| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Launcher | US59866056 | 1956-07-18 | US2922602A | 1960-01-26 | MATHEISEL RUDOLPH A; COOKE CONRAD H |
| 62 | Heavy caliber recoilless gun | US3650648 | 1948-07-01 | US2741160A | 1956-04-10 | WALTON MUSSER CLARENCE |
| 63 | 발화가스 제거부재가 구비된 발사장치 | KR1020130099695 | 2013-08-22 | KR1020150022203A | 2015-03-04 | 고주용 |
| 발사체용 발화가스 제거장치가 개시되어 있다.
개시된 발사체용 발화가스 제거장치는, 발사체의 후방동체 벽면에 설치되는 인터페이스부; 상기 인터페이스부의 외측에 연결되며, 비활성가스가 공급되는 공급관; 상기 인터페이스부의 내측에 연결되며, 상기 공급관으로 유입되는 비활성가스가 유입되는 유입관; 및 상기 유입관에 연결된 채 상기 후방동체의 챔버 내에 설치되며, 상기 유입관을 통해 유입되는 비활성가스를 챔버 내부를 향해 고압으로 분사하기 위한 다수의 분사공이 형성되어, 상기 챔버 내부의 발화가스를 챔버 벽면에 형성된 배출구를 통해 외부로 배출하는 매니폴드를 포함하는 것이다. |
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| 64 | 로켓 포드 탑재 시스템 | KR1020080128961 | 2008-12-18 | KR101138154B1 | 2012-04-23 | 구자상 |
| PURPOSE: A rocket pod loading system is provided to reduce the transfer distance of the center beam transfer method for transferring the rocket pod carriage. CONSTITUTION: A rocket pod mount system comprises a launcher housing(10), a fixed beam(20), a center beam(30), a center beam transfer unit(40), a rocket pod carriage(50), a roller, and a wire. The fixed beam is inserted and fixed inside the launcher housing. The center beam is transferred to backward and forward in the fixed beam inside. The center beam transfer unit transfers the center beam to backward and forward. The rocket pod carriage transfers a rocket pod to the inner and outer launch station housing. The roller is installed in the front-end or the back-end of the center beam. The one end of the wire is fixed to the fixed beam. The other end of the wire is fixed to the rocket pod carriage. | ||||||
| 65 | WAFFENTRÄGER | EP16186534.0 | 2016-08-31 | EP3136040B1 | 2018-11-14 | GILCH, Joachim; GEBHARDT, Thomas |
| 66 | Vorrichtung und Verfahren zum Richten eines Raketenabschussbehälters | EP14150441.5 | 2014-01-08 | EP2754989A3 | 2016-03-23 | Prummenbaum, Eric; Lieberum, Karl; Lorenz, Bernhard; Dieling, Frank |
Die Erfindung betrifft eine Vorrichtung zum Richten eines Raketenabschussbehälters (20) mit einem Seitenrichtteil (2) und einem an dem Seitenrichtteil (2) angeordneten Höhenrichtteil (3) zur Aufnahme des Raketenabschussbehälters (20), wobei das Seitenrichtteil (2) ein Hubelement (4) zum Anheben und Absenken des Höhenrichtteils (3) aufweist. Einen weiteren Gegenstand der Erfindung bildet ein entsprechendes Verfahren zum Richten eines Raketenabschussbehälters (20).
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| 67 | Militärisches Fahrzeug, Transportbehälter und Verfahren zum Verstauen von Ausrüstungsgegenständen | EP12187744.3 | 2012-10-09 | EP2587208A3 | 2015-04-01 | Mergard, Tino; Freudenstein, Manfred; Schilling, Martin |
Militärisches Fahrzeug mit einer in Elevation richtbaren Werfereinrichtung, die einen in Elevation richtbaren Höhenrichtteil aufweist, wobei an dem Höhenrichtteil ein Transportbehälter (20) mit einem Stauraum (21) zum Verstauen von Ausrüstungsgegenständen angeordnet ist. Transportbehälter mit einem Stauraum (21) zum Verstauen von Ausrüstungsgegenständen zur Anordnung an einem in Elevation richtbaren Höhenrichtteil einer Werfereinrichtung eines militärischen Fahrzeugs. Verfahren zum Verstauen von Ausrüstungsgegenständen an einer Werfereinrichtung eines militärischen Fahrzeugs, die einen in Elevation richtbaren Höhenrichtteil aufweist, wobei ein Transportbehälter (20), der einen Stauraum (21) zum Verstauen von Ausrüstungsgegenständen aufweist, an dem Höhenrichtteil angeordnet wird.
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| 68 | A MOBILE MISSILE LAUNCH SYSTEM AND METHOD THEREOF | EP10707675.4 | 2010-01-11 | EP2414766B1 | 2013-10-09 | GURUPRASAD, Siddalingappa; KATTI, Shreedhar, Aravind; GOUD, Alasani Prasad; WAGHMARE, Vikas, Narayan; KUMAR, Sanjay; GUPTA, Atul; KHIRE, Ravindra, Sudhakar; SANTOSH, Tushar, Kant; GAUTAM, Bimal; RAM, Paras |
| 69 | DEFORMABLE MODULAR ARMORED COMBAT SYSTEM | EP09844465.6 | 2009-12-22 | EP2373510A2 | 2011-10-12 | HALLIDAY, Donald, R. |
| A modular, wheeled vehicle suitable for military use, includes a driver module having a width for seating one person and having length for seating a second (and optional third) person therebehind, and an engine module disposed behind the driver module containing an engine for powering the modular vehicle. The engine module has a rear surface adapted to receive a storage module. The driver module and the engine module form a central element having a pair of sides, a bottom, and a top. The central element is adapted to receive the modules on both of the central element sides. The central element has air inlet for personnel and for the engine disposed atop the central element. The bottom of the central element and troop side pods generally are V-shaped with slanted, upward extending sides. | ||||||
| 70 | Waffenplattform | EP09007295.0 | 2009-06-02 | EP2133647A2 | 2009-12-16 | Bruns, Thomas; Hamberg, Frank; Künzl, Thomas; Lechner, Martin; Mannertz, Heiko; Mittelsdorf, Oliver |
Die Erfindung betrifft eine Waffenplattform mit folgenden Merkmalen: |
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| 71 | Mobile carrier for a projectile launcher | EP06013537.3 | 2006-06-30 | EP1739382B1 | 2008-09-03 | Dekel, Ehud |
| 72 | Kampffahrzeug sowie Transportsystem zu seiner Verladung in Transportflugzeuge | EP94107517.8 | 1994-05-14 | EP0664431B1 | 1998-08-05 | Baus, Rüdiger, Dipl.-Ing.; Linge, Reiner |
| 73 | Kippbarer Aufbau für ein Militärfahrzeug | EP93118482.4 | 1993-11-16 | EP0612969B1 | 1997-04-16 | Ennenga, Luitjen, Dipl.-Ing. |
| 74 | 로켓 포드 탑재 시스템 | KR1020080128961 | 2008-12-18 | KR1020100070425A | 2010-06-28 | 구자상 |
| PURPOSE: A rocket pod loading system is provided to reduce the transfer distance of the center beam transfer method for transferring the rocket pod carriage. CONSTITUTION: A rocket pod mount system comprises a launcher housing(10), a fixed beam(20), a center beam(30), a center beam transfer unit(40), a rocket pod carriage(50), a roller, and a wire. The fixed beam is inserted and fixed inside the launcher housing. The center beam is transferred to backward and forward in the fixed beam inside. The center beam transfer unit transfers the center beam to backward and forward. The rocket pod carriage transfers a rocket pod to the inner and outer launch station housing. The roller is installed in the front-end or the back-end of the center beam. The one end of the wire is fixed to the fixed beam. The other end of the wire is fixed to the rocket pod carriage. | ||||||
| 75 | 차량용 하역 장치 및 이를 구비한 다연장 로켓 시스템 | KR1020080067826 | 2008-07-11 | KR1020100007264A | 2010-01-22 | 박수진; 이강일 |
| PURPOSE: A loading and unloading device for a vehicle and a multiple rocket launching system including the same are provided to easily load and unload objects using a simple structure. CONSTITUTION: Loading objects are placed on a base(210). A rotatable first actuator(220) is installed on the base. A rotatable first link member(230) is installed on the base. The rotatable first link member is positioned in order to receive the power from the first actuator. A rotatable second link member(240) is installed on the base. A third link member(250) connects the rotatable first link member and the rotatable second link member. A rotatable fourth link member(260) is installed and connected the second link member. One part of a second actuator(270) is installed on the rotatable second link member, and the other part of the second actuator is installed on the rotatable fourth link member. | ||||||
| 76 | 차량용 하역 장치 및 이를 구비한 다연장 로켓 시스템 | KR1020080065631 | 2008-07-07 | KR1020100005543A | 2010-01-15 | 박인규 |
| PURPOSE: A loading and unloading device for a vehicle and an MLRS(Multiple Launch Rocket System) using the same are provided to reduce the number of manufacturing steps and the manufacturing cost by simplifying the inner structure of the device. CONSTITUTION: A loading and unloading device(100) for a vehicle is composed of a base(110), first and second actuators(121,122), lower, middle, and upper link members(130,140,180), a protruded fixed unit(150), a parallel link member(160), one or more connection link member(170). The first actuator is rotatably installed on the base. The lower link member is rotated by operation of the first actuator. The middle link member is rotatably mounted on the lower link member. One end of the second actuator is mounted on the lower link member and the other end is mounted on the middle link member. The parallel link member is rotatably mounted on the middle link member. The connection link member connects the parallel link member and the protruded fixed unit each other. The upper link member applies force to loaded articles. One end of the third actuator is mounted on the middle link member and the other end is mounted on the upper link member. | ||||||
| 77 | Flying object firing apparatus | JP30465096 | 1996-11-15 | JPH10141892A | 1998-05-29 | KITAJIMA HIDEKUNI |
| PROBLEM TO BE SOLVED: To separate a servo actuator by enabling firing of a flying object from the state of being housed by internally housing and transferring it. SOLUTION: A guide rail is arranged in a firing apparatus 1 in the direction of the axis thereof and has an opening near a firing port 11. A lever 4 is provided with an inserting part 42 to be inserted into a flying object at one end thereof and a glinding surface pushing part 43 which glides down from the opening to be separated from a gliding surface while running on the gliding surface of the guide rail at the other end thereof and has the central part thereof fastened on a servo actuator 2. A stopper 19 is fastened at the tip of the guide rail and is engaged with a front protrusion part 23 protrusively arranged on the front end side of the servo actuator to stop the running of the servo actuator. Thus, the servo actuator is accurately separated from the flying object in the firing apparatus. COPYRIGHT: (C)1998,JPO | ||||||
| 78 | Mobile on-vehicle type missile launcher | JP25279692 | 1992-09-22 | JPH06101995A | 1994-04-12 | OGAWA MOTOHIDE |
| PURPOSE: To eliminate influence of jet on a vehicle, effectively move after launching and rapidly retract an operator after preparation for launching is completed by separating a launching mechanism having an outrigger from the vehicle at the time of launching to be isolated. CONSTITUTION: A launching mechanism 2 is separated from a vehicle l on the ground by an outrigger 6 to be independently supported at the time of launching a missile. At the time of transporting, a truck of the vehicle is inserted under the mechanism 2 stood and supported by the outrigger 6, and the mechanism 2 is fixed to the vehicle 1 by a connecting/separating mechanism provided at the side of the vehicle 1. Thus, the vehicle is separated from the mechanism 2 at the time of launching the missile so that the vehicle is retractable to eliminate influence of jet to the vehicle 1, and an operator is rapidly retracted after a preparation for launching is completed. At the time of moving, the mechanism 2 is carried on the vehicle 1 to be connected, and hence can be rapidly moved. COPYRIGHT: (C)1994,JPO&Japio | ||||||
| 79 | Suction port of engine generator for missile launcher | JP9648492 | 1992-04-16 | JPH05296694A | 1993-11-09 | OGAWA MOTOHIDE |
| PURPOSE: To prevent engine-stop by a method wherein a missile launcher is provided with a plurality of tubular bodies for sucking air, which are superposed in the shape of a telescope, and a driving rod for extending and/or contracting the tubular bodies to prevent the sucking of jet gas of a missile through the suction port of an engine generator. CONSTITUTION: A missile launcher 20 is mounted on the rear part of a self-propelling launcher while an engine generator 3, supplying an electric power to the power supplying device, the controller and the like of a missile 14, is mounted on the fore part of the same launcher. The engine generator 3 sucks air through a suction port 1, however, the suction port 1 is constituted of a plurality of tubular bodies 1a-1d, superposed in the shape of a telescope, and a driving rod 2 for driving the extension and contraction of the same tubular bodies. When the engine generator 3 is operated, the tubular bodies, which are stored in the tubular body 1a, are extended by driving them by the driving rod 2 whereby a suction port 10 is positioned above the diffusing position of the jet stream gas S of the missile 4 to prevent the sucking of the jet stream gas S. COPYRIGHT: (C)1993,JPO&Japio | ||||||
| 80 | Jet gas deflecting device at the time of launching missile | JP4352091 | 1991-03-08 | JPH05272896A | 1993-10-22 | Masao Inoue; Osamu Watanabe; 政雄 井上; 脩 渡辺 |
| PURPOSE: To launch a missile from a narrow place by deflecting downward jet gas at the time of launching a missile obliquely downward in a rearward direction and further upward by first, second deflectors. CONSTITUTION: Jet gases 5-1, 5-2 to be injected downward from a missile are respectively deflected obliquely downward by deflectors 2-1, 2-2, and further deflected horizontally and obliquely upward at an angle to a horizontal direction by a deflector 2. The gas 5 deflected obliquely upward in this manner is extended vertically upward and downward and laterally leftward and rightward by a separator 3, and turbulent flow mixture with the same air is vigorously activated. Accordingly, temperature and speed distributions of the gas are made uniform, and the temperature and the speed are reduced. Thus, the missile can be launched in a narrow place, and a force for operating in a horizontal direction to a launcher can be decreased. COPYRIGHT: (C)1993,JPO&Japio | ||||||
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