专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

101. 发明授权

US3807306A Follow through device capable of injecting material (liquid) through hole formed by shaped charge 失效
标题翻译：通过能够通过形状填充形成的材料（液体）注入材料的装置
公开(公告)号：US3807306A
公开(公告)日：1974-04-30
申请号：US67252557
申请日：1957-07-17
申请人： US ARMY
发明人： ALPER A , CUTLER M , DI PAOLO V
IPC分类号： F42B12/16 , F42B12/50 , F42B15/10
CPC分类号： F42B12/16 , F42B12/50
摘要： 1. In a rocket projectile comprising a rocket motor and a shaped charge, the combination of a detonator housing mechanism behind said shaped charge, a sealed liquid container behind said detonator housing and in front of said rocket motor, said detonator mechanism comprising a detonator charge, a firing pin positioned against said detonator charge and an inertia weight behind said firing pin so that on impact of the projectile, the inertia weight moves forward, thereby engaging the firing pin to set off the detonator and subsequently the shaped charge, whereupon the exploding detonator and shaped charge drives the inertia weight back into the liquid container, rupturing the same and displacing its contents forward through the opening made by the shaped charge.
摘要翻译： 1.在包括火箭发动机和成形装药的火箭弹中，在所述成形装置之后的雷管壳体机构的组合，位于所述雷管外壳之后和所述火箭发动机前面的密封液体容器，所述雷管机构包括雷管充电，一个靠着所述雷管充电定位的撞针和在所述撞针之后的惯性重锤，使得在弹丸撞击时，惯性重量向前移动，从而接合撞针以引爆雷管并随后形成成形电荷，于是爆炸雷管和成形装置将惯性重量推回到液体容器中，将其重新打开并将其内容物向前移动通过由成形装料制成的开口。

102. 发明授权

US3749333A Dead reckoning back-up navigational system for a drone 失效
标题翻译：死亡记录背景导航系统
公开(公告)号：US3749333A
公开(公告)日：1973-07-31
申请号：US3749333D
申请日：1972-06-15
申请人： LEAR SIEGLER INC
发明人： LYKKEN L , SCHULZE E
IPC分类号： F41G7/34 , F42B8/24 , F42B15/01 , G01C21/20 , F42B15/10 , F42B15/02 , F42B15/32
CPC分类号： G01C21/20 , F41G7/343 , F42B8/24 , F42B15/01 , G05D1/0055 , G05D1/0202
摘要： The heading and range to a recovery area for a drone on a mission are continuously monitored and stored on board the drone. Any failure in the primary navigational system in the drone is detected and the stored heading and stored range are available for comparison with the on-board compass reading of the drone and an on-board air speed integrator for the drone. Any deviation between the drone compass reading and the stored heading is corrected by generation of an error signal to operate the flight controls of the auto-pilot on the drone to steer the drone towards the recovery area. A landing command signal, in turn, is provided only when the integrated air speed equals the stored range. Corrections for wind conditions are automatically included in the stored heading and range information so that accurate dead reckoning back to the recovery area is realizable. A wholly selfcontained means is thus provided for returning a drone to a specified recovery area in the event of failure of its primary navigational system at any point in time during its mission.
摘要翻译：任务中无人机的恢复区的航向和距离不断被监控并存储在无人机上。检测到无人机中的主导航系统中的任何故障，并且存储的航向和存储的范围可用于与无人机的机载罗盘读数和用于无人机的机载航空速度积分器进行比较。通过产生误差信号来校正无人机罗盘读数和存储的航向之间的任何偏差，以操作无人机上的自动飞行员的飞行控制以引导无人机朝向恢复区域。仅当集成的空气速度等于存储的范围时，才提供着陆命令信号。风向的校正被自动包含在存储的标题和范围信息中，从而可以实现到恢复区域的准确的航位推算。因此，提供完全独立的手段，用于在其任务期间的任何时间点将无人机返回到指定的恢复区域，以防其主导航系统发生故障。

103. 发明授权

US3613580A Wedge-shaped free-fall device 失效
标题翻译： WEDGE-SHAPED FREE-FALL DEVICE
公开(公告)号：US3613580A
公开(公告)日：1971-10-19
申请号：US3613580D
申请日：1969-11-10
申请人： AVCO CORP
发明人： BENCH THOMAS E , COFFENBERRY JAMES H
IPC分类号： F42B10/26 , F42B15/10 , F42B25/16
CPC分类号： F42B15/105 , F42B10/26
摘要： A free-fall device is disclosed which has a generally wedgeshaped body. Flutes or vanes are provided on all of the triangular faces of the body which cause the body to autorotate and glide when freely falling through the air.

104. 发明授权

US3457861A Missile booster pressure control mechanism 失效
标题翻译： MISSILE BOOSTER压力控制机构
公开(公告)号：US3457861A
公开(公告)日：1969-07-29
申请号：US3457861D
申请日：1968-01-25
申请人： US NAVY
发明人： CROCKETT SYDNEY R
IPC分类号： F02K9/76 , F42B15/36 , F42B15/10
CPC分类号： F02K9/763 , F42B15/36

105. 发明授权

US2992794A Guided missile 失效
公开(公告)号：US2992794A
公开(公告)日：1961-07-18
申请号：US20068050
申请日：1950-12-13
申请人： BOYD WILLIAM H A
发明人： BOYD WILLIAM H A
IPC分类号： F42B15/10 , F42B15/22 , F42B15/36
CPC分类号： F42B15/22 , F42B15/105 , F42B15/36

106. 发明授权

US2691495A Projectile 失效
标题翻译：射弹
公开(公告)号：US2691495A
公开(公告)日：1954-10-12
申请号：US8067849
申请日：1949-03-10
申请人： PIERRE CHIROKY
发明人： PIERRE CHIROKY
IPC分类号： F02K7/10 , F42B15/10
CPC分类号： F02K7/10 , F42B15/105

107. 发明授权

US1300708A Projectile. 失效
公开(公告)号：US1300708A
公开(公告)日：1919-04-15
申请号：US7783316
申请日：1916-02-12
申请人： EDISON THOMAS A
发明人： EDISON THOMAS A
IPC分类号： F42B15/10
CPC分类号： F42B15/105

108. 发明授权

US1152668A Projectile. 失效
公开(公告)号：US1152668A
公开(公告)日：1915-09-07
申请号：US211115
申请日：1915-01-14
申请人： SULLIVAN CHARLES F , SULLIVAN VIRGINIA A
发明人： SULLIVAN CHARLES F , SULLIVAN VIRGINIA A
IPC分类号： F42B15/10
CPC分类号： F42B15/105

109. 发明授权

US11940251B2 Remotely controllable aeronautical ordnance 有权
公开(公告)号：US11940251B2
公开(公告)日：2024-03-26
申请号：US17378765
申请日：2021-07-19
申请人： Overwerx Ltd
发明人： Jeffrey Hill
IPC分类号： F42B10/14 , F42B10/38 , F42B12/02 , F42B15/01 , F42B15/10 , F42C1/00 , F42C13/04 , G05D1/00 , H04N7/18
CPC分类号： F42B10/14 , F42B10/38 , F42B12/02 , F42B15/01 , F42B15/10 , F42C1/00 , F42C13/047 , G05D1/0022 , G05D1/0038 , H04N7/185
摘要： An ordnance for air-borne delivery to a target under remotely controlled in-flight navigation. In one embodiment, self-powered aerial ordnance includes upper and lower cases. A plurality of co-axial, deployable blades is powered by a motor positioned in the upper case. When deployed, the blades are rotatable about the upper case to impart thrust and bring the vehicle to a first altitude above a target position. An explosive material and a camera are positioned in a lower case which is attached to the upper case. The camera generates a view along the ground plane and above the target when the ordinance is in flight. When the vehicle is deployed it is remotely controllable to deliver the vehicle to the target to detonate the explosive at the target. The ordnance may drop directly on a target as a bomb does.

110. 发明授权

US11879410B2 Metal-stabilized propellant grain for gun-fired rocket motor, and rocket motor baffled end cap for reliable gunfire 有权
公开(公告)号：US11879410B2
公开(公告)日：2024-01-23
申请号：US17184470
申请日：2021-02-24
申请人： Raytheon Company
发明人： Joseph A. Carmody , Benjamin C. Hulbert , Ryan J. Paffenroth , Andrew J. Harris
IPC分类号： F02K9/32 , F02K9/26 , F42B15/10 , F42B5/10 , F42B15/00 , F02K9/97 , F42B14/00
CPC分类号： F02K9/32 , F02K9/26 , F02K9/978 , F42B5/10 , F42B5/105 , F42B14/00 , F42B15/00 , F42B15/10
摘要： A rocket motor for a gun-fired projectile is configured stiffen the burnable propellant in the rocket motor during burning and/or protect the rocket motor from the pressure that occurs during firing of the projectile from the gun. The rocket motor may include a rigid structure that is integrated into the burnable propellant grain to stabilize the burnable propellant grain during burning of the burnable propellant grain. The rigid structure has a matrix or truss-like shape that extends into the depth of the burnable propellant grain. The rocket motor may include a baffled end cap that covers a nozzle of the rocket motor. The end cap defines a baffled path through the end cap to dampen gas flow into the nozzle and prevent particles of the gun propellant from entering the rocket motor. A rocket motor may implement the rigid structure or the baffled end cap, or both structures.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式