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1. 发明授权

US10914551B2 Vehicle device separation system with telescoping piston springs 有权
公开(公告)号：US10914551B2
公开(公告)日：2021-02-09
申请号：US16217766
申请日：2018-12-12
申请人： Raytheon Company
发明人： Philip Wright , Jayson Kahle Bopp , Stephen A. Streib , Brian R. Kavalar
IPC分类号： F41F3/06 , F41F5/00
摘要： An ejector system for ejecting/separating a store, such as a weapon, from a launch platform includes a pair of spring assemblies that each include nested springs that are contained in a housing when the spring assemblies are in a compressed configuration. To separate the store from the aircraft the spring assemblies each move from the initial compressed configuration to an extended configuration, using the potential energy stored in the springs when compressed. The extension of the springs extends the springs mostly out of the spring assembly housings, extending telescoped sleeves of the spring assemblies. The extension of the spring assemblies provides a safe and steady way of separating the store from the launch platform, while having the advantages of being reusable, low cost and low weight, not producing any debris, and providing a softer push than may be produced by other separation mechanisms, such as the use of pyrotechnic devices.

2. 发明授权

US10240896B2 Tube to bulkhead bonded joint design 有权
公开(公告)号：US10240896B2
公开(公告)日：2019-03-26
申请号：US14656128
申请日：2015-03-12
申请人： Raytheon Company
发明人： Orlando L. Mijares , Keith A. Elkins , Jack W. Reany
IPC分类号： F41F3/042 , F16L37/00 , F41F3/06 , F41F3/065 , F16B11/00 , F41F3/073
摘要： A tube to bulkhead joint is provided. The joint includes a bulkhead defining an aperture and comprising an interior facing sidewall at the aperture, a tubular element, which is insertible into the aperture, the tubular element including an end sized to fit into the aperture and slotted to form multiple deflectable fingers, and adhesive disposable between at least the multiple deflectable fingers and the interior facing sidewall of the aperture.

3. 发明授权

US09783296B2 Aircraft store deployment system with improved safety of arming and releasing stores 有权
公开(公告)号：US09783296B2
公开(公告)日：2017-10-10
申请号：US14532121
申请日：2014-11-04
申请人： Raytheon Company
发明人： Michael S. Ray , Armando Guerrero
IPC分类号： B64D7/08 , B64D1/06 , F41F3/06 , B64D1/04
CPC分类号： B64D1/06 , B64D1/04 , B64D7/08 , F41F3/06
摘要： A deployment system for deploying a store from an aircraft includes a lock member that selectively engages the store to the deployment system, an ejector that selectively ejects the store from the deployment system, and a deployment system controller communicatively coupled to the lock member and to the ejector, the system controller communicatively coupled to the aircraft to receive commands from the aircraft, wherein upon receipt of a master arm command from the aircraft the system controller maintains the lock member in an engaged state relative to the store, and wherein upon receipt of a fire command from the aircraft the system controller disengages the lock member from the store and activates the ejector to eject the store from the deployment system.

4. 发明申请

US20150122113A1 Guidance Section Connector Interface for Advanced Rocket Launchers 有权
标题翻译：高级火箭发射器的导引部分连接器接口
公开(公告)号：US20150122113A1
公开(公告)日：2015-05-07
申请号：US14070250
申请日：2013-11-01
申请人： Raytheon Company
发明人： Roy P. McMahon , Michael R. Hlavek
IPC分类号： F41F3/055 , F42B15/01 , F41F3/06
CPC分类号： F41F3/055 , B64G1/645 , F41F3/06 , F42B15/01
摘要： A guidance section connector interface system operable with smart or guided rockets to be launched from a rocket launcher comprising a rocket connector of a rocket in electronic communication with a guidance system of a guidance head of the rocket, a connector saver, and a launcher connector of a rocket launcher. The connector saver can be configured to connect the rocket connecter to the launcher connector. The connection between the connector saver and the rocket connector is configured to release upon launching the rocket, wherein the connector saver remains connected to the launcher connector to protect the launcher connector from the extreme conditions within the rocket launcher at launch.
摘要翻译：引导部分连接器接口系统，其可操作的智能或引导火箭从火箭发射器发射，所述火箭发射器包括与火箭的引导头的引导系统电子通信的火箭的火箭连接器，连接器保护器和发射器连接器一个火箭发射器。连接器保护程序可以配置为将火箭连接器连接到发射器连接器。连接器保护器和火箭连接器之间的连接被配置为在发射火箭时释放，其中连接器保护器保持连接到发射器连接器，以在发射时保护发射器连接器免受火箭发射器内的极端条件的影响。

5. 发明授权

US08281697B2 Method for launching naval mines 有权
标题翻译：发射海军的方法
公开(公告)号：US08281697B2
公开(公告)日：2012-10-09
申请号：US13235770
申请日：2011-09-19
申请人： Thomas H. McCants, Jr.
发明人： Thomas H. McCants, Jr.
IPC分类号： F41F5/00 , F41F3/06
CPC分类号： F41F3/06 , B64D1/04 , F41F3/042 , F41F3/073
摘要： An air-based vertical launch system is described by means of which ballistic missile defense can be achieved effectively from a large aircraft. A method for ensuring safe missile egress is proposed. A method for ensuring that the missile strikes the ballistic missile payload section is also proposed. Together, the air basing method employing vertical (or near-vertical) launch and semi-active laser guidance yield an affordable and operationally effective missile defense against both tactical and long-range ballistic missiles. The affordability of missile defense is enhanced by the ability of an aircraft equipped with a vertical launcher to simultaneously carry out several defensive and offensive missions and to provide other capabilities such as satellite launch at other times. Methods for employing an aircraft equipped with a vertical (or near-vertical launcher) and one or more of the proposed egress assurance mechanisms in offensive ground attack missions, mine laying, and satellite launch missions are also proposed.
摘要翻译：通过这种方式，可以从大型飞机上有效地实现弹道导弹防御的空中垂直发射系统。提出了一种确保安全导弹出口的方法。还提出了一种确保导弹撞击弹道导弹有效载荷部分的方法。使用垂直（或近垂直）发射和半主动激光制导的空气基础方法一起为战术和远程弹道导弹提供了经济实惠和有效的导弹防御。导弹防御的负担能力由配备垂直发射器的飞机同时进行若干防御和进攻任务的能力提高，并提供其他能力，如其他时间的卫星发射。还提出了使用装备垂直（或近垂直发射器）的飞机和进攻地面攻击任务，排雷和卫星发射任务中提出的一个或多个出口保证机制的方法。

6. 发明申请

US20100320312A1 MINIATURE MISSILE 有权
标题翻译：微型MISSILE
公开(公告)号：US20100320312A1
公开(公告)日：2010-12-23
申请号：US12377604
申请日：2007-08-16
申请人： Yariv Bril , Yakov Hetz , Oded Yehezkeli , Ehud Chishinsky
发明人： Yariv Bril , Yakov Hetz , Oded Yehezkeli , Ehud Chishinsky
IPC分类号： F42B15/01 , F41G7/00 , F42B10/00 , G06F19/00 , F41F3/04 , F41F3/045 , F41F3/06
CPC分类号： F42B15/00 , F41G7/008 , F41G7/2206 , F41G7/2213 , F41G7/2253 , F41G7/2293
摘要： A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.
摘要翻译：微型轻型高机动导弹（10）具有导弹体（12），具有三组至少两个气动控制表面（14,16,18），用于独立控制导弹的滚动，俯仰和偏航。每组控制表面（14,16,18）由部署在导弹体（12）内的对应致动器（20）独立地控制。其他优选特征包括选择目标处的高度入射角，以及在爆炸和动力学操作模式之间切换。

7. 发明授权

US5970842A Hanger assembly for missiles 失效
标题翻译：导弹用吊架总成
公开(公告)号：US5970842A
公开(公告)日：1999-10-26
申请号：US58216
申请日：1998-04-10
申请人： Klaus-Dieter Knapp , Peter Gerd Fisch , Dirk Bross
发明人： Klaus-Dieter Knapp , Peter Gerd Fisch , Dirk Bross
IPC分类号： B64D1/04 , B64D7/08 , F41F3/04 , F41F3/06
CPC分类号： B64D1/04 , B64D7/08 , F41F3/0406
摘要： A hanger assembly for missiles, in which a hanger, with opposite carrying rails to guide the missile in a launcher, is connected to the missile by means of a screwed connection. The hanger is screwed from the outside, with screws to a enlargement or increased thickness portion (16,60). Preferably a clamp, provided with a enlargement or increased thickness portion surrounds the airframe (Zelle) of the missile and is fixed thereto. The screw connection of the hanger is effected with screws the axes of which form an angle with the plane of the carrying rails.
摘要翻译：用于导弹的吊架组件，其中具有相对的承载导轨以将导弹引导到发射器中的悬挂架通过螺纹连接连接到导弹。衣架从外部拧紧，用螺钉拧紧，以扩大或增加厚度部分（16,60）。优选地，设置有放大或增加的厚度部分的夹具围绕导弹的机身（Zelle）并且固定到其上。悬挂器的螺钉连接通过其轴线与承载轨道的平面形成一角度的螺钉来实现。

8. 发明授权

US5614896A Method and system for aircraft weapon station testing 失效
标题翻译：飞机武器站测试方法和系统
公开(公告)号：US5614896A
公开(公告)日：1997-03-25
申请号：US409106
申请日：1995-03-23
申请人： R. Winston Monk , David P. Van Cleve
发明人： R. Winston Monk , David P. Van Cleve
IPC分类号： F41A31/00 , B64D7/08 , B64F5/00 , F41F3/06 , F41G7/00 , G08B21/00
CPC分类号： F41G7/006
摘要： A weapon station testing system for testing the mission readiness of an aircraft (10) having a plurality of weapon stations including a first weapon station (12a) and a second weapon station (12b) comprises a common electronics module (14) and a plurality of interchangeable mechanical fixtures (16a, 16b). A first interchangeable fixture (16a) is operative for interconnecting the common electronics module (14) with the first weapon station (12a). A second interchangeable fixture (16b) is operative for interconnecting the common electronics module (14) with the second weapon station (12b).
摘要翻译：一种用于测试具有包括第一武器站（12a）和第二武器站（12b）在内的多个武器站的飞机（10）的任务准备的武器站测试系统包括公共电子模块（14）和多个可互换的机械夹具（16a，16b）。第一可互换固定装置（16a）用于将共用电子模块（14）与第一武器站（12a）互连。第二可互换夹具（16b）用于将共用电子模块（14）与第二武器站（12b）互连。

9. 发明授权

US5291820A Inertial restraint mechanism for rail-mounted missiles 失效
标题翻译：轨道导弹惯性约束机制
公开(公告)号：US5291820A
公开(公告)日：1994-03-08
申请号：US988612
申请日：1992-12-10
申请人： Barton J. Hainsworth , Anton J. Kompare
发明人： Barton J. Hainsworth , Anton J. Kompare
IPC分类号： F41F3/052 , F41F3/06
CPC分类号： F41F3/052
摘要： An inertial restraint mechanism restrains a rail mounted missile against forward movement along a missile launch rail in response to a deceleration force. The restraint mechanism comprises a mass the movement of which is opposed by a spring force. When the mass overcomes the spring force due to a deceleration force in excess of a threshold magnitude, a locking mechanism is activated to a missile restraining position, thereby restraining the missile against forward movement. The restraint mechanism is locked in the missile restraining position to prevent release of a missile in response to multiple deceleration forces experienced by the missile and launch rail. Additionally, a detent may be provided which prevents actuation of the restraint mechanism to the missile restraining position unless the missile is stored in a storage compartment.
摘要翻译：惯性约束机制限制轨道安装的导弹，以响应于减速力沿着导弹发射轨向前运动。约束机构包括其运动由弹簧力相反的质量。当质量克服由于超过阈值大小的减速力引起的弹簧力时，锁定机构被激活到导弹限制位置，从而限制导弹向前移动。限制机制锁定在导弹限制位置，以防止导弹和导弹经受的多重减速力的弹力释放。此外，可以设置制动器，其防止约束机构致动到导弹限制位置，除非导弹被存储在储藏室中。

10. 发明授权

US4842218A Pivotal mono wing cruise missile with wing deployment and fastener mechanism 失效
标题翻译： Pivotal单翼巡航导弹与翼部署和紧固机构
公开(公告)号：US4842218A
公开(公告)日：1989-06-27
申请号：US159423
申请日：1988-02-08
申请人： Frederick D. Groutage , Samuel N. Conjerti , Lockburn S. Shaw
发明人： Frederick D. Groutage , Samuel N. Conjerti , Lockburn S. Shaw
IPC分类号： B64C39/02 , F41F3/06 , F42B10/14
CPC分类号： F41F3/06 , B64C39/024 , F42B10/14
摘要： A moveable wing aircraft including a quick release, attachment mechanism carrying the aircraft on a bomb rack or other carrier and a mechanism for deploying the moveable wing from its captive carry position to its extended free flight position are disclosed. The aircraft includes an elongate fuselage, a portion of the top surface of which is substantially flat in order to accommodate the moveable wing. The moveable wing is positional between a captive carry position in which it is aligned with the longitudinal axis of the fuselage and an extended free flight position. The single, moveable wing is pivoted around a central point from its captive carry position to its extended free flight position such that it is substantially perpendicular to the aircraft fuselage. The quick release mechanism extends through apertures in the wing in its captive carry position and is spring biased to retract through the wing and into the aircraft fuselage when released from the bomb rack or other carrier. The deployment mechanism includes a spring loaded cable and pulley arrangement and serves to connect the moveable wing to the fuselage and to bias it from its captive carry position to its extended free flight position when activated upon release of the quick release mechanism.
摘要翻译：公开了一种可移动翼飞机，其包括用于将飞机运载在炸弹架或其他载体上的快速释放，附接机构和用于将可动翼从其捕获携带位置展开到其延伸的自由飞行位置的机构。飞行器包括细长机身，其顶表面的一部分基本上是平坦的，以便容纳可动翼。可移动机翼位于被夹持的携带位置之间，其中其与机身的纵向轴线对齐并具有延长的自由飞行位置。单个可动翼围绕中心点从其捕获携带位置枢转到其延伸的自由飞行位置，使得其基本上垂直于飞行器机身。快速释放机构延伸穿过机翼中的孔，处于其自身携带位置，并且当从炸弹架或其他载体释放时，弹簧偏置以缩回通过机翼并进入飞机机身。展开机构包括弹簧加载的电缆和滑轮装置，并用于将可移动的翼连接到机身，并且在释放快速释放机构时被激活时将其从其自身携带位置偏置到其延伸的自由飞行位置。

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