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1. 发明授权

US06928931B1 Release mechanism in missile 失效
标题翻译：导弹释放机制
公开(公告)号：US06928931B1
公开(公告)日：2005-08-16
申请号：US10009281
申请日：2000-06-02
申请人： Hans B. Biserød
发明人： Hans B. Biserød
IPC分类号： F15B15/19 , F15B15/22 , F42B10/12 , F42B12/06 , F42B15/00 , F42B15/36 , F42B15/10
CPC分类号： F42B15/36 , F15B15/19 , F15B15/22 , F42B10/12 , F42B12/06 , F42B15/00
摘要： A release mechanism between a projectile and a rocket motor in a missile. The projectile releases from the rocket motor during flight of the missile when the rocket motor burns out and aerodynamic retardation commences. The front end of the rocket motor comprises a forward closure, a lock retainer received and movable within the forward closure, at least one lock, at least one spring that biases the lock against the lock retainer in a direction opposite the to the direction of motion of the missile. The rear end of the projectile has a central boss surrounded by the forward closure of the rocket motor, wherein the boss comprises recesses or a circumferential groove in which the at least one lock lies and keeps the forward closure and the boss axially together.
摘要翻译：导弹与火箭发动机之间的释放机制。当火箭发动机燃烧和空气动力学迟滞开始时，弹药在导弹飞行期间从火箭发动机释放。火箭发动机的前端包括一个向前的封闭件，一个在前部封闭件内容纳并可移动的锁定保持器，至少一个锁，至少一个弹簧，其将锁定件抵靠锁定保持器沿与运动方向相反的方向的导弹。抛射体的后端具有由火箭发动机的前封闭件包围的中心凸台，其中凸台包括凹槽或周向凹槽，其中至少一个锁定位于其中，并将前盖和凸台轴向保持在一起。

2. 发明授权

US3179052A Drag collar for varying the range of rockets 失效
标题翻译：拖动项圈以改变火箭的范围
公开(公告)号：US3179052A
公开(公告)日：1965-04-20
申请号：US20416662
申请日：1962-06-21
申请人： HOTCHKISS BRANDT
发明人： RAYMOND JASSE JOSEPH
IPC分类号： F42B10/12 , F42B10/50
CPC分类号： F42B10/12 , F42B10/50

3. 发明授权

US3125957A lipinski 失效
公开(公告)号：US3125957A
公开(公告)日：1964-03-24
申请号：US3125957D
IPC分类号： F42B10/06 , F42B10/12 , F42B14/06
CPC分类号： F42B10/12 , F42B10/06 , F42B14/061

4. 发明授权

US2437211A Rocket 失效
标题翻译：火箭
公开(公告)号：US2437211A
公开(公告)日：1948-03-02
申请号：US54648244
申请日：1944-07-25
申请人： SCHERMULY PISTOL ROCKET APP
发明人： DAVID SCHERMULY CONRAD , JAMES SCHERMULY ALFRED , CHARLES SCHERMULY
IPC分类号： F42B10/12 , F42B12/68
CPC分类号： F42B12/68 , F42B10/12

5. 发明授权

US2409904A Rocket 失效
标题翻译：火箭
公开(公告)号：US2409904A
公开(公告)日：1946-10-22
申请号：US54009344
申请日：1944-06-13
申请人： SCHERMULY PISTOL ROCKET APP
发明人： DAVID SCHERMULY CONRAD , JAMES SCHERMULY ALFRED , CHARLES SCHERMULY
IPC分类号： F42B10/12 , F42B12/68
CPC分类号： F42B12/68 , F42B10/12

6. 发明授权

US2359515A Variable range projectile 失效
标题翻译：可变射弹
公开(公告)号：US2359515A
公开(公告)日：1944-10-03
申请号：US43773342
申请日：1942-04-06
申请人： MARTIN C MOGENSEN , HERBERT W ERSKINE , CLEVE F SHAFFER , HENRY GRUENHAGEN
发明人： FANGER HERMAN J
IPC分类号： F42B10/12
CPC分类号： F42B10/12

7. 发明授权

US11220324B2 Apparatus for a vehicle 有权
公开(公告)号：US11220324B2
公开(公告)日：2022-01-11
申请号：US16478221
申请日：2018-02-01
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Shahar Bar Hillel , Saar Shragai
IPC分类号： B64C5/12 , F42B10/06 , F42B10/50 , F42B10/20 , F42B10/28 , F42B10/12
摘要： Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.

8. 发明授权

US06986481B2 Extendable joined wing system for a fluid-born body 失效
标题翻译：用于流体出生体的可扩展连接翼系统
公开(公告)号：US06986481B2
公开(公告)日：2006-01-17
申请号：US10698580
申请日：2003-10-31
申请人： Jerome P. Fanucci , Michael J. King , David P. Maass , Pavel Bystricky
发明人： Jerome P. Fanucci , Michael J. King , David P. Maass , Pavel Bystricky
IPC分类号： F42B10/12
CPC分类号： B64C3/40 , B63B1/30 , B64C3/56 , B64C39/068 , Y02T50/14
摘要： An extendable wing system for a fluid-born body has a forward wing and an aft wing pivotably coupled together at a location outward of their wing roots. A linkage mechanism mounted on the body provides both pivoting of the wing roots about a pivot point and translation of the wing roots and their pivot points to extend the joined wings from a stowed position to a deployed position. Translation of the forward wing root pivot point allows the stowed wing system to occupy additional space toward the nose of the body, thereby allowing use of wings having a longer wingspan and greater aspect ratio. The linkage mechanism can also be used to incorporate flight control, such as roll and pitch control, directly into the wing system. In another embodiment, the wings can incorporate actuator elements on or within the wings to effect flight control by deformation of the wing structure.
摘要翻译：用于流体出身体的可延伸的翼系统具有前翼和后翼，它们在其翼根的外侧的位置处可枢转地联接在一起。安装在主体上的连杆机构提供了机翼根部围绕枢轴点的枢转以及机翼根部及其枢转点的平移，以将结合的机翼从收起位置延伸到展开位置。前翼根枢轴点的翻译允许收起的翼系统占据身体鼻部的额外空间，从而允许使用具有较长翼展和更大纵横比的翼。连杆机构也可用于将飞行控制，如滚转和俯仰控制，直接融入机翼系统。在另一个实施例中，翼可以将致动器元件结合在翼上或翅膀内，以通过翼结构的变形来实现飞行控制。

9. 发明授权

US5846147A Bow launcher and arrow system 失效
标题翻译：弓发射器和箭头系统
公开(公告)号：US5846147A
公开(公告)日：1998-12-08
申请号：US818883
申请日：1997-03-17
申请人： Ronald Basik
发明人： Ronald Basik
IPC分类号： F41B5/22 , F42B6/04 , F42B6/06 , F42B10/12 , F41B5/00
CPC分类号： F41B5/143 , F42B10/12 , F42B6/04 , F42B6/06
摘要： In order to provide enhanced performance from fletching, an integral or slidable stabilizer is operatively associated with an arrow shaft. The stabilizer in either form includes a plurality of radial vanes each of which imparts aerodynamic force to the shaft so as to cause the arrow to roll or "spin" when the arrow is in flight. In the preferred embodiments of the invention, the radial vanes of the stabilizer have a cross section in the form of an airfoil to thereby induce the roll or "spin."
摘要翻译：为了提供从快速提升的性能，整体或可滑动的稳定器与箭头轴可操作地相关联。任何形式的稳定器包括多个径向叶片，每个径向叶片向轴施加空气动力，以便当箭头处于飞行状态时使箭头滚动或“旋转”。在本发明的优选实施例中，稳定器的径向叶片具有翼型形式的横截面，从而引起滚动或“旋转”。

10. 依法登记的发明

USH942H Saboted munition with a movable fin group 失效
标题翻译：具有活动鳍组的撒旦弹药
公开(公告)号：USH942H
公开(公告)日：1991-08-06
申请号：US612287
申请日：1990-11-06
申请人： Martin L. Pardee
发明人： Martin L. Pardee
IPC分类号： F42B10/12
CPC分类号： F42B10/12
摘要： An armor piercing convertible fin saboted round for a machine gun includes penetrator on which a fin group is mounted so that the penetrator can extend into a prelaunch sabot with the fin group arranged around the penetrator. The fin group advantageously carries a pin which engages in an elongated groove defined on the penetrator and permits the fin group to slide along the body of the penetrator during launch so that it may move from a forward position adjacent the tip of the penetrator rearwardly during launch to an end position in which it is engaged adjacent the end of the penetrator and stabilizes the penetrator during flight.

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