专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08704699B2 Dipole based decoy system 有权
公开(公告)号：US08704699B2
公开(公告)日：2014-04-22
申请号：US10706665
申请日：2003-11-12
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： H01Q15/00
CPC分类号： F41H11/02 , F41J2/00 , F41J9/10 , F42B12/66 , H01Q1/28 , H01Q1/30 , H01Q15/0006 , H01Q15/14
摘要： A dipole based decoy system provides an inexpensive alternative to chaff. A non-conductive filament patterned with lengths of conductive material that form dipole antennas at one or more radar frequencies is stored on the air vehicle and attached to a projectile. In response to a RWR warning, a programmed time or location or a time-to-target, a mechanism releases the projectile(s) to deploy the filament with its dipole antennas at a speed greater than or equal to the speed of the air vehicle to present an extended target or a separate false target to enemy radar. The projectile is either towed behind the air vehicle or launched away from the air vehicle. Either approach is effective to overcome Doppler and moving range gating by presenting coherent signal returns and ranges and velocities consistent with the air vehicle during a threat interval posed by the radar defense systems.

2. 发明申请

US20140009319A1 Dipole based decoy system 有权
标题翻译：基于偶极子的诱饵系统
公开(公告)号：US20140009319A1
公开(公告)日：2014-01-09
申请号：US10706665
申请日：2003-11-12
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： F41H11/02 , H01Q15/14
CPC分类号： F41H11/02 , F41J2/00 , F41J9/10 , F42B12/66 , H01Q1/28 , H01Q1/30 , H01Q15/0006 , H01Q15/14
摘要： A dipole based decoy system provides an inexpensive alternative to chaff. A non-conductive filament patterned with lengths of conductive material that form dipole antennas at one or more radar frequencies is stored on the air vehicle and attached to a projectile. In response to a RWR warning, a programmed time or location or a time-to-target, a mechanism releases the projectile(s) to deploy the filament with its dipole antennas at a speed greater than or equal to the speed of the air vehicle to present an extended target or a separate false target to enemy radar. The projectile is either towed behind the air vehicle or launched away from the air vehicle. Either approach is effective to overcome Doppler and moving range gating by presenting coherent signal returns and ranges and velocities consistent with the air vehicle during a threat interval posed by the radar defense systems.
摘要翻译：基于偶极子的诱饵系统提供了廉价的谷壳替代品。在一个或多个雷达频率上形成偶极天线的导电材料长度图案化的非导电细丝被存储在飞行器上并附着到抛射体上。响应于RWR警告，编程的时间或位置或时间到目标，机构释放射弹以其偶极子天线部署灯丝，速度大于或等于机动车辆的速度向敌方雷达提出扩展目标或单独的虚假目标。抛射体被拖在机动车辆后面或从空中车辆上离开。任何一种方法都有效地通过在雷达防御系统构成的威胁间隔期间呈现与航空器一致的相干信号返回和范围和速度来克服多普勒和移动范围门控。

3. 发明授权

US08344304B2 Methods and apparatus for missile air inlet 有权
标题翻译：导弹入口的方法和装置
公开(公告)号：US08344304B2
公开(公告)日：2013-01-01
申请号：US12964798
申请日：2010-12-10
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： F41G7/00 , F42B15/01 , G06F19/00
CPC分类号： F02K7/10 , F02K7/105 , F02K7/18 , F42B10/38 , F42B15/10
摘要： Methods and apparatus for delivering a missile may operate in conjunction with a missile comprising an outer skin. The missile may be configured in a closed position and an open position. In the open position, an aperture is opened in the outer skin, for example to supply air to an air-breathing engine. In the closed position, the aperture is closed.
摘要翻译：用于传送导弹的方法和装置可以与包括外部皮肤的导弹一起操作。导弹可以配置在关闭位置和打开位置。在打开位置时，在外皮中开孔，例如将空气供给到空气呼吸引擎。在关闭位置，孔关闭。

4. 发明申请

US20120175458A1 GUIDANCE CONTROL FOR SPINNING OR ROLLING PROJECTILE 有权
标题翻译：纺纱或卷边工程指导控制
公开(公告)号：US20120175458A1
公开(公告)日：2012-07-12
申请号：US13005175
申请日：2011-01-12
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： F42B15/01 , F42C14/00 , F42B10/00
CPC分类号： F42B15/01 , F42B10/06 , F42B10/64
摘要： A projectile, air vehicle or submersible craft with a spinning or rolling fuselage, rotating on its axis, has a collar which can be positioned relative to a longitudinal axis of the projectile using aerodynamic forces. Aerodynamic surfaces, such as lift-producing surfaces, for example tails or canards, are coupled to the collar, and rotate with the collar. An actuator system or mechanism controls orienting of the lift-producing surfaces, such as tilting of the lift producing surfaces, to direct the collar into a desired position relative to a longitudinal axis of the projectile, and to maintain the collar in that position. With such a control the projectile is able to be steered using bank-to-turn maneuvering. The actuator system may use any of a variety of mechanisms to move the lift-producing surfaces, thereby positioning the collar.
摘要翻译：具有以其轴线旋转的旋转或滚动机身的抛射体，机动车辆或潜水艇具有可以使用空气动力力相对于射弹的纵向轴线定位的轴环。空气动力学表面，例如提升产生表面，例如尾部或者尾部，联接到套环上，并与套环一起旋转。致动器系统或机构控制提升产生表面的定向，例如提升产生表面的倾斜，以将轴环引导到相对于抛射体的纵向轴线的期望位置，并将轴环保持在该位置。有了这样的控制，射弹能够使用银行对转机动来引导。致动器系统可以使用各种机构中的任一种来移动提升产生表面，从而定位套环。

5. 发明授权

US08212195B2 Projectile with inertial measurement unit failure detection 有权
标题翻译：具有惯性测量单元故障检测的抛射体
公开(公告)号：US08212195B2
公开(公告)日：2012-07-03
申请号：US13235246
申请日：2011-09-16
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： F41G7/36 , F42B15/01 , F41G7/00 , F42B15/00
CPC分类号： F42B15/01 , F42B10/62
摘要： A guided projectile may include a projectile body. An inertial measurement unit may be disposed within the projectile body, the inertial measurement unit including sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes. Each of the first, second, and third mutually orthogonal axes may form an oblique angle with a longitudinal axis of the projectile body. A controller may be configured to control a trajectory of the guided projectile in response, at least in part, to measurement data received from the inertial measurement unit.
摘要翻译：引导弹丸可能包括射弹体。惯性测量单元可以设置在射弹体内，惯性测量单元包括用于测量相对于第一，第二和第三相互正交轴线的运动参数的传感器。第一，第二和第三相互正交的轴中的每一个可以与射弹体的纵向轴线形成倾斜的角度。控制器可以被配置为至少部分地响应于从惯性测量单元接收的测量数据来控制被引导的射弹的轨迹。

6. 发明授权

US08071928B2 Projectile with filler material between fins and fuselage 有权
标题翻译：飞机与飞翼与机身之间的填充材料
公开(公告)号：US08071928B2
公开(公告)日：2011-12-06
申请号：US12257699
申请日：2008-10-24
申请人： Chris E. Geswender , Shawn B. Harline , Nicholas E. Kosinski
发明人： Chris E. Geswender , Shawn B. Harline , Nicholas E. Kosinski
IPC分类号： F42B15/01
CPC分类号： F42B10/16
摘要： A projectile has filler material placed between an outer surface of its fuselage, and fins that are hingedly coupled to the fuselage. The filler material fills space that otherwise would be occupied by pressurized gases. Such pressurized gases could cause undesired outward force against the projectile fins during launch of the projectile from a launch tube or gun, such as when pressure outside the fins is suddenly removed, as in when the projectile passes a muzzle brake in the launch tube. The filler material may be any of a variety of lightweight solid materials, such as suitable plastics or closed cell foams. The filler material prevents pressurized gases from entering at least some of the space between the fins and the outer fuselage surface. When the fins deploy after the projectile emerges from the launch tube the filler material pieces fall away harmlessly.
摘要翻译：抛射体具有放置在其机身的外表面之间的填充材料和铰接到机身的翅片。填充材料填充否则将被加压气体占据的空间。这样的加压气体可能在从发射管或喷枪发射抛射物时引起对弹丸的不期望的向外的力，例如当突出部分的翅片外部的压力被突然移除时，如在射弹通过发射管中的枪口制动器时。填充材料可以是各种轻质固体材料中的任何一种，例如合适的塑料或闭孔泡沫。填充材料防止加压气体进入翅片和外部机身表面之间的至少一些空间。当射弹从发射管出来时，翅片部署，填充材料片无害化掉。

7. 发明授权

US08558153B2 Projectile with inertial sensors oriented for enhanced failure detection 有权
标题翻译：具有惯性传感器的抛射体，用于增强故障检测
公开(公告)号：US08558153B2
公开(公告)日：2013-10-15
申请号：US12359156
申请日：2009-01-23
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： F42B15/01 , F42B10/62 , F42B15/00 , F42B10/00
CPC分类号： F42B15/01 , F42B10/62
摘要： A guided projectile may include a projectile body, an inertial measurement unit disposed within the projectile body, one or more control surfaces extendable from the projectile body, and a controller which controls the one or more control surfaces in response, at least in part, to measurement data received from the inertial measurement unit. The inertial measurement unit may include sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes, wherein each of the first, second and third mutually orthogonal axes is oblique to a longitudinal axis of the projectile body.
摘要翻译：引导射弹可以包括抛射体，设置在射弹体内的惯性测量单元，可从射弹体延伸的一个或多个控制表面，以及一个控制器，该控制器至少部分响应地控制一个或多个控制表面从惯性测量单元接收的测量数据。惯性测量单元可以包括用于测量相对于第一，第二和第三相互正交的轴的运动参数的传感器，其中第一，第二和第三相互正交的轴中的每一个相对于射弹体的纵向轴线倾斜。

8. 发明授权

US08426788B2 Guidance control for spinning or rolling projectile 有权
标题翻译：旋转或滚动抛射体的引导控制
公开(公告)号：US08426788B2
公开(公告)日：2013-04-23
申请号：US13005175
申请日：2011-01-12
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： F42B10/64 , F42B10/26
CPC分类号： F42B15/01 , F42B10/06 , F42B10/64
摘要： A projectile, air vehicle or submersible craft with a spinning or rolling fuselage, rotating on its axis, has a collar which can be positioned relative to a longitudinal axis of the projectile using aerodynamic forces. Aerodynamic surfaces, such as lift-producing surfaces, for example tails or canards, are coupled to the collar, and rotate with the collar. An actuator system or mechanism controls orienting of the lift-producing surfaces, such as tilting of the lift producing surfaces, to direct the collar into a desired position relative to a longitudinal axis of the projectile, and to maintain the collar in that position. With such a control the projectile is able to be steered using bank-to-turn maneuvering. The actuator system may use any of a variety of mechanisms to move the lift-producing surfaces, thereby positioning the collar.
摘要翻译：具有以其轴线旋转的旋转或滚动机身的抛射体，机动车辆或潜水艇具有可以使用空气动力力相对于射弹的纵向轴线定位的轴环。空气动力学表面，例如提升产生表面，例如尾部或者尾部，联接到套环上，并与套环一起旋转。致动器系统或机构控制提升产生表面的定向，例如提升产生表面的倾斜，以将轴环引导到相对于抛射体的纵向轴线的期望位置，并将轴环保持在该位置。有了这样的控制，射弹能够使用银行对转机动来引导。致动器系统可以使用各种机构中的任一种来移动提升产生表面，从而定位套环。

9. 发明申请

US20130092790A1 FIN DEPLOYMENT METHOD AND APPARATUS 有权
标题翻译： FIN部署方法和装置
公开(公告)号：US20130092790A1
公开(公告)日：2013-04-18
申请号：US13274426
申请日：2011-10-17
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： B64F1/04 , F41B11/00
CPC分类号： F42B10/14 , F41A21/32 , F41A21/46
摘要： An air vehicle that is launched from inside a launcher, includes a release mechanism for releasing fins of the vehicle from a stowed condition to a deployed condition. The release mechanism includes a pin that is located within a cavity in the fuselage of the air vehicle. Pressurized gasses initially fill the cavity in the fuselage. The launcher includes a reduced-pressure portion such as from a muzzle brake. When the air vehicle passes into the reduced-pressure portion of the launcher, the gas pressure behind the air vehicle is reduced. This causes the pressurized gas within the cavity to drive the release mechanism backwards out of the cavity. The length of the pin may be used to control the timing of the fin deployment, the delay between the initial movement of the release mechanism out of the cavity, and when the fins are released.
摘要翻译：从发射器内部发射的空中车辆包括用于将车辆的散热片从收起状态释放到展开状态的释放机构。释放机构包括位于机动车辆的机身中的空腔内的销。加压气体最初填充机身中的空腔。发射器包括诸如从枪口制动器的减压部分。当机动车辆进入发射器的减压部分时，空中车辆后面的气体压力减小。这使得空腔内的加压气体向后驱动释放机构。销的长度可以用于控制翅片展开的时间，释放机构的初始移动到空腔之间以及当翅片被释放时的延迟。

10. 发明申请

US20120025008A1 Projectile With Inertial Measurement Unit Failure Detection 有权
标题翻译：具有惯性测量单元故障检测的抛射体
公开(公告)号：US20120025008A1
公开(公告)日：2012-02-02
申请号：US13235246
申请日：2011-09-16
申请人： Chris E. Geswender
发明人： Chris E. Geswender
IPC分类号： F42B15/01
CPC分类号： F42B15/01 , F42B10/62
摘要： A guided projectile may include a projectile body. An inertial measurement unit may be disposed within the projectile body, the inertial measurement unit including sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes. Each of the first, second, and third mutually orthogonal axes may form an oblique angle with a longitudinal axis of the projectile body. A controller may be configured to control a trajectory of the guided projectile in response, at least in part, to measurement data received from the inertial measurement unit.
摘要翻译：引导弹丸可能包括射弹体。惯性测量单元可以设置在射弹体内，惯性测量单元包括用于测量相对于第一，第二和第三相互正交轴线的运动参数的传感器。第一，第二和第三相互正交的轴中的每一个可以与射弹体的纵向轴线形成倾斜的角度。控制器可以被配置为至少部分地响应于从惯性测量单元接收的测量数据来控制被引导的射弹的轨迹。

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