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61. 发明授权

US5294078A Integrated system and method for assembling, and then transporting and supporting a launch vehicle 失效
标题翻译：集成系统和方法，用于组装，然后运输和支持运载火箭
公开(公告)号：US5294078A
公开(公告)日：1994-03-15
申请号：US909966
申请日：1992-07-07
申请人： John W. Gurr
发明人： John W. Gurr
IPC分类号： B64G5/00 , F41F3/04 , B64F1/04
CPC分类号： B64G5/00 , F41F3/04 , F41F3/0413
摘要： The system includes an assembly building of sufficient dimension to permit a launch vehicle to be vertically integrated within the building, and to simultaneously receive a combination launch pedestal-lift and transport unit within the building. The launch vehicle is vertically integrated within the building upon the pedestal, and then transported to the launch pad where the vertical height of the lift and transport unit is reduced, leaving the launch pedestal and vehicle in place at the launch pad. Various other features facilitate low cost launch programs using the system and method.
摘要翻译：该系统包括足够尺寸的组装建筑物，以允许运载工具垂直地集成在建筑物内，并且同时接收在建筑物内的组合发射基座升降机和运输单元。运载火箭在基座上垂直集成在建筑物内，然后运送到发射台，电梯和运输单元的垂直高度减小，将发射台和车辆放置在发射台上。各种其他功能便于使用系统和方法的低成本启动程序。

62. 发明授权

US5136922A Self-actuating rocket chamber closures for multi-missile launch cells 失效
标题翻译：用于多导弹发射电池的自动致动火箭筒闭合
公开(公告)号：US5136922A
公开(公告)日：1992-08-11
申请号：US698696
申请日：1991-05-13
申请人： Edward T. Piesik
发明人： Edward T. Piesik
IPC分类号： F41A13/00 , F41F3/04 , F41F3/077
CPC分类号： F41F3/0413
摘要： An exhaust gas management system for missile launch arrangements having multiple launch cells exhausting into a common plenum includes automatic aft closure members which serve to close off the flow passages to inactive cells while providing an open passage for exhaust gases from an active cell undergoing a missile firing. This arrangement prevents back flow or recirculation of exhaust gases into the volume in the cell which is upstream of the rocket nozzle exit.

63. 发明授权

US5012718A Impingement pressure regulator 失效
标题翻译：冲击压力调节器
公开(公告)号：US5012718A
公开(公告)日：1991-05-07
申请号：US412807
申请日：1989-09-27
申请人： Lee D. Miller
发明人： Lee D. Miller
IPC分类号： F41A1/00 , F41A21/28 , F41F3/04
CPC分类号： F41A1/00 , F41A21/28 , F41F3/0413
摘要： Apparatus for launching a projectile which has a nozzle for emitting gas during launch, said apparatus comprising means for supporting a projectile and a chamber having an orifice positioned to receive some or all of a jet from the projectile nozzle wherein the chamber is configured so that pressure is developed therein to provide an additional boost to the projectile during launch.

64. 发明授权

US4134327A Rocket launcher tube post-launch rear closure 失效
标题翻译：火箭发射管后发射后关闭
公开(公告)号：US4134327A
公开(公告)日：1979-01-16
申请号：US860039
申请日：1977-12-12
申请人： Edward T. Piesik
发明人： Edward T. Piesik
IPC分类号： F41F3/04 , F41F3/077
CPC分类号： F41F3/077 , F41F3/0413
摘要： A rear door for a rocket launch tube provided to prevent rocket exhaust gas flow into an empty launch tube from an associated multiple-rocket plenum chamber. The door is maintained in a stored position while a missile is in the launch tube and is activated when the missile leaves the launcher. The door may be latched open and released by a sensor device at a selected position of the missile as it is leaving the launch tube. Preferably, gases from the launching missile power closure of the door, once the door is released from its open latched position. Once the door closes, a second latch locks it in place to seal off the launch tube from the plenum chamber.
摘要翻译：用于火箭发射管的后门，用于防止火箭废气从相关联的多火箭增压室流入空的发射管。当导弹在发射管中时，门保持在存储位置，并且当导弹离开发射器时被激活。当导弹离开发射管时，门可以被锁定在导弹的选定位置处由传感器装置释放。优选地，一旦门从其打开的锁定位置释放，来自门的发射导弹动力闭合的气体。一旦门关闭，第二个闩锁将其锁定就位，以将发射管从增压室密封。

65. 发明授权

US3228296A Arrangement for venting blast gases and for water injection 失效
标题翻译：用于排放鼓风气体和注水的排列
公开(公告)号：US3228296A
公开(公告)日：1966-01-11
申请号：US28282263
申请日：1963-05-23
申请人： NEUMAN MILTON C , HOGEN ANTHONY J
发明人： NEUMAN MILTON C , HOGEN ANTHONY J
IPC分类号： F41F3/04
CPC分类号： F41F3/0413

66. 发明授权

US2998754A Missile launcher 失效
公开(公告)号：US2998754A
公开(公告)日：1961-09-05
申请号：US81698859
申请日：1959-05-29
申请人： BIALY KAROL J
发明人： BIALY KAROL J
IPC分类号： F41F3/04 , F41F3/073
CPC分类号： F41F3/073 , F41F3/0413

67. 发明授权

US09874420B2 Missile canister gated obturator 有权
公开(公告)号：US09874420B2
公开(公告)日：2018-01-23
申请号：US14586414
申请日：2014-12-30
申请人： BAE Systems Land & Armaments, L.P.
发明人： Mark J. Miller , Peter C. Woods
IPC分类号： F41F3/042 , F41F3/04
CPC分类号： F41F3/042 , F41F3/0413
摘要： Apparatus and methods relating to a missile canister that utilizes a variable obturator assembly. The variable obturator assembly can include a plurality of gates that adjust based upon canister pressure at a base plate. In a maximum pressure situation experienced during successful missile egress from the canister, one or more of the gates can open in response to canister flyout pressure so as to increase flow area through the base plate, thereby reducing canister pressure. In a restrained firing scenario, the plurality of gates remain closed thereby preventing missile exhaust gases from flow up past the base plate which could lead to heating of a rocket motor and warhead. The variable obturator assembly can have multiple individual gates that are mounted to the base plate with a hinge assembly, with the gates held in a closed position against the base plate with a spring assembly.

68. 发明申请

US20150053073A1 Multiple Missile Carriage and Launch Guidance Module 有权
标题翻译：多导弹运载和发射指导模块
公开(公告)号：US20150053073A1
公开(公告)日：2015-02-26
申请号：US13970865
申请日：2013-08-20
申请人： Lockheed Martin Corporation
发明人： William Kalms , John-Nathan Russell Snediker
IPC分类号： F41F3/04 , F41F7/00
CPC分类号： F41F3/0406 , F41F3/0413 , F41F3/073 , F41F3/077
摘要： A multiple missile carriage and launch guidance module comprising a plurality of missile launch rails that are each configured to carry and guide the launch of a missile and are carried on a common missile carriage wall in respective positions and orientations allowing for missile carriage and launch from the rails.
摘要翻译：一个多导弹托架和发射指导模块，其包括多个导弹发射轨道，每个导弹发射轨道被配置为携带和引导导弹的发射，并且在各自的位置和方位上承载在共同导弹托架壁上，从而允许导弹运载和发射轨道

69. 发明申请

US20130319211A1 PLUME EXHAUST MANAGEMENT FOR VLS 有权
标题翻译： VLS的排气管理
公开(公告)号：US20130319211A1
公开(公告)日：2013-12-05
申请号：US13374637
申请日：2011-12-06
申请人： Michael Ryan Whitney , Paul G. Atkinson , Perry J. Fridley, JR. , Keith M. DeLoach , Luis C. Gominho , Michael J. Morrison , Doyle B. Green , Douglas L. Wynings
发明人： Michael Ryan Whitney , Paul G. Atkinson , Perry J. Fridley, JR. , Keith M. DeLoach , Luis C. Gominho , Michael J. Morrison , Doyle B. Green , Douglas L. Wynings
IPC分类号： F41F3/04
CPC分类号： F41F3/0413
摘要： A system is provided for directing a flow of gas, including a launching mechanism, a plenum, a layer of meltable material, and an open-ended uptake component. The launching mechanism is adapted to expel rocket exhaust gas. The plenum includes an upper portion having at least one fire resistant breachable plug. The upper portion is adjacent to the launching mechanism. The layer of meltable material is disposed on the upper portion. The heat generated by the gas melts the layer of meltable material. The open-ended uptake component operatively connects to the plenum. The plug moves onto a lower portion of the plenum due to force generated by the gas onto the plug, and the gas flows through the plenum and the uptake component to vent said gas in a controlled manner.
摘要翻译：提供了一种用于引导气流的系统，包括发射机构，增压室，可熔融材料层和开放式吸收组分。发射机构适用于排放火箭废气。气室包括具有至少一个耐火可破裂塞子的上部部分。上部与发射机构相邻。可熔材料层设置在上部。由气体产生的热量可熔化材料层。开放吸收组件可操作地连接到气室。塞子由于气体在塞子上产生的力而移动到集气室的下部，并且气体流经气室和吸收组件以受控的方式排出所述气体。

70. 发明授权

US08181906B2 Method and apparatus for ram deceleration in a launch system 有权
标题翻译：发射系统中压头减速的方法和装置
公开(公告)号：US08181906B2
公开(公告)日：2012-05-22
申请号：US12417418
申请日：2009-04-02
申请人： Jeffrey H. Koessler , Brian L. Cochran , Mark A. DeBake , Steven J. Elder
发明人： Jeffrey H. Koessler , Brian L. Cochran , Mark A. DeBake , Steven J. Elder
IPC分类号： B64F1/04
CPC分类号： B64F1/04 , F41F1/00 , F41F3/0413 , F41F3/08
摘要： One embodiment includes a launch vessel defining an elongate, linear interior extending from a bottom portion to an exit opening. The embodiment includes a ram slidably disposed in the launch vessel, the ram sealed to the vessel. The embodiment also includes one or more wedges coupled to the launch vessel along the interior proximal the exit opening, with each wedge shape sized to increasingly narrow a cross section of the interior along an exit vector extending from the bottom portion toward the exit opening. In the embodiment, the vessel is to house a charge proximal the bottom portion, the charge to propel the ram along the exit vector, with the one or more wedges sized to stop be ram inside the interior.
摘要翻译：一个实施例包括限定从底部延伸到出口的细长的线性内部的发射器。该实施例包括可滑动地设置在发射容器中的柱塞，密封到容器的柱塞。该实施例还包括一个或多个楔形件，其沿着沿着出口开口的内部联接到发射容器，每个楔形尺寸被设计成沿着从底部向出口开口延伸的出口矢量逐渐变窄内部横截面。在该实施例中，容器将容纳靠近底部的电荷，电荷沿着出口矢量推动冲头，其中一个或多个楔的尺寸被设计成在内部停止。

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