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101. 发明专利

JPS60205199A PROPELLER FOR MISSILE 失效
公开(公告)号：JPS60205199A
公开(公告)日：1985-10-16
申请号：JP6160184
申请日：1984-03-29
申请人： MITSUBISHI ELECTRIC CORP
发明人： NUMATA YOSHIO
IPC分类号： F41F3/00 , B64D7/08 , F41F3/06

102. 实用新型

JPS60154797U 失效
公开(公告)号：JPS60154797U
公开(公告)日：1985-10-15
申请号：JP4123684
申请日：1984-03-23
IPC分类号： F41F3/00 , F41F3/06

103. 发明专利

JPS60200100A PROPELLING DEVICE FOR MISSILE 失效
公开(公告)号：JPS60200100A
公开(公告)日：1985-10-09
申请号：JP5582784
申请日：1984-03-23
申请人： MITSUBISHI ELECTRIC CORP
发明人： FUKUDA HIDEO
IPC分类号： F41F3/00 , F41F3/06 , F42B15/00 , F42B15/01 , F42C14/00

104. 发明专利

JPS567157B2 失效
公开(公告)号：JPS567157B2
公开(公告)日：1981-02-16
申请号：JP10963373
申请日：1973-09-29
IPC分类号： F41F3/06 , B64D7/08 , F41G7/34 , G01C21/00

105. 发明专利

JPS5023560B1 失效
公开(公告)号：JPS5023560B1
公开(公告)日：1975-08-08
申请号：JP9908171
申请日：1971-12-09
IPC分类号： F41A19/65 , F41F3/04 , F41F3/06

106. 实用新型

JPS4887800U 失效
公开(公告)号：JPS4887800U
公开(公告)日：1973-10-23
申请号：JP1184472
申请日：1972-01-29
IPC分类号： F41F3/04 , F41F3/06 , G09F3/02

107. 发明专利

KR20210033520A KR20210033520A - Military supply rack with structural elements and insertable ejectors 审中-公开
公开(公告)号：KR20210033520A
公开(公告)日：2021-03-26
申请号：KR1020217005273A
申请日：2019-09-04
申请人： 레이던 컴퍼니
发明人： 로버트 에이. 베일리 , 제임스 티. 에드먼 , 스티븐 에이. 스트리브 , 아만도 게레로 , 로이 피. 맥마혼 , 제시카 알. 디허트
IPC分类号： B64D1/06 , B64D7/08 , F41F3/06 , F41G7/00 , F42B39/28
CPC分类号： B64D1/06 , F42B39/28 , B64D1/04 , B64D7/08 , F41F3/06 , F41G7/007
摘要： 군수품 랙은 다수 개의 소형 이젝터들을 갖는 군수품 구조체를 포함한다. 상기 구조체는 한 쌍의 외부 길이 방향 리브들에 한 쌍의 내부 길이 방향 리브들을 포함한다. 군수품 랙 구조체의 스파인은 상기 모든 리브들을 연결하며, 상기 군수품 랙 구조체는 단일 피스의 재료로 형성될 수 있다. 상기 리브들은 상기 폭탄의 좌현과 우현의 측면에 있는 한 쌍의 사이드 리세스들을 정의하며, 각각은 이물 포켓과 고물 포켓으로 세분될 수 있다. 제거 가능한 이젝터들은 상기 포켓들에 위치한다. 상기 이젝터들은 상기 이젝터들의 외부에 위치한 가압 가스원(들)으로부터 가압 가스를 공급받을 수 있다. 상기 이젝터들에는 각각 다수 개의 이물 피스톤과 다수 개의 고물 피스톤이 있을 수 있다. 상기 이젝터들에는 상기 이물 피스톤(들)과 상기 후방 피스톤(들)으로 보내지는 상대적인 양의 가압 가스를 제어하기 위한 피치 제어 밸브가 포함될 수 있다.

108. 发明专利

JP2011033249A Launching system and launching apparatus 有权
标题翻译：启动系统和启动装置
公开(公告)号：JP2011033249A
公开(公告)日：2011-02-17
申请号：JP2009178507
申请日：2009-07-31
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： KURODA YOSHIKATSU , KAWAMATA YOSHIHIRO , SHINGO MIKA
IPC分类号： F41F3/06 , B64C37/02 , B64C39/02
CPC分类号： B64D1/04 , B64D3/00 , B64G1/005
摘要： PROBLEM TO BE SOLVED: To provide a launching system and a launching apparatus which enables air launch of a rocket without preparing a specific carrier aircraft.
SOLUTION: The launching apparatus 10 in which an air-launching missile 11 is detachably mounted on a wing body 12 is towed by an aircraft 30 via a cable 20 and is run and taken off. After the launching system 10 is lifted to the launching height of the missile 11 by the aircraft 30, the missile 11 is released from the wing body 12 in the air and then the missile 11 is ignited and launched in the air. When the system for launching in the air is developed, since it is not required to newly develop a carrier aircraft as a platform, a development cost can be remarkably reduced. In the case where a small satellite is installed in the missile 11, it is possible to develop a prompt-response type satellite which promptly responds to security matters and disaster observation etc.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种发射系统和发射装置，其能够在不准备特定载体飞机的情况下使空中发射火箭。
解决方案：其中空中发射导弹11可拆卸地安装在翼体12上的发射装置10由飞机30经由电缆20拖拉并被运行和取下。在飞机30将发射系统10提升到导弹11的发射高度之后，导弹11在空中从翼体12释放，然后导弹11被点燃并在空中发射。在空中发射的系统开发中，由于不需要新开发载具飞机作为平台，因此可以显着降低开发成本。在导弹11中安装小型卫星的情况下，可以制定及时响应安全事项和灾害观察等的及时响应型卫星。（C）2011年，JPO和INPIT

109. 发明专利

JP2008122013A Duration missile intercepting system 审中-公开
标题翻译： DURATION MISSILE INTERCEPTING SYSTEM
公开(公告)号：JP2008122013A
公开(公告)日：2008-05-29
申请号：JP2006308069
申请日：2006-11-14
申请人： Toshiba Corp , 株式会社東芝
发明人： SODA MAKOTO
IPC分类号： F41F3/06 , F41G7/22 , G01S13/88
摘要： PROBLEM TO BE SOLVED: To provide a duration missile intercepting system for intercepting a missile flying at a low altitude, more reliably. SOLUTION: The duration missile intercepting system stays in the sky uninfluenced by topography, buildings, or the like, by a body staying in the air, and detects and tracks the missile flying at the low altitude, from all directions and a relatively long distance using a radio wave sensor and a light wave sensor. In addition, a plurality of interceptor missiles are stored in a turning type pallet, and when firing the interceptor missile, the interceptor missile is rapidly directed toward a desired flying route and fired, and many firing opportunities are secured. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于拦截导弹在低空飞行的持续时间导弹拦截系统，更可靠。
解决方案：持续时间导弹拦截系统停留在天空不受地形，建筑物等影响，身体停留在空中，并从各个方向检测和跟踪导弹在低空飞行，相对而言长距离使用无线电波传感器和光波传感器。此外，多个拦截导弹存储在转动式托盘中，当发射拦截导弹时，拦截导弹迅速地朝向所需的飞行路线并被发射，并且确保了许多击发机会。版权所有（C）2008，JPO＆INPIT

110. 发明专利

JP2002236000A LAUNCHER FOR GUIDED MISSILE 失效
公开(公告)号：JP2002236000A
公开(公告)日：2002-08-23
申请号：JP2001033818
申请日：2001-02-09
申请人： MITSUBISHI ELECTRIC CORP
发明人： HARA HIROYA
IPC分类号： F41F3/06
摘要： PROBLEM TO BE SOLVED: To deal with both a front target and rear target in such a state that a guided missile is mounted forward to the progressing direction of a mother ship in a launcher for the missile that is launched rearward of an aircraft. SOLUTION: This device is provided with a hanger 12 hanging a guided missile 3 at the lower part of a launcher 2, an ejector F7 that is provided at the lower part of the launcher 2 to depress the front part of the guided missile 3 downward of an aircraft at the time of launch, an ejector A8 depressing the rear part of the guided missile 3 downward of the aircraft, an actuator 22 actuating the ejector F7 and the ejector A8, a rotating mechanism 10 that is provided at the rear end of the launcher 2 and connected with the rear end of the guided missile 3 to rotate the guided missile 3 in the direction of a pitch at the time of launch, and an angle detector 21 for detecting the rotating angle of the guided missile 3.

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