公开(公告)号：US07102113B2

公开(公告)日：2006-09-05

申请号：US10781701

申请日：2004-02-20

申请人： Toshiharu Fujita ,  Shozo Hidaka

发明人： Toshiharu Fujita ,  Shozo Hidaka

IPC分类号： F41G7/00 ,  G05D1/00

CPC分类号： F42B10/663

摘要： A three-axis attitude control propulsion device and a flying object like a rocket including the device are provided in which combustion gas for attitude control can be efficiently used. A three-axis attitude control propulsion device 4, having six nozzles has a motor case 6 and three-way discharge changeover valves 10, 10′ of a valve plug rotation type enabling a changeover of a flow passage by rotation of the valve plug. Combustion gas 18 is generated by combustion of propellant 8 in the motor case 6. The three-axis attitude control propulsion device is operated so that one or two of the nozzles are opened to thereby discharge the combustion gas 18 and the remaining five or four nozzles are fully closed. Thereby, a three-axis attitude control of pitch control, roll control and yaw control, and control of a neutral state, can be selected.

摘要翻译： 提供三轴姿态控制推进装置和包括该装置的火箭等飞行物体，其中可以有效地使用用于姿态控制的燃烧气体。 具有六个喷嘴的三轴姿态控制推进装置4具有电动机壳体6和阀芯旋转型的三通排出切换阀10,10'，能够通过阀塞的旋转来切换流路。 燃烧气体18由推进剂8在电动机壳体6中的燃烧产生。 操作三轴姿态控制推进装置使得一个或两个喷嘴打开，从而排出燃烧气体18，剩下的五个或四个喷嘴完全关闭。 因此，可以选择俯仰控制，侧倾控制和偏航控制的三轴姿态控制以及中立状态的控制。

公开(公告)号：US07201362B2

公开(公告)日：2007-04-10

申请号：US10511147

申请日：2003-04-16

申请人： Shozo Hidaka

发明人： Shozo Hidaka

IPC分类号： F16K51/00

CPC分类号： F16K41/04 ,  F16J15/004 ,  F16K27/02

摘要： A thruster valve for controlling a flow of high temperature fluid, comprising a valve casing, a graphite liner, a drive rod, and at least one relief hole. The graphite liner is disposed in a through hole within the valve casing. The drive rod being slidably received in drive rod through holes within the graphite liner, such that a seal is formed and maintained between the drive rod and the graphite liner. The drive rod is arranged so as to be driven in an axial direction by an actuator attached to an end of the drive rod arranged outside the valve casing. At least one of the relief holes is formed to extend through the graphite liner and valve casing to communicate the cavity with the exterior of the valve casing provide a drain passage. Thus, leakage of the high temperature fluid is prevented.

摘要翻译： 一种用于控制高温流体流动的推进器阀，包括阀壳，石墨衬垫，驱动杆和至少一个释放孔。 石墨衬垫设置在阀壳内的通孔内。 驱动杆可滑动地容纳在驱动杆内，通过石墨衬垫内的孔，从而在驱动杆和石墨衬垫之间形成并保持密封。 驱动杆被布置成通过附接到布置在阀壳体外部的驱动杆的端部的致动器沿轴向驱动。 至少一个释放孔形成为延伸穿过石墨衬垫和阀壳体以将空腔与阀壳体的外部连通提供排水通道。 因此，防止了高温流体的泄漏。

公开(公告)号：US20060157662A1

公开(公告)日：2006-07-20

申请号：US10511147

申请日：2003-04-16

申请人： Shozo Hidaka

发明人： Shozo Hidaka

IPC分类号： F16K31/44

CPC分类号： F16K41/04 ,  F16J15/004 ,  F16K27/02

摘要： A high temperature resistant seal structure having no problem that an actuator is exposed to a high temperature environment to lead to an operation disorder, a valve having a reduced valve drive force and an aerospace craft side thruster are provided. In a high temperature resistant seal structure, provided in a casing into which a high temperature fluid is supplied, comprising a shaft through hole portion into which a shaft to be driven in an axial direction of the shaft is inserted passing through the shaft through hole portion, a liner, made of graphite, comprising a cavity formed therein and slidable holes provided at both end portions of the cavity is provided being inserted into the shaft through hole portion so that the shaft slidably passes through the slidable holes with a seal state being maintained between the shaft and the liner and a relief hole is provided being bored in a lateral direction relative to the axial direction of the shaft so that the cavity and the outside of the casing communicate with each other. By this construction, leakage of the high temperature fluid in the shaft axial direction is prevented, the surrounding parts and components connected to a shaft end portion are prevented from being exposed to the high temperature fluid and a shaft drive force is reduced. Also, the valve and aerospace craft side thruster comprising the present seal structure can be made smaller and lighter and reliability thereof can be enhanced.

摘要翻译： 提供了一种耐高温密封结构，其不存在致动器暴露于高温环境以导致操作障碍，具有减小的阀驱动力的阀和航空航天工艺侧推进器的问题。 在设置在供给高温流体的壳体中的耐高温密封结构中，包括轴贯通孔部，所述轴通孔部通过轴穿过所述轴通孔部而插入待轴驱动轴， 设置有由石墨构成的衬垫，其中形成有腔，并且设置在空腔的两个端部的可滑动孔设置在轴通孔部分中，使得轴可滑动地穿过可滑动的孔，并保持密封状态 在所述轴和所述衬套之间设置有相对于所述轴的轴向方向在横向上钻孔的释放孔，使得所述腔和所述壳体的外部彼此连通。 通过这种结构，防止高温流体在轴向方向上的泄漏，防止连接到轴端部的周围部件暴露于高温流体并减小轴驱动力。 此外，包括本密封结构的阀和航空航天工艺侧推进器可以做得更小和更轻，并且可以提高其可靠性。