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1. 发明申请

WO2007044977A2 EXHAUST ASSEMBLY FOR MASS EJECTION DRIVE SYSTEM 审中-公开
标题翻译：用于质量喷射驱动系统的排气组件
公开(公告)号：WO2007044977A2
公开(公告)日：2007-04-19
申请号：PCT/US2006/040482
申请日：2006-10-14
申请人： RAYTHEON COMPANY , MELKERS, Edgar, R. , EISENTRAUT, Rudy , STRASSMAN, Doron
发明人： MELKERS, Edgar, R. , EISENTRAUT, Rudy , STRASSMAN, Doron
IPC分类号： F02C9/00
CPC分类号： F02K1/78 , F02K9/97 , F05D2250/31 , F42B10/16 , F42B10/28 , F42B10/665
摘要： The present invention discloses a system, device and method for providing an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tailfin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.
摘要翻译：本发明公开了一种用于提供排气组件的系统，装置和方法，所述排气组件适于与大容量排出驱动系统一起使用以产生围绕所述驱动系统的主轴的旋转扭矩。代表性特征通常包括叶片，该叶片被适当地构造成至少部分地接合质量喷射物流以施加围绕驱动系统的主轴线的净旋转扭矩，以及联接至该至少一个叶片的尾翼。尾翼被构造成从至少部分收起的位置选择性地展开，以减少围绕驱动系统的主轴线施加净旋转扭矩。

2. 发明申请

WO2010074780A2 MULTI-STAGE HYPER-VELOCITY KINETIC ENERGY MISSILE 审中-公开
标题翻译：多级高速动力能量失效
公开(公告)号：WO2010074780A2
公开(公告)日：2010-07-01
申请号：PCT/US2009/057880
申请日：2009-09-22
申请人： RAYTHEON COMPANY , STRASSMAN, Doron , JANIK, Richard
发明人： STRASSMAN, Doron , JANIK, Richard
IPC分类号： F42B12/06 , F42B15/10
CPC分类号： F42B12/06 , F41G7/32 , F42B12/625 , F42B15/01 , F42B15/04
摘要： A multi-stage hyper-velocity kinetic energy missile (HVKEM) uses a 'missile in a missile' architecture in which the HVKEM includes a 1st stage flight missile and a 2nd stage kill missile that includes a KE-rod penetrator. The flight missile cruises at a relatively low velocity (less than Mach 1.5, typically less than Mach 1) to conserve propellant (weight) and to allow for effective guidance and maneuvering until the missile is in close proximity to the target. When the missile is within the lethal range of the KE- rod penetrator, the kill missile separates and boosts to a much higher velocity (greater than Mach 3, typically greater than Mach 5) and flies unguided to impact the target in less than a second. Waiting to boost the KE-rod until "the last second" reduces the total propellant (weight) needed to deliver the KE-rod on target and simplifies the guidance. The missile may be configured for use with different platforms and different guidance systems but is particularly well suited for use with the existing base of TOW launch containers and platforms satisfying all of the physical, operational and CLOS guidance constraints while maintaining the performance of the KE-rod penetrator.
摘要翻译：多级高速动能导弹（HVKEM）使用“导弹”导弹，其中HVKEM包括第一级飞行导弹和第二级杀伤导弹，其中包括一个KE杆穿透器。飞行导弹以相对较低的速度（小于马赫1.5，通常小于马赫数1）巡航，以节省推进剂（重量），并允许有效的引导和机动，直到导弹靠近目标。当导弹处于KE-杆穿透器的致命范围内时，杀死导弹分离并提升到更高的速度（大于马赫数3，通常大于马赫5），并且在不到一秒的时间内不引导飞行以撞击目标。等待提升KE杆直到“最后一秒”减少了将KE杆放在目标上所需的总推进剂（重量），并简化了指导。导弹可以配置为用于不同的平台和不同的导向系统，但特别适用于现有的TOW发射容器和平台的基础，满足所有的物理，操作和CLOS指导约束，同时保持KE- 杆穿透器。

3. 发明公开

EP2329216A2 MULTI-STAGE HYPER-VELOCITY KINETIC ENERGY MISSILE 有权
标题翻译：多级平衡地板HYPER声速
公开(公告)号：EP2329216A2
公开(公告)日：2011-06-08
申请号：EP09822879.4
申请日：2009-09-22
申请人： Raytheon Company
发明人： STRASSMAN, Doron , JANIK, Richard
IPC分类号： F42B12/06 , F42B15/01
CPC分类号： F42B12/06 , F41G7/32 , F42B12/625 , F42B15/01 , F42B15/04
摘要： A multi-stage hyper-velocity kinetic energy missile (HVKEM) uses a 'missile in a missile' architecture in which the HVKEM includes a 1st stage flight missile and a 2nd stage kill missile that includes a KE-rod penetrator. The flight missile cruises at a relatively low velocity (less than Mach 1.5, typically less than Mach 1) to conserve propellant (weight) and to allow for effective guidance and maneuvering until the missile is in close proximity to the target. When the missile is within the lethal range of the KE- rod penetrator, the kill missile separates and boosts to a much higher velocity (greater than Mach 3, typically greater than Mach 5) and flies unguided to impact the target in less than a second. Waiting to boost the KE-rod until "the last second" reduces the total propellant (weight) needed to deliver the KE-rod on target and simplifies the guidance. The missile may be configured for use with different platforms and different guidance systems but is particularly well suited for use with the existing base of TOW launch containers and platforms satisfying all of the physical, operational and CLOS guidance constraints while maintaining the performance of the KE-rod penetrator.

4. 发明授权

EP2329216B1 MULTI-STAGE HYPER-VELOCITY KINETIC ENERGY MISSILE 有权
标题翻译：多级平衡地板HYPER声速
公开(公告)号：EP2329216B1
公开(公告)日：2016-04-06
申请号：EP09822879.4
申请日：2009-09-22
申请人： Raytheon Company
发明人： STRASSMAN, Doron , JANIK, Richard
IPC分类号： F42B12/06 , F42B12/62 , F42B15/01 , F42B15/04 , F41G7/32
CPC分类号： F42B12/06 , F41G7/32 , F42B12/625 , F42B15/01 , F42B15/04

5. 发明授权

EP1934547B1 EXHAUST ASSEMBLY FOR MASS EJECTION DRIVE SYSTEM 有权
标题翻译：面向大规模排放出口组件驱动系统
公开(公告)号：EP1934547B1
公开(公告)日：2012-12-12
申请号：EP06826075.1
申请日：2006-10-13
申请人： Raytheon Company
发明人： MELKERS, Edgar, R. , EISENTRAUT, Rudy , STRASSMAN, Doron
IPC分类号： F42B10/00 , F42B10/16 , F42B10/28 , F02K9/97 , F02K1/78
CPC分类号： F02K1/78 , F02K9/97 , F05D2250/31 , F42B10/16 , F42B10/28 , F42B10/665

6. 发明公开

EP1934547A2 EXHAUST ASSEMBLY FOR MASS EJECTION DRIVE SYSTEM 有权
标题翻译：面向大规模排放出口组件驱动系统
公开(公告)号：EP1934547A2
公开(公告)日：2008-06-25
申请号：EP06826075.1
申请日：2006-10-13
申请人： Raytheon Company
发明人： MELKERS, Edgar, R. , EISENTRAUT, Rudy , STRASSMAN, Doron
IPC分类号： F42B10/00
CPC分类号： F02K1/78 , F02K9/97 , F05D2250/31 , F42B10/16 , F42B10/28 , F42B10/665
摘要： The present invention discloses a system, device and method for providing an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tailfin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.

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