018-11-08
申请号：US15479868
申请日：2017-04-05
申请人： Howard R. Vermillion, JR.
发明人： Howard R. Vermillion, JR.
IPC分类号： H01Q1/00 , H01Q1/42
CPC分类号： H01Q1/005 , B64C1/08 , B64C1/36 , B64C25/58 , F16F1/06 , F16F15/067 , F16F2232/08 , F16F2238/026 , F42B10/46 , H01Q1/281 , H01Q1/42
摘要： A truss reinforced radome crown structure shock absorbing and recoiling system that is utilized with an aircraft antenna adapter plate or other satellite communication (SAT-COM) structure to an aircraft airframe or fuselage and for allowing for pressurized expansion and contraction of the fuselage, or to protect against a bird strike incident or rapid decompression event. There are multiple design configurations of the system, with all configurations utilizing an actuating recoiling strut. In first and second design configurations, the strut is used on an adapter plate or adjacent to attachment lugs. A third design configuration uses a strut with a sliding mechanism. In all configurations after decompression, a bird strike incident or rapid decompression event the system will allow a fuselage to return to an original position.

5. 发明授权

US09952019B2 Ultrasonic electro-optic seeker 有权
公开(公告)号：US09952019B2
公开(公告)日：2018-04-24
申请号：US15059720
申请日：2016-03-03
申请人： Raytheon Company
发明人： Michael K. Burkland
IPC分类号： F41G7/22 , F42B30/00 , F41G7/00
CPC分类号： F41G7/2213 , F42B10/46 , F42B15/01 , F42B15/08 , F42B30/006
摘要： A ball joint gimbal (BJG) seeker assembly is provided and includes a back shell, a retaining system disposed to urge the seeker ball toward the back shell and a piezoelectric ultrasonic motor and sensor system arrayed between the seeker ball and the back shell. The piezoelectric ultrasonic motor and sensor system is pre-loaded by the retaining system and configured to controllably drive an angular orientation of the seeker ball.

6. 发明申请

US20180095191A1 PHASE GRADIENT NANOCOMPOSITE WINDOW FABRICATION AND METHOD OF FABRICATING DURABLE OPTICAL WINDOWS 审中-公开
公开(公告)号：US20180095191A1
公开(公告)日：2018-04-05
申请号：US15724683
申请日：2017-10-04
申请人： Raytheon Company
发明人： Catherine Trent , Gary A. Frazier , Kyle L. Grosse
IPC分类号： G02B1/11 , H05K9/00 , G02B1/16
CPC分类号： G02B1/11 , B29C41/04 , B29K2995/0011 , B29K2995/0026 , B29L2011/00 , B29L2031/778 , B32B1/00 , B32B5/16 , B32B7/02 , B32B2307/212 , B32B2307/412 , B32B2551/00 , B82Y30/00 , C04B35/01 , C04B35/053 , C04B35/505 , C04B35/645 , C04B35/6455 , C04B2235/3206 , C04B2235/3225 , C04B2235/60 , C04B2235/75 , C04B2235/9653 , F42B10/46 , G02B1/10 , G02B1/16 , G02B5/0221 , G02B5/0294 , H01Q1/42 , H01Q15/0013 , H05K9/009
摘要： An optical window is provided and includes a core layer, a cladding layer and an electromagnetic interference (EMI) layer interposed between the core and cladding layers.

7. 发明申请

US20180057191A1 Thermal protection and drag reduction method and system for ultra high-speed aircraft 审中-公开
公开(公告)号：US20180057191A1
公开(公告)日：2018-03-01
申请号：US15550777
申请日：2016-02-06
申请人： NINGBO INSTITUTE OF MATERIALS TECHNOLOGY & ENGINEERING, CHINESE ACADEMY OF SCIENCES , BEIJING INSTITUTE OF SPACECRAFT ENVIRONMENT ENGINEERING
发明人： Wenwu ZHANG , Shuhong XIANG , Chunhai GUO , Jingyu TONG , Tianrun ZHANG , Yang YANG , Tao SONG
IPC分类号： B64G1/58 , B64C21/04
CPC分类号： B64G1/58 , B64C1/38 , B64C21/04 , B64C2230/16 , B64D13/006 , B64G1/50 , F15D1/008 , F42B10/38 , F42B10/40 , F42B10/46 , F42B15/34 , Y02T50/56
摘要： Disclosed are the thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source is and a cold source driving device are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores are arranged on a wall surface of the cavity. The cold source driving device comprises an air pump, a cold source reservoir and a buffer. The air pump supplies compressed air to a cold source reservoir during operation. The cold source enters the buffer and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores to form a gas film on the outer surface of the cavity. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and the external gas, by virtue of which the thermal barrier phenomenon is alleviated or eliminated. Therefore, security of the ultra high-speed aircraft is improved and service life is prolonged.

8. 发明申请

US20170045344A1 METALLIC NOSECONE WITH UNITARY ASSEMBLY 有权
标题翻译：具有军事装配的金属NOSECONE
公开(公告)号：US20170045344A1
公开(公告)日：2017-02-16
申请号：US14826668
申请日：2015-08-14
申请人： Raytheon Company
发明人： Stephanie G. Rodriguez , Todd Kuhar , Thomas H. Penhollow , Brian B. Greer , Mark A. Hahn , Regina P. Reed , Richard M. Cordova , Patrick G. Dickerson , Kenneth G. Preston , Rick A. Ramos , Brady A. Hink , Gary H. Johnson
IPC分类号： F42B10/46 , B64C1/40 , B64C1/00 , B64C30/00
CPC分类号： F42B10/46 , B64C1/0009 , B64C1/40 , B64C30/00 , F42B15/36
摘要： A nosecone is provided and includes a ring that includes an angled surface, a nosecone tip, a double-walled shroud portion including inner and outer dome elements, a first end that interfaces with and is constrained by the nosecone tip and a second end that is connectable to the ring to define with the angled surface a sliding, resistive interface and a shim disposable in the double walled shroud portion to pre-load the sliding, resistive interface and to provide for separation distance between the inner and outer dome elements.
摘要翻译：提供了一种鼻锥，并且包括一个环，该环包括成角度的表面，鼻锥尖端，包括内部和外部圆顶元件的双壁护罩部分，与鼻锥尖端相接合并受其包围的第一端，可连接到所述环以与所述成角度的表面一起确定滑动，电阻接口和垫片，所述滑动，电阻接口和垫片一次性装在所述双壁护罩部分中，以预加载所述滑动电阻接口并提供所述内圆顶元件与所述外圆顶元件之间的间隔距离。

9. 发明申请

US20160318634A1 APPARATUS AND METHODS FOR HYPERSONIC STOCHASTIC SWITCH 审中-公开
标题翻译：装置和方法用于超静态开关
公开(公告)号：US20160318634A1
公开(公告)日：2016-11-03
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： B64G1/62 , F25D3/10 , F25J3/02
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。

10. 发明授权

US09366511B1 Reduced drag projectile 有权
标题翻译：减少弹丸
公开(公告)号：US09366511B1
公开(公告)日：2016-06-14
申请号：US14667867
申请日：2015-03-25
申请人： Lockheed Martin Corporation
发明人： John A. Wood
IPC分类号： F42B10/46 , F42B10/32
CPC分类号： F42B10/46 , F42B5/02 , F42B10/32 , F42B10/38
摘要： A reduced drag projectile is provided. The projectile includes a conductive shell that has a leading end and a trailing end. The conductive shell forms an interior volume. The projectile includes a conductive bullet core disposed at least partially within the interior volume. The conductive bullet core has a leading end element and is electrically insulated from the conductive shell. A voltage system is electrically coupled to the conductive shell and electrically coupled to the conductive bullet core. The projectile is configured to expose the leading end element to the atmosphere during flight, and the voltage system is configured to, during flight, generate a voltage at the leading end element that forms a corona discharge at the leading end element.
摘要翻译：提供了减少的弹丸。抛射体包括具有前端和后端的导电壳。导电壳形成内部容积。抛射体包括至少部分地设置在内部体积内的导电子弹芯。导电弹芯具有前端元件并与导电外壳电绝缘。电压系统电耦合到导电外壳并电耦合到导电子弹芯。抛射体被配置为在飞行期间将前端元件暴露于大气中，并且电压系统被配置为在飞行期间在前端元件处在前端元件处形成电晕放电的前端元件处产生电压。

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