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. 发明申请

US20170138310A1 AEROSPIKE ROCKET MOTOR ASSEMBLY 审中-公开
公开(公告)号：US20170138310A1
公开(公告)日：2017-05-18
申请号：US14938952
申请日：2015-11-12
申请人： Raytheon Company
发明人： James Kendall Villarreal , Mark T. Langhenry , Jeremy C. Danforth
IPC分类号： F02K9/97 , F42B15/01 , F42B15/36 , F02K9/95 , F42B15/10
CPC分类号： F02K9/97 , F02K9/10 , F02K9/18 , F02K9/24 , F02K9/34 , F02K9/36 , F02K9/90 , F02K9/95 , F02K9/978 , F41A1/00 , F41F3/04 , F41F3/0413 , F42B15/00 , F42B15/01 , F42B15/10 , F42B15/105 , F42B15/36 , F42B30/08 , F42B30/10 , F42B30/12
摘要： A motor assembly is provided for use with projectiles, such as munitions, having relatively low length to diameter ratios. The motor assembly has an aerospike nozzle and a casing disposed about the aerospike nozzle, where interior aerospike volume contains propellant and where walls of both the cowl of the casing and of the aerospike nozzle jointly define a combustion chamber.

2. 发明申请

US20150175278A1 GAS GUN LAUNCHER 有权
公开(公告)号：US20150175278A1
公开(公告)日：2015-06-25
申请号：US14642720
申请日：2015-03-09
申请人： QUICKLAUNCH, INC.
发明人： John William HUNTER , Harry E. CARTLAND , Philip James SLUDER , Richard Edward TWOGOOD
IPC分类号： B64G1/00 , F41B11/68 , F41B11/723 , F41F1/00
CPC分类号： B64G1/002 , B64G5/00 , F41A1/02 , F41B11/60 , F41B11/68 , F41B11/723 , F41F1/00 , F41F3/04 , F41F3/0413 , F41F3/077 , F42B10/26 , F42B10/66 , F42B14/06 , F42B15/00
摘要： A gas gun launcher has a pump tube and a launch tube with a first end of the launch tube slidably inserted into a second end of the pump tube. The pump tube may hold a heat exchanger to heat a light gas used to launch a vehicle. A sliding seal can be employed to manage recoil and to retain the gas within the launch tube and the pump tube. A fast-closing muffler at the second end of the launch tube can conserve the light gas utilized for launching a vehicle, enabling the light gas to be recycled. A launch tube alignment system is preferably automatic, ensuring the survival of the launch vehicle.

3. 发明申请

US20120152090A1 Self-Contained Munition Gas Management System 有权
标题翻译：自备军火气体管理系统
公开(公告)号：US20120152090A1
公开(公告)日：2012-06-21
申请号：US12862287
申请日：2010-08-24
申请人： Daniel A. Skurdal , John Snediker
发明人： Daniel A. Skurdal , John Snediker
IPC分类号： F41F3/073
CPC分类号： F41F3/0413 , F41F3/073
摘要： An apparatus is disclosed that is a self-contained gas management system (hereinafter “GMS”) that accommodates individual canisters of highly energetic small munitions, but is not so limited. By decoupling the gas management system for a given munition from an adjacent munition, the risk of downing a multi-pack launcher or munition adapter is reduced. Thermal wear, overheating, restrained firing and aft closure debris can be isolated through the separation of gas management systems. In addition, the GMS allows for ease of replenishment and maintenance of a given sub-cell of a multi-pack system. The GMS works with existing munitions and canisters without the need to modify them. Each GMS is dimensioned to fit the canistered munition it receives as well as the launch system with which it is used. The illustrative GMS comprises a plenum, and a first and a second uptake structure. The plenum receives the exhaust from the canistered munition when the munition fires. The plenum is fluidically coupled to the first and second uptake structures. The uptake structures in the illustrative embodiment receive the missile exhaust from the plenum and vent the exhaust to the atmosphere. In the illustrative embodiment, the first and second uptake structures are disposed along opposite sides of the canistered munition, flanking it.
摘要翻译：公开了一种装置，其是容纳高能量小弹药的各个罐的独立气体管理系统（以下称为“GMS”），但不限于此。通过将给定弹药的天然气管理系统与相邻的弹药解耦，减少多包发射器或弹药适配器的风险。通过气体管理系统的分离，可以隔离热磨损，过热，约束的点火和后盖碎片。此外，GMS允许容易地对多包系统的给定子单元进行补充和维护。 GMS与现有的弹药和罐一起工作，无需修改它们。每个GMS的尺寸都是为了适应它所接收的可燃弹药以及使用它的发射系统。示例性GMS包括增压室和第一和第二吸收结构。当弹药火灾时，全会收到了从弹药弹出的废气。气室与第一和第二吸收结构流体耦合。在说明性实施例中的摄取结构接收来自气室的导弹排气并将排气排放到大气中。在说明性实施例中，第一和第二摄取结构沿着它的侧翼的相对侧布置。

4. 发明申请

US20120104219A1 SYSTEM AND METHOD FOR SHOCK ISOLATION IN A LAUNCH SYSTEM 有权
标题翻译：发射系统中的震动隔离系统和方法
公开(公告)号：US20120104219A1
公开(公告)日：2012-05-03
申请号：US12715063
申请日：2010-03-01
申请人： William Kalms , Tejbir Arora , John Snediker
发明人： William Kalms , Tejbir Arora , John Snediker
IPC分类号： F16M11/20 , F16F7/00
CPC分类号： F41F3/073 , F41F3/0413 , F41F3/052
摘要： A system and method for providing a munitions launching system with dynamic shock isolation in which a spring plate skirt having an integral spring arrangement is provided between a munitions frame and a munitions extension, the spring plate skirt defining an opening that provides for the uninterrupted flow of expelled rocket gases, as well as underside access to the munitions frame.
摘要翻译：一种用于提供具有动态隔震的弹药发射系统的系统和方法，其中具有整体弹簧装置的弹簧板裙部设置在弹药框架和弹药延伸部之间，弹簧板裙部限定开口，该开口提供不间断的流动驱逐火箭气体，以及进入弹药框架的下方。

5. 发明申请

US20100236391A1 Housing-transportation-launch assembly for vertical-launch missiles, method of producing such an assembly, and ground missile launcher 有权
标题翻译：用于垂直发射导弹的住房运输发射组件，制造这种装置的方法和地面导弹发射器
公开(公告)号：US20100236391A1
公开(公告)日：2010-09-23
申请号：US11400017
申请日：2006-04-07
申请人： Bruno Baldi , Roberto De Girolamo , Teodoro Andrea Dragani , Sandro Mazzuca , Gian Fabrizio Venarucci
发明人： Bruno Baldi , Roberto De Girolamo , Teodoro Andrea Dragani , Sandro Mazzuca , Gian Fabrizio Venarucci
IPC分类号： F41F3/042 , F41F3/04
CPC分类号： F41F3/073 , F41F3/04 , F41F3/0413 , F41F3/042 , F41F3/052 , F41F3/077
摘要： In a ground launcher, two or more housing-transportation-launch assemblies for respective missiles are placed one on top of the other and connected releasably and interchangeably to each other; each housing-transportation-launch assembly has a respective outer casing, which in turn has longitudinal end walls breakable from inside the casing, and a deflecting body for deflecting the exhaust gas of the engine of the missile; a guide and protection assembly being interposed between the casing and the missile to guide the missile in the set launch direction, and to protect the missile against shock or vibration.
摘要翻译：在地面发射器中，用于各个导弹的两个或多个外壳运输发射组件一个放置在另一个的顶部上，并且彼此可释放地和互换地相连; 每个壳体运输发射组件具有相应的外壳，其又具有可从壳体内部破裂的纵向端壁和用于偏转导弹发动机的排气的偏转体; 引导和保护组件插入在外壳和导弹之间以在发射方向上引导导弹，并保护导弹免受冲击或振动。

6. 发明申请

US20060214062A1 Missile ejection system and launching canister thereof 有权
公开(公告)号：US20060214062A1
公开(公告)日：2006-09-28
申请号：US11169022
申请日：2005-06-28
申请人： Woo-Jeon Shim , Il-Soo Kim , Seung-Jong Oh , Jae-Hoon Ha , Ji-Chul Kim
发明人： Woo-Jeon Shim , Il-Soo Kim , Seung-Jong Oh , Jae-Hoon Ha , Ji-Chul Kim
IPC分类号： B64C1/22 , B64D1/08 , B64D9/00
CPC分类号： F41F3/0413 , F41F3/00 , F41F3/042 , F41F3/073 , F42B5/045 , F42B14/064
摘要： The present invention discloses a missile ejection system and a canister thereof. The missile ejection system comprises: comprising: a canister formed as a cylindrical shell, a partition wall protruding from an inner wall of the canister so as to divide the canister into a first chamber for housing a missile therewithin and a second chamber, and having at least one hole therethrough for allowing the flowing of gas through the partition wall, a gas generator secured to the partition wall in the second chamber so that a gas outlet thereof faces in an opposite direction from the first chamber, and an obturator including a sealing plate formed with a concave surface toward a fore-end of the missile for enclosing a tail end of the missile, and a radially extending skirt plate extended from the circumference of the sealing plate to the inner wall of the canister and inclined toward the fore-end of the missile for covering the space between the missile and the inner canister, wherein the missile is propelled by the pressure of the gas discharged out of the gas generator from the second chamber to the first chamber through the hole, being pressurized by the flown-in gas in the first chamber, pushing upon the obturator. Thereby, the system is able to effectively release a missile from a canister by a gas generator without using a missile propulsion engine, thereby fundamentally preventing the damage of ground equipments or peripheral missiles.

7. 发明授权

US4471684A Transom missile launcher module 失效
标题翻译：横渡导弹发射模块
公开(公告)号：US4471684A
公开(公告)日：1984-09-18
申请号：US301847
申请日：1981-09-14
申请人： Carl T. Johnson , Edward R. Betzold
发明人： Carl T. Johnson , Edward R. Betzold
IPC分类号： F41F3/04 , F41F3/077
CPC分类号： F41F3/0413 , F41F3/04 , F41F3/077
摘要： A transom missile launching system is configured to mount rigidly above the water line on the stern of ships designated to carry missile type ordnance. The missile launcher consists of two symmetrical modules containing eight missile cells each. Missiles are launched in the normal mode from a "all up round" canister at a fixed angle of about 60.degree. from a line athwartship both to port and to starboard. At this angle the probability of launch into a wave in heavy seas due to ship roll is eliminated. The missiles propulsion motor exhaust gases are vented directly overboard at launch without being directed either within the ship or across the weather deck. At ignition a water tight cover at the base of the launching chamber is blown directly overboard into the water by the exhaust gas pressure and a path is therefore provided for the exhaust gas to be discharged directly into the sea.
摘要翻译：艉翼导弹发射系统被配置为刚好安装在指定用于携带导弹型弹药的船舶船尾上的水线之上。导弹发射器由两个对称的模块组成，每个模块包含八个导弹单元。导弹以正常模式从“全方位”罐以60度左右的固定角度从一条直线到港口和右舷发射。在这个角度，消除了由于船运而在海洋中发射波浪的概率。导弹推进电机废气在发射时直接排放到外面，而不会在船内或穿过露天甲板上。在点火时，发射室底部的防水盖通过废气压力直接吹向水中，因此为排气直接排放到海中提供路径。

8. 发明授权

US4373420A Combustion suppressor 失效
标题翻译：燃烧抑制器
公开(公告)号：US4373420A
公开(公告)日：1983-02-15
申请号：US194533
申请日：1980-10-06
申请人： Edward T. Piesik
发明人： Edward T. Piesik
IPC分类号： F41F3/04
CPC分类号： F41F3/0413
摘要： Method and apparatus for preventing combustion of exhaust gases in rocket launch systems using a plurality of launch tubes connected to a plenum including pressure sensors in each launch tube, a control system sensitive to atmospheric pressure and launch tube pressure which provides a signal to an inert gas supply flow controller to initiate flow of gas into the plenum when pressure in a launch tube, after launch of a rocket, reaches a predetermined level.
摘要翻译：使用连接到包括每个发射管中的压力传感器的增压室的多个发射管来防止火箭发射系统中的废气燃烧的方法和装置，对大气压敏感的控制系统和向惰性气体提供信号的发射管压力供应流量控制器以在发射管中的发射管中的压力达到预定水平之后启动气体流入气室。

9. 发明授权

US4106389A Aircraft weapon mountings 失效
标题翻译：飞机武器装置
公开(公告)号：US4106389A
公开(公告)日：1978-08-15
申请号：US795626
申请日：1977-05-10
申请人： Gerald David Walley
发明人： Gerald David Walley
IPC分类号： B64D7/06 , F41A23/20 , F41F3/04 , F41F3/06
CPC分类号： B64D7/06 , F41A23/20 , F41F3/0413 , F41F3/06
摘要： An aircraft has a fuselage with a forward cockpit, an aft mounted fin, and an upper deck extending between the two, there being a weapon launcher assembly of elongated form with a forward end through which rocket propelled weapons are launched, a rearward end through which rocket exhaust is dissipated, and an upper deck extending between the two, the launcher being pivotable between a stowed position wherein it lies with its upper deck smoothly continuous with the upper deck of the fuselage and an extended weapon launch position wherein the weapons can be launched clear of the forward cockpit.
摘要翻译：一架飞机有一个机身与一个前驾驶舱，一个后安装的翅片和一个在两者之间延伸的上甲板，有一个伸长形式的武器发射组件，前端有一个火箭推进的武器，一个后端，火箭排气被消散，并且在两者之间延伸的上甲板，发射器可在收起位置之间枢转，其中它与其上甲板位于其机身的上甲板平滑连续并且延伸的武器发射位置，其中可以发射武器远离驾驶舱。

10. 发明授权

US3228294A Missile transporting and launching pad 失效
标题翻译：导弹运输和发射台
公开(公告)号：US3228294A
公开(公告)日：1966-01-11
申请号：US20844162
申请日：1962-07-09
申请人： AEROJET GENERAL CO
发明人： JACK HICKMAN
IPC分类号： F41F3/04
CPC分类号： F41F3/0413

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