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公开(公告)号：US11913753B2
公开(公告)日：2024-02-27
申请号：US17655596
申请日：2022-03-21
Applicant: Raytheon Company
Inventor： Joaquim A. Bento , Samuel S. Han , Michael R. Souliotis , Bruce F. Gogolen , Howard R. Kornstein , Michael V. Corbin
IPC: F41F3/04
CPC classification number: F41F3/0406
Abstract: Methods and apparatus for a brace for attachment to a launch rail for a projectile for distributing loading of the projectile when supported by the launch rail. A height of the brace can be adjusted to distribute loading. In embodiments, a release mechanism can allow movement of a wear plate during launch of the projectile.
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公开(公告)号：US20170297740A1
公开(公告)日：2017-10-19
申请号：US15426273
申请日：2017-02-07
Applicant: Robonic Ltd Oy
Inventor： Pentti Lipponen
CPC classification number: B64F1/06 , B64C39/024 , B64C2201/084 , F41F3/0406
Abstract: The invention relates to a ramp of a catapult and to a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) is supported on a ramp (1). The ramp is formed of one or more ramp elements (1a-1m). The ramp element comprises four frame plates, namely two parallel side plates (20a, 20b), a top plate (21) and a bottom plate (22). The frame plates are separate pieces which are connected at fastening points (25) to each other by means of mechanical fastening elements (26).
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公开(公告)号：US09617016B2
公开(公告)日：2017-04-11
申请号：US14211779
申请日：2014-03-14
Applicant: Palmer Labs, LLC , 8 Rivers Capital, LLC
Inventor： Miles R. Palmer , Glenn William Brown, Jr.
CPC classification number: B64G1/409 , B64G1/002 , B64G1/402 , B64G1/406 , F02K9/95 , F41A1/04 , F41B6/00 , F41B6/006 , F41F1/00 , F41F3/04 , F41F3/0406 , F42B6/006 , F42B15/10 , F42B15/12 , F42C11/00 , F42C11/04
Abstract: The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.
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公开(公告)号：US20150101478A1
公开(公告)日：2015-04-16
申请号：US14052874
申请日：2013-10-14
Applicant: The Boeing Company
Inventor： Todd J. Palmer , Thaddeus M. Jakubowski, Jr. , Cory Gordon Keller , Steven Michael Schoen , Richard Raymond Kreutzman, Jr. , Daniel DiDomenico , Aaron Ross Cowin , Gregory M. Sisti , Samuel Jerome Huhman , Mike Heller , Daryl D. Carpenter , David Michael Paruleski
CPC classification number: H01Q15/14 , F41F3/0406 , F41F3/06 , F41F7/00 , F41H3/00 , H01Q1/28 , H01Q17/00
Abstract: A cover for an empty rail missile launcher that can be used in flight. The cover is shaped to reflect radar signals transmitted by a radar transmitter away from the radar transmitter to reduce detectibility by radar. The cover may also be coated with radar absorbent material to reduce detectibility by radar. Hangers are used to mount the cover to the rail missile launcher. The cover is provided with a grounding mechanism to dissipate precipitation static. A restraint mechanism is provided to prevent the cover from inadvertently sliding off the rail missile launcher.
Abstract translation: 一个可以在飞行中使用的空轨导弹发射器的盖子。 盖子成形为将雷达信号发射的雷达信号反射离雷达发射器，以减少雷达的可检测性。 盖子也可以涂覆雷达吸收材料，以减少雷达的可检测性。 挂衣架用于将盖子安装到轨道导弹发射器上。 盖上设有接地机构，以消除静电沉淀。 提供了一种约束机制，以防止盖子无意中从导弹发射器滑落。
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公开(公告)号：US07954755B2
公开(公告)日：2011-06-07
申请号：US12463617
申请日：2009-05-11
Applicant: Pentti Lipponen
Inventor： Pentti Lipponen
IPC: B64F1/04
CPC classification number: F41F7/00 , F41B3/02 , F41F3/0406
Abstract: A method of launching a catapult, a catapult and a locking device for a catapult. The catapult comprises a carriage for fastening an aircraft. The carriage can be provided with a high acceleration by directing a launching force generated by a launching device thereto. The carriage can be held at a launching position by means of the locking device. The catapult further comprises a takeoff damper that generates a damping force having a direction opposite relative to the launching force. Accordingly, the takeoff damper restricts the acceleration of the carriage at the initial launching moments.
Abstract translation: 发射弹射器，弹射器和弹射器的锁定装置的方法。 弹射器包括用于紧固飞行器的滑架。 可以通过将由发射装置产生的发射力引导到滑架来提供高加速度。 托架可以通过锁定装置保持在发射位置。 弹射器还包括起飞阻尼器，其产生具有相对于发射力相反的方向的阻尼力。 因此，起飞阻尼器限制了在初始发射时刻的滑架的加速度。
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公开(公告)号：US07931486B1
公开(公告)日：2011-04-26
申请号：US12824161
申请日：2010-06-26
Applicant: James C. Walters
Inventor： James C. Walters
IPC: H01R13/62
CPC classification number: H01R13/465 , F41F3/0406 , F42C19/06 , H01R13/623 , H01R13/631 , H01R13/642 , H01R2107/00 , H01R2201/26
Abstract: An electrical connector for testing of a missile launch rail is provided. A stationary housing is combined with a coupling ring to form an outer housing. An internal plunger is housed in the outer housing and spans the length of the outer housing. The stationary housing anchors to the missile launch rail, while the coupling ring is free to rotate about the internal plunger. The coupling ring is rotated via a hand grasp. The coupling ring rotation translates into forward and aft movement of the pin assembly. The connector provides forward and backward stops for limiting pin insertion and extraction moves to desired distances. Rotation via triple-start threads readily overcomes insertion and extraction resistance of a bulky multi-pin assembly and provides a smooth and controlled electrical connection. The size of the connector approaches that of a small conventional military standard 38999 series III connector.
Abstract translation: 提供了用于测试导弹发射轨的电连接器。 固定壳体与联接环组合以形成外壳体。 内部柱塞容纳在外壳中并且跨过外壳的长度。 固定的壳体锚定在导弹发射轨上，而联接环可以围绕内部柱塞自由旋转。 联轴器通过手把旋转。 联接环旋转转换成销组件的向前和向后运动。 连接器提供前进和后退止动件，用于限制插针和提取移动到所需的距离。 通过三重启动螺纹的旋转可以轻松克服笨重的多针组件的插拔力，并提供平滑和受控的电气连接。 连接器的尺寸接近传统军用标准38999系列III型连接器的尺寸。
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公开(公告)号：US07562843B2
公开(公告)日：2009-07-21
申请号：US10578016
申请日：2004-11-11
Applicant: Pentti Lipponen
Inventor： Pentti Lipponen
IPC: B64F1/06
CPC classification number: F41F7/00 , F41B3/02 , F41F3/0406
Abstract: A method of launching a catapult, a catapult and a locking device for a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) can be provided with a high acceleration by directing a launching force (F1) generated by a launching device thereto. The carriage (4) can be held at a launching position (6) by means of the locking device (9). The catapult further comprises a takeoff damper (34) that generates a damping force (F2) having a direction opposite relative to the launching force. Accordingly, the takeoff damper (34) restricts the acceleration of the carriage (4) at the initial launching moments.
Abstract translation: 发射弹射器，弹射器和弹射器的锁定装置的方法。 弹射器包括用于紧固飞行器（5）的滑架（4）。 滑架（4）可以通过将由发射装置产生的发射力（F1）引导到其上而被提供高加速度。 托架（4）可以通过锁定装置（9）保持在发射位置（6）。 弹射器还包括起飞阻尼器（34），其产生具有相对于发射力相反方向的阻尼力（F2）。 因此，起飞阻尼器34在最初的起动时刻限制滑架4的加速度。
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公开(公告)号：US20070084965A1
公开(公告)日：2007-04-19
申请号：US10578016
申请日：2004-11-11
Applicant: Pentti Lipponen
Inventor： Pentti Lipponen
IPC: B64F1/04
CPC classification number: F41F7/00 , F41B3/02 , F41F3/0406
Abstract: A method of launching a catapult, a catapult and a locking device for a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) can be provided with a high acceleration by directing a launching force (F1) generated by a launching device thereto. The carriage (4) can be held at a launching position (6) by means of the locking device (9). The catapult further comprises a takeoff damper (34) that generates a damping force (F2) having a direction opposite relative to the launching force. Accordingly, the takeoff damper (34) restricts the acceleration of the carriage (4) at the initial launching moments.
Abstract translation: 发射弹射器，弹射器和弹射器的锁定装置的方法。 弹射器包括用于紧固飞行器（5）的滑架（4）。 滑架（4）可以通过将由发射装置产生的发射力（F 1> 1）指向其而被提供高加速度。 托架（4）可以通过锁定装置（9）保持在发射位置（6）。 弹射器还包括起飞阻尼器（34），其产生具有相对于发射力相反方向的阻尼力（F 2> 2）。 因此，起飞阻尼器34在最初的起动时刻限制滑架4的加速度。
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公开(公告)号：US20040069136A1
公开(公告)日：2004-04-15
申请号：US09976389
申请日：2001-10-12
Inventor： Joseph P. Smith , John K. Coolidge , Stanley G. Turner
IPC: F41F003/04 , F41A009/00
CPC classification number: F41F3/0406
Abstract: A launcher platform including a support structure and a number of rails mounted on the support structure for supporting missles thereon, each adjacent rail elevated above the other rails to accommodate additional missles and different type missles while maintaining low center of gravity.
Abstract translation: 发射台平台包括支撑结构和安装在支撑结构上的多个轨道，用于支撑其上的导弹，每个相邻的轨道在另一导轨上方升高以容纳额外的导弹和不同型号的导弹，同时保持低的重心。
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公开(公告)号：US06561074B1
公开(公告)日：2003-05-13
申请号：US05823885
申请日：1977-07-28
Applicant: Seymour J. Engel , William M. Foster , Carroll D. Phillips , Clifton F. Orchard
Inventor： Seymour J. Engel , William M. Foster , Carroll D. Phillips , Clifton F. Orchard
IPC: F41F304
CPC classification number: F41G7/2246 , F41F3/0406 , F41F3/073 , F41F3/077 , F41G7/2206 , F41G7/2286 , G01S7/03 , G01S13/225 , G01S13/30 , G01S13/426 , G01S13/4463 , G01S13/449 , G01S13/72 , G01S13/78 , G01S13/86 , G01S13/87 , G01S2013/0272
Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile. The invention herein described was made in the course of or under a contract or subcontract thereunder, with the Department of Defense.
