-
-
2.发明专利
公开(公告)号：JP2011012903A
公开(公告)日：2011-01-20
申请号：JP2009157853
申请日：2009-07-02
申请人： Hiroto Hanyu , Ihi Aerospace Co Ltd , Ihi Aerospace Engineering Co Ltd , Yasuhiro Morita , 株式会社Ihiエアロスペース , 株式会社アイ・エイチ・アイ・エアロスペース・エンジニアリング , 泰弘 森田 , 宏人 羽生
发明人： HANYU HIROTO , MORITA YASUHIRO , MIYAGAWA KIYOSHI , KOREKI TAKEMASA , TANAKA NAOHIRO , UEKUSA YASUYUKI , KATSUMATA MASAAKI
摘要： PROBLEM TO BE SOLVED: To provide a device and method for radio ignition of pyrotechnics for a rocket, enabling stable operation by a battery of small capacity for a total operation period from time immediately before installation on a launcher to ignition operation (e.g. maximum seven days), and reducing delay and variation of ignition timing of the plurality of pyrotechnics within an intended tolerance (e.g. less than 10 ms).SOLUTION: The device comprises: a master unit; and slave units 20 each having a slave side radio communication unit 22 enabling interactive communications with a master side radio communication unit, an ignition circuit 28 for making ignition current flow in a fuse head 21, and a sub computer 24 for controlling the slave side radio communication unit 22 and the ignition circuit 28. The sub computer 24 can switch a waiting mode for alternately repeating reception time and sleep time, and an operation mode enabling continuous reception. By communications by the master unit, the sub computers 24 of the plurality of slave units 20 are switched from the waiting mode to the operation mode, and then, by concurrent communications from the master unit, simultaneous ignition is commanded to the plurality of slave units 20.
摘要翻译： 要解决的问题：提供用于火箭的烟火的无线电点火的装置和方法，使得能够由安装在发射器之前的时间到点火操作（例如最多7天）的整个操作时段的小容量的电池的稳定操作 ），并且在预定的公差（例如小于10ms）内减少多个烟火的点火正时的延迟和变化。解决方案：该装置包括：主单元; 和从单元20，每个具有从侧无线电通信单元22，其使得能够与主侧无线电通信单元进行交互式通信，点火电路28用于使点火电流流入保险丝头21;以及副计算机24，用于控制从侧无线电 通信单元22和点火电路28.次计算机24可以切换等待模式以交替地重复接收时间和休眠时间，以及可以连续接收的操作模式。 通过主单元的通信，多个从单元20的子计算机24从等待模式切换到操作模式，然后通过来自主单元的并发通信，指令同时点火到多个从单元 20。
-
公开(公告)号：JP2009287620A
公开(公告)日：2009-12-10
申请号：JP2008138883
申请日：2008-05-28
发明人： YAJIMA SUGURU , NAMIBA HISAYUKI , HORIGUCHI SHINJI
摘要： PROBLEM TO BE SOLVED: To provide a valve unit capable of improving response performance, capable of carrying out flow control of fluid, and suiting a thruster for spacecrafts.
SOLUTION: The valve unit V improving response performance, providing flow control of fluid without using a regulator, and suiting the thruster for spacecrafts is provided by a configuration equipped with a valve seat 6 having a communication hole 5 to be one part of a passage in a middle of the passage from an inlet side of the fluid to an outlet side, a ball 7 elastically retaining the communication hole 5 is a blocked state, a poppet 8 pushing the ball 7 through the communication hole 5, and a piezoelectric actuator 2 carrying out reciprocative driving the poppet 8.
COPYRIGHT: (C)2010,JPO&INPIT摘要翻译： 要解决的问题：提供能够改善响应性能的阀单元，能够执行流体的流量控制，并且适合用于航天器的推进器。 解决方案：具有改进响应性能的阀单元V，不使用调节器提供流体流量控制，并且适合用于航天器的推进器由配备有阀座6的构造提供，阀座6具有连通孔5，该连接孔5为一部分 在从流体的入口侧到出口侧的通道的中间的通道中，弹性地保持连通孔5的球7是阻塞状态，通过连通孔5推动球7的提升阀8和压电 执行器2执行往复驱动提升阀8.版权所有（C）2010，JPO＆INPIT
-
公开(公告)号：JP2008089265A
公开(公告)日：2008-04-17
申请号：JP2006272603
申请日：2006-10-04
发明人： KIMURA SATOHIDE
摘要： PROBLEM TO BE SOLVED: To provide a bullet shooting structure capable of reducing machining time and costs, and making a bullet unreusable after shooting.
SOLUTION: An inner face 15 of a guide member 14 (a barrel, a launcher) is formed as a smooth cylindrical face, a spin generating part 24 is provided on an outer circumference of a bullet 22, and at shooting of the bullet 22, the bullet 22 is rotated around an axis by advance while the spin generating part 24 shaves the inner face 15 of the guide member 14.
COPYRIGHT: (C)2008,JPO&INPIT摘要翻译： 要解决的问题：提供能够减少加工时间和成本的子弹拍摄结构，并且在拍摄后使子弹不可用。 解决方案：引导构件14（筒，发射器）的内表面15形成为平滑的圆柱面，在子弹22的外周设置旋转发生部24，并且在 子弹22，子弹22绕轴线转动，同时旋转发生部分24刮去引导部件14的内表面15.版权所有（C）2008，JPO＆INPIT
-
公开(公告)号：JP4072930B2
公开(公告)日：2008-04-09
申请号：JP19059598
申请日：1998-07-06
-
公开(公告)号：JP4048237B2
公开(公告)日：2008-02-20
申请号：JP11299698
申请日：1998-04-23
-
-
公开(公告)号：JP2007306715A
公开(公告)日：2007-11-22
申请号：JP2006132841
申请日：2006-05-11
发明人： OYORI HITOSHI , WAKITA MASAYA
摘要： PROBLEM TO BE SOLVED: To provide an actuator for achieving reduction in cost and improvement in the quality, and driving a plurality of control wings without troubles, when a compact rocket having the control wings is equipped with the actuator. SOLUTION: A plurality of motors 32 are respectively provided with a stator 33 and a rotor 34 and disposed in series. The stator 33 of the motor 32 is fixed to a fixing shaft 31, positioned at the shaft center of the motor 32, the rotor 34 is supported rotatably, and teeth 34a are provided on an outer circumference of the rotor 34 in the motor 32. The actuator 3 is disposed on a mechanical axis L. A plurality of rotating shafts 42 are disposed along the mechanical axis L and transmit rotational forces to the control wings 2; and small gears 45 are provided to the rotating shafts 42 and are engaged with the teeth 34a of the rotor 34 in the actuator 3. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译： 要解决的问题：当具有控制翼的紧凑型火箭配备有致动器时，提供用于实现成本降低和质量提高的致动器，并且驱动多个控制翼而没有麻烦。 解决方案：多个电动机32分别设置有定子33和转子34并串联布置。 电动机32的定子33固定在位于电动机32的轴心的固定轴31上，转子34可旋转地支撑，齿34a设置在电动机32的转子34的外周。 致动器3设置在机械轴线L上。多个旋转轴42沿着机械轴线L设置并将旋转力传递到控制翼2; 并且小齿轮45设置到旋转轴42并且与致动器3中的转子34的齿34a接合。版权所有（C）2008，JPO＆INPIT
-
-
-
-
-
-
-
搜索结果
276 条记录 (耗时 0.035 秒)
