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1. 发明专利

JP2014156974A Engagement structure of resistance wing 有权
标题翻译：电阻耦合结构
公开(公告)号：JP2014156974A
公开(公告)日：2014-08-28
申请号：JP2013028375
申请日：2013-02-15
申请人： Technical Research & Development Institute Ministry Of Defence , 防衛省技術研究本部長 , Komatsu Ltd , 株式会社小松製作所
发明人： NAGAE TAKIZO , HIGO HIRONOBU , TANAKA MASAHIRO , MATSUSHITA HIROSHI , FUJIWARA YOSHIHIKO
IPC分类号： F42B10/48
摘要： PROBLEM TO BE SOLVED: To provide a missile including an engagement structure of a resistance wing which achieves compactification.SOLUTION: In an engagement structure, a first engaging part 204 includes a recessed part 204a and a cutout part 204b. The cutout part 204b is annularly formed lying astride an inner side surface 204S1 and a bottom surface 204S2. A first engaged part 214 includes a powder chamber 214a and a protruding part 214b. The protruding part 214b is connected with the powder chamber 214a and is inserted into the recessed part 204a.
摘要翻译：要解决的问题：提供一种包括电阻翼的接合结构的导弹，其实现紧密化。解决方案：在接合结构中，第一接合部204包括凹部204a和切口部204b。切口部204b环绕着内侧面204S1和底面204S2。第一接合部214包括粉末室214a和突出部214b。突出部214b与粉末室214a连接并插入凹部204a。

2. 发明专利

JP2014157089A Measuring system and measuring method for measuring output frequency error of oscillator built in gps receiver 有权
标题翻译：用于测量GPS接收机振荡器输出频率误差的测量系统和测量方法
公开(公告)号：JP2014157089A
公开(公告)日：2014-08-28
申请号：JP2013028278
申请日：2013-02-15
申请人： Technical Research & Development Institute Ministry Of Defence , 防衛省技術研究本部長 , Komatsu Ltd , 株式会社小松製作所
发明人： HIGO HIRONOBU , NAGAE TAKIZO , CHIMURA OSAMU , TANAKA MASAHIRO , NAKAJIMA TAKAYASU , SHIMIZU KEITA
IPC分类号： G01S19/23 , G01R23/00 , G01R23/10 , G01S19/18 , G01S19/26 , G01S19/29
摘要： PROBLEM TO BE SOLVED: To provide a measuring system and a measuring method for measuring an output frequency error of an oscillator built in a GPS receiver.SOLUTION: A measuring system 100 includes an output frequency error calculation part 50f which calculates an output frequency error ΔF by subtracting natural frequency Fxtal from output frequency Fstd calculated based on theoretical received frequency Frecv' and a synchronizing signal Sync.
摘要翻译：要解决的问题：提供一种用于测量内置于GPS接收机中的振荡器的输出频率误差的测量系统和测量方法。解决方案：测量系统100包括输出频率误差计算部分50f，其计算输出频率误差＆Dgr F通过从基于理论接收频率Frecv'和同步信号Sync计算的输出频率Fstd减去固有频率Fxtal。

3. 发明专利

JP2014156975A Missile 有权
标题翻译：导弹
公开(公告)号：JP2014156975A
公开(公告)日：2014-08-28
申请号：JP2013028376
申请日：2013-02-15
申请人： Technical Research & Development Institute Ministry Of Defence , 防衛省技術研究本部長 , Komatsu Ltd , 株式会社小松製作所
发明人： NAGAE TAKIZO , HIGO HIRONOBU , TANAKA MASAHIRO , NAKAMURA TAKASHIGE , YAMAGAMI KAZUICHI , FUJIWARA YOSHIHIKO
IPC分类号： F42B15/08 , F42B10/44 , H01Q1/40
摘要： PROBLEM TO BE SOLVED: To provide a missile capable of inhibiting an antenna from being damaged.SOLUTION: An artillery shell 100 includes: an antenna substrate 41 stored in a front annular recessed part 70; and an antenna cover 42 which covers the antenna substrate 41. The front annular recessed part 70 has a first cutout part 201 formed at a front side surface 200A provided at the inner front side. The antenna cover 42 includes a protruding part 42a of the antenna cover which is inserted into the first cutout part 201.
摘要翻译：要解决的问题：提供能够抑制天线受损的导弹。解决方案：炮壳100包括：存储在前环形凹部70中的天线基板41; 以及覆盖天线基板41的天线罩42.前环形凹部70具有形成在设置在内前侧的前侧面200A的第一切口部201。天线罩42包括插入第一切口部201中的天线盖的突出部42a。

4. 发明专利

JP2014156973A Resistance wing structure 有权
标题翻译：电阻结构
公开(公告)号：JP2014156973A
公开(公告)日：2014-08-28
申请号：JP2013028374
申请日：2013-02-15
申请人： Technical Research & Development Institute Ministry Of Defence , 防衛省技術研究本部長 , Komatsu Ltd , 株式会社小松製作所
发明人： NAGAE TAKIZO , HIGO HIRONOBU , TANAKA MASAHIRO , MATSUSHITA HIROSHI , FUJIWARA YOSHIHIKO
IPC分类号： F42B10/50
摘要： PROBLEM TO BE SOLVED: To provide a missile equipped with a resistance wing structure capable of being made compact.SOLUTION: In a resistance wing structure 40, a first locked part of a first supporting member 210 is locked to a first locking part 204 of a cam member 200. A first cam protrusion of a first resistance wing 101 is fitted to a first cam groove 301 of the cam member 200, and a pair of first guide protrusions 101d of the first resistance wing 101 is fitted to a pair of first guide grooves of the first supporting member 210. A second cam protrusion of a second resistance wing 102 is fitted to a second cam groove 302 of the cam member 200, and a pair of second guide protrusions 102d of the second resistance wing 102 is fitted to a pair of second guide grooves of the first supporting member 210.
摘要翻译：要解决的问题：提供一种配备有能够紧凑的电阻翼结构的导弹。解决方案：在电阻翼结构40中，第一支撑构件210的第一锁定部分被锁定到第一锁定部分204 凸轮构件200.第一电阻翼101的第一凸轮突起装配到凸轮构件200的第一凸轮槽301，并且第一电阻翼101的一对第一引导突起101d装配到一对第一引导件第二电阻翼102的第二凸轮突起装配到凸轮构件200的第二凸轮槽302，并且第二阻力翼102的一对第二引导突起102d安装到第一支撑构件210的一对第二引导槽。

5. 发明专利

JP2014157088A Position finding system and position finding method for position finding with gps receiver mounted on flying object 有权
标题翻译：位置查找系统和位置查找方法，用于在飞行对象上安装GPS接收器
公开(公告)号：JP2014157088A
公开(公告)日：2014-08-28
申请号：JP2013028277
申请日：2013-02-15
申请人： Technical Research & Development Institute Ministry Of Defence , 防衛省技術研究本部長 , Komatsu Ltd , 株式会社小松製作所
发明人： HIGO HIRONOBU , NAGAE TAKIZO , CHIMURA OSAMU , TANAKA MASAHIRO , NAKAJIMA TAKAYASU , SHIMIZU KEITA
IPC分类号： G01S19/18 , F42B15/08 , G01S19/09 , G01S19/35
摘要： PROBLEM TO BE SOLVED: To provide a position finding system and a position finding method that make possible acquisition of flight data of a gun shell in the early stage of its flight.SOLUTION: In a position finding system 100, a GPS receiver 11 has a memory 11d that stores digital output signals T based on input signals generated from a plurality of satellite waves W, and an analyzer 40 has a controller 41 that, after executing search of carrier frequencies and code phases and synchronous tracking of carrier components and code phases while reproducing the digital output signals T, executes collection and position finding of pseudo ranges and navigation messages while reproducing the digital output signals T once again.
摘要翻译：要解决的问题：提供一种位置查找系统和位置查找方法，其可以在其飞行的早期阶段获得枪壳的飞行数据。解决方案：在位置查找系统100中，GPS接收器11具有存储器11d，其基于从多个卫星波W产生的输入信号存储数字输出信号T.分析器40具有控制器41，其在执行载波频率和码相位的搜索以及载波分量和码相位的同步跟踪之后，同时再现数字输出信号T，再一次再现数字输出信号T，执行伪范围和导航消息的收集和位置查找。

6. 发明专利

JP2014156972A Missile having thermal battery 有权
标题翻译：具有热电池故障
公开(公告)号：JP2014156972A
公开(公告)日：2014-08-28
申请号：JP2013028276
申请日：2013-02-15
申请人： Technical Research & Development Institute Ministry Of Defence , 防衛省技術研究本部長 , Komatsu Ltd , 株式会社小松製作所
发明人： NAGAE TAKIZO , HIGO HIRONOBU , CHIMURA OSAMU , TANAKA MASAHIRO , NOMURA KYOSUKE
IPC分类号： F42C11/04
摘要： PROBLEM TO BE SOLVED: To provide a missile capable of heat insulation of a thermal battery and capable of suppressing heat conduction to periphery of the thermal battery.SOLUTION: A shell includes a body 32, first and second annular support members 34, and first to third reflection films 35 to 37. The first annular support member is attached at a front end part of the body 32, and the second annular support member 34 is attached at a rear end part of the body 32. The first reflection film 35 is disposed at inside of the first annular support member, at the front of the body 32. The second reflection film 36 is disposed at inside of the second annular support member 34 at the rear of the body 32. The third reflection film 37 is disposed between the first annular support member and the second annular support member 34 at the side of the body 32.
摘要翻译：要解决的问题：提供能够对热电池进行隔热并能够抑制热传导到热电池周围的导弹。解决方案：壳体包括主体32，第一和第二环形支撑构件34，并且首先到第三反射膜35〜37.第一环状支撑构件安装在主体32的前端部，第二环状支撑构件34安装在主体32的后端部。第一反射膜35配置在第一环形支撑构件的内部位于主体32的前部。第二反射膜36设置在主体32的后部的第二环形支撑构件34的内侧。第三反射膜37设置在第一环形支撑构件和位于主体32侧的第二环形支撑构件34。

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