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. 发明专利

JP2017155653A ロケットモータ审中-公开
公开(公告)号：JP2017155653A
公开(公告)日：2017-09-07
申请号：JP2016039716
申请日：2016-03-02
申请人：川崎重工業株式会社
发明人：安倍智宏 , 渡辺清幸 , 西川達哉
IPC分类号： F42B10/30 , F02K9/36 , F02K9/10 , F02K9/24
摘要：【課題】発射時における固体推進薬14の耐衝撃性の向上を図ったロケットモータ10を提供する。【解決手段】ロケットモータ10は、後端開口を有するケース13と、前記ケース13に装填された固体推進薬14と、前記ケース13の前記後端開口に取り付けられ、前記固体推進薬14の燃焼ガスの噴射口を有するノズル15と、前記ノズル15の前記噴射口を覆う蓋16と、前記固体推進薬14と前記蓋16との間で前記ノズル15に充填された火薬17と、を備えている。【選択図】図1

2. 发明专利

JP5307297B2 How to control the flight of the missile using the attitude control thruster 有权
公开(公告)号：JP5307297B2
公开(公告)日：2013-10-02
申请号：JP2012526741
申请日：2010-04-20
申请人：レイセオンカンパニー
发明人：キンジー・ジュニア、ロイド , クック、ジェームズ・エム．
IPC分类号： F42B15/01 , F42B10/30 , G05D1/12
CPC分类号： F42B10/661
摘要： A method of controlling flight of a missile includes using gyroscopes, such as pitch rate gyroscopes, to sense when a factor based on the angular rate of change of the missile exceeds a threshold value. One the threshold value is exceeded, a decision may be made to use one or more compensation thrusters to reduce the angular rate of change. The use of the compensation thrusters may correct residual angular velocities from a pitch over maneuver used to put the missile on an intended course. In addition, the compensation thrusters may be used to compensate for errors in missile heading induced after the pitch over maneuver, such as induced by misalignment of thrust provided by a main rocket motor of the missile. Multiple compensation thrusters may be used to compensate for angular changes in the pitch and yaw directions.

3. 发明专利

JP5272560B2 Induction methods and guidance system of the flying object 有权
公开(公告)号：JP5272560B2
公开(公告)日：2013-08-28
申请号：JP2008193592
申请日：2008-07-28
申请人：三菱電機株式会社
发明人：惇一内田
IPC分类号： F41G7/36 , F41G7/22 , F42B10/30 , F42B15/01 , G01C21/16 , G01C21/24
摘要： PROBLEM TO BE SOLVED: To provide a guiding method for a missile enabling flight on an optimal flight route corresponding to types of targets. SOLUTION: The guiding method for the missile includes: a step of acquiring target information comprising the position, speed and type of a target; a step of selecting a flight route minimizing flight time until the missile 1 meets the target and a flight route maximizing remaining speed when the missile meets the target; a step of acquiring a firing table corresponding to the chosen flight route and indicating flight time until the missile reaches a predetermined position and the turning direction immediately after firing; a step of calculating a meeting point where the missile meets the target based on the target position, target speed and firing table; a step of extracting the turning direction from the firing table based on the meeting point; and a step of controlling the missile so that the turning direction of the missile immediately after firing becomes the extracted turning direction. COPYRIGHT: (C)2010,JPO&INPIT

4. 发明专利

JP2011237075A Flying object 有权
标题翻译：飞行对象
公开(公告)号：JP2011237075A
公开(公告)日：2011-11-24
申请号：JP2010107370
申请日：2010-05-07
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： SUZUKI YASUHITO , FURUYA SHOJIRO , KITANO TAKAHISA
IPC分类号： F42B10/30 , F42B15/00
摘要： PROBLEM TO BE SOLVED: To obtain a flying object which does not increase the whole length and mass and has a simple configuration for obtaining propelling force even when equipped with a sub-propelling means for generating propelling force by jetting combustion gas to the side face direction of a body.SOLUTION: A hollow body 24 contains solid propellant 22 in areas 20A, 20B. The solid propellant 22 is burned by so-called multi-pulse which ignites the solid propellant 22 in the areas 20A, 20B sequentially. A nozzle 26 arranged at the back of the body 24 generates propelling force by jetting combustion gas generated by combustion of the solid propellant 22 to the rear of the body 24. A side thrustor 32 attached to the side face of the body 24 generates propelling force by jetting the combustion gas generated by combustion of the solid propellant 22 in the area 20A ahead of the body 24 to the side face direction of the body 24.
摘要翻译：要解决的问题：为了获得不增加整个长度和质量的飞行物体，并且具有用于获得推进力的简单构造，即使当配备有通过向燃烧气体喷射燃烧气体而产生推进力的副推进装置身体的侧面方向。解决方案：中空体24在区域20A，20B中包含固体推进剂22。固体推进剂22被所谓的多脉冲燃烧，顺序地点燃区域20A，20B中的固体推进剂22。布置在主体24的后部的喷嘴26通过将固体推进剂22的燃烧产生的燃烧气体喷射到主体24的后部而产生推进力。附接到主体24的侧面的侧推进器32产生推进力通过将主体24前方的区域20A中的固体推进剂22的燃烧产生的燃烧气体喷射到主体24的侧面方向。（C）2012年，JPO＆INPIT

5. 发明专利

JP2011185566A Side thruster for missile 审中-公开
标题翻译：侧面打击器为MISSILE
公开(公告)号：JP2011185566A
公开(公告)日：2011-09-22
申请号：JP2010053162
申请日：2010-03-10
申请人： Mitsubishi Electric Corp , 三菱電機株式会社
发明人： OGURA EIJI
IPC分类号： F42B10/30
摘要： PROBLEM TO BE SOLVED: To provide a side thruster for a missile controlling change in aerodynamic characteristics of the missile due to injection by suppressing expansion of a low pressure region on a body surface in rear of an injection nozzle when the injection nozzle performs injection while minimizing effects on the aerodynamic characteristics when the injection nozzle does not perform injection, in the missile including the injection nozzle performing injection to the lateral side.
SOLUTION: On the body surface of the missile 1, a circular groove 7 is provided around the injection nozzle 2. Thus, this can suppress expansion of the low pressure region on the body surface in rear of the injection nozzle 2 when the injection nozzle 2 performs injection, while the effects on the aerodynamic characteristics when the injection nozzle 2 does not perform injection are minimized.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种侧向推进器，用于通过在喷射喷嘴执行时抑制喷射喷嘴后部的体表面上的低压区域的膨胀来控制由于注射而导致的导弹的空气动力特性的变化在喷射喷嘴不执行喷射的同时最小化对空气动力学特性的影响的导弹，包括喷射喷嘴到侧面的导弹。
解决方案：在导弹1的身体表面上，在注射喷嘴2周围设置有圆形槽7.因此，这可以抑制喷嘴2后部的体表面上的低压区域的膨胀，喷射喷嘴2进行喷射，同时对喷射喷嘴2不进行喷射时的空气动力特性的影响最小化。版权所有（C）2011，JPO＆INPIT

6. 发明专利

JP2010117059A High-speed missile destructing device 审中-公开
标题翻译：高速故障破坏设备
公开(公告)号：JP2010117059A
公开(公告)日：2010-05-27
申请号：JP2008289403
申请日：2008-11-12
申请人： Toshihisa Shirakawa , 白川利久
发明人： SHIRAKAWA TOSHIHISA
IPC分类号： F41H13/00 , F42B3/00 , F42B10/30 , F42B12/02 , F42B15/00 , F42B19/00 , G21J3/00
摘要： PROBLEM TO BE SOLVED: To provide a device for destructing a high-altitude high-speed missile such as a huge meteorite by generating small nuclear explosion by small fissile substance amount. SOLUTION: By opening/closing through the remote control of a valve 268 attached in the middle of a propulsion gas pipe 69, propulsion gas 65 is emitted from a nozzle 71 fixed to the outer face of each of a storage container 3 and an auxiliary tank 60 to the external world to wait a high-speed missile in its advancing direction. By injecting an excessive moderator nuclear fuel solution 61 into the air gap of excessively small solid moderator-mixed gadolinium addition nuclear fuel rod lattice 50 with a pump 63, a moderator ratio is optimized and kinf is maximized. When the kinf becomes maximum, neutron is generated to cause nuclear explosion. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于通过以小的易裂变物质量产生小型核爆炸来破坏诸如巨大陨石的高空高速导弹的装置。解决方案：通过安装在推进气管69中间的阀门268的遥控器打开/关闭，推进气体65从固定在每个储存容器3的外表面上的喷嘴71发出，向外部世界等待高速导弹前进方向的辅助水箱60。通过将过量的缓和剂核燃料溶液61注入到具有泵63的过小的固体慢化剂混合的钆添加核燃料棒格50的气隙中，调节剂比率被优化并且kinf最大化。当kinf变得最大时，产生中子以引起核爆炸。版权所有（C）2010，JPO＆INPIT

7. 发明专利

JPS491120B1 失效
公开(公告)号：JPS491120B1
公开(公告)日：1974-01-11
申请号：JP8615069
申请日：1969-10-29
IPC分类号： F41F3/00 , F42B10/30 , F41F3/04

8. 发明公开

EP1283980A4 DIRECTIONAL CONTROL OF MISSILES 审中-公开
标题翻译： SYSTEM FOR驾驶BODY飞行
公开(公告)号：EP1283980A4
公开(公告)日：2006-03-22
申请号：EP01980025
申请日：2001-05-25
申请人： METAL STORM LTD
发明人： O'DWYER JAMES MICHAEL
IPC分类号： F42B10/60 , F41G7/20 , F42B5/03 , F42B10/30 , F42B10/48 , F42B10/66 , G05D1/12 , B64G1/24 , F41G7/00 , F42B15/01 , G05D1/10
CPC分类号： F41H11/02 , F41G7/20 , F42B5/035 , F42B10/30 , F42B10/48 , F42B10/66 , F42B10/661 , G05D1/12
摘要： Missile (10) includes one or more of barrel assemblies (11) which are displaced from the centre of gravity of missile (10). Each barrel assembly (11) includes a plurality of projectiles axially disposed within the barrel, and each projectiles is associated with a discrete propellant charge for propelling the projectile sequentially from the barrel. Each array of barrel assemblies (11) is capable of selectively firing the projectiles from selected barrels whereby missile (10) is accelerated by the reactionary force generated by said firing of projectiles and the missile is deflected onto a new course or trajectory. This enables missile (10) to be steered to intercept its target even if the target is undertaking evasive manoeuvre. Each barrel assembly (11) can include up to twelve projectiles.

9. 发明授权

EP3128285B1 FEUERWERKSRAKETE MIT VORBESTIMMBARER ORIENTIERUNG DES AM HIMMEL DARGESTELLTEN BILDES, UMFASSEND EINE ELEKTRONIKEINHEIT UND MAGNETFELDSENSOREN 有权
公开(公告)号：EP3128285B1
公开(公告)日：2019-11-06
申请号：EP16001751.3
申请日：2016-08-07
申请人： Buchner, Alexander , Kränzle, Ralph
发明人： Buchner, Alexander , Kränzle, Ralph
IPC分类号： F42B4/06 , F42B4/08 , F42B10/30

10. 发明公开

EP2972063A4 FIN DEPLOYMENT SYSTEM 审中-公开
标题翻译： EINSATZSYSTEM
公开(公告)号：EP2972063A4
公开(公告)日：2017-01-04
申请号：EP14807894
申请日：2014-03-11
申请人： BAE SYSTEMS LAND & ARMAMENTS L P
发明人： CARLSON EUGENE W , ZOLEN THOMAS A , CITRO ROBERT W CITRO , TRAN KIEN D
IPC分类号： F42B10/16 , F42B10/06 , F42B10/26 , F42B10/30 , F42B10/60
CPC分类号： F42B10/16 , F42B10/06 , F42B10/26 , F42B10/30
摘要： A projectile having a fin deployment system disposed about its circumference. The fins are initially contained by a fin cover that is removed by aerodynamic force. The fins are then rotated around a rotational axis parallel to and offset from the central axial axis of the projectile body by the centrifugal forces created by the rotation of the projectile as the projectile passes through a barrel of a gun system or tube launcher. The fin deployment system can also have locking systems that lock the fins in the deployed position and prevent the fins from rotating back into the retracted position after deployment.
摘要翻译：具有围绕其圆周布置的翅片展开系统的抛射体。翅片最初由翅片盖包含，其通过空气动力力去除。然后，当弹丸穿过枪系统或管发射器的枪管时，翅片围绕平行于射弹体的中心轴线的旋转轴线旋转，并且通过由弹丸的旋转产生的离心力旋转。翅片展开系统还可以具有将翅片锁定在展开位置的锁定系统，并且防止翅片在展开之后回到缩回位置。

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