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1. 发明公开

US20240384972A1 PROJECTILE WITH ENHANCED BALLISTICS 审中-公开
公开(公告)号：US20240384972A1
公开(公告)日：2024-11-21
申请号：US18787619
申请日：2024-07-29
申请人： G9 Holdings, LLC
发明人： Joshua Mahnke
IPC分类号： F42B12/02 , F42B10/22 , F42B10/24 , F42B10/26 , F42B10/46 , F42B12/06 , F42B12/34 , F42B12/74 , F42B30/02
CPC分类号： F42B12/02 , F42B10/22 , F42B10/24 , F42B10/26 , F42B10/46 , F42B12/06 , F42B12/34 , F42B12/74 , F42B30/02
摘要： The present invention provides a projectile device and a method of manufacture of a projectile device and in particular, to a pistol bullet and a rifle bullet and method of manufacture of same. In one embodiment, the projectile apparatus has a cylindrical body portion having a diameter, a front nose section tapering from a most proximal point of the projectile to the cylindrical body portion, and a rear tail section connected to the body portion and extending to the most distal point of the projectile, in which the front nose portion comprises a plurality of twisting depressions forming troughs.

2. 发明授权

US12123687B2 Steerable projectile 有权
公开(公告)号：US12123687B2
公开(公告)日：2024-10-22
申请号：US18007133
申请日：2021-07-21
申请人： BAE SYSTEMS plc
发明人： James Joshua Norris
IPC分类号： F42B10/62 , F42B10/46
CPC分类号： F42B10/62 , F42B10/46
摘要： There is provided a projectile, a system and a related method of operation of a projectile comprising: a front ogive section; an aft section; and a control module; wherein the front ogive section is rotatably connected to the aft section by a coupling device, the front ogive section further comprising an asymmetric surface such that the asymmetric surface exerts an imbalance upon the projectile, where in use, the angular rotation of the front ogive section can be selectively adjusted relative to the aft section by commands from the control module to the coupling device influencing a helical trajectory of the projectile in flight thereby causing a change in direction thereby steering the projectile towards a target.

3. 外观设计

USD1043897S1 Projectile 有权
公开(公告)号：USD1043897S1
公开(公告)日：2024-09-24
申请号：US29859102
申请日：2022-11-07
申请人： G9 Holdings, LLC
设计人： Joshua Mahnke
CPC分类号： F42B12/02 , F42B10/22 , F42B10/24 , F42B10/26 , F42B10/46 , F42B12/06 , F42B12/74 , F42B30/02
摘要： FIG. 1 is a perspective view of a projectile showing my new design;
FIG. 2 is a left elevation view thereof;
FIG. 3 is a front elevation view thereof, which is the same as the rear elevation view, top plan view, and bottom plan view because the projectile is symmetrical around its longitudinal axis;
FIG. 4 is a right elevation view thereof;
FIG. 5 is a perspective view of another embodiment of a projectile showing my new design;
FIG. 6 is a left elevation view of the projectile of FIG. 5;
FIG. 7 is a front elevation view of the projectile of FIG. 5, which is the same as the rear elevation view, top plan view, and bottom plan view because the projectile is symmetrical around its longitudinal axis;
FIG. 8 is a right elevation view of the projectile of FIG. 5;
FIG. 9 is a perspective view of another embodiment of a projectile showing my new design;
FIG. 10 is a left elevation view of the projectile of FIG. 9;
FIG. 11 is a front elevation view of the projectile of FIG. 9, which is the same as the rear elevation view, top plan view, and bottom plan view because the projectile is symmetrical around its longitudinal axis; and,
FIG. 12 is a right elevation view of the projectile of FIG. 9.
The dot-dash lines are provided to show the boundary of the claim and form no part of the claim. The dash-dash lines showing portions of a projectile are provided for the purpose of illustrating environment and form no part of the claimed design.

4. 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.

5. 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.

6. 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.

7. 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.

8. 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.

9. 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.

10. 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.

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