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14 条记录 (耗时 0.012 秒)

    Three-axis attitude control propulsion device and flying object comprising the same
    1.
    发明授权
    Three-axis attitude control propulsion device and flying object comprising the same 有权
    三轴姿态控制推进装置和飞行物体相同

    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。

    Universal joint
    6.
    发明授权
    Universal joint 失效
    万向节

    公开(公告)号：US4826342A

    公开(公告)日：1989-05-02

    申请号：US104181

    申请日：1987-10-05

    申请人： Toshiharu Fujita

    发明人： Toshiharu Fujita

    IPC分类号： F16D3/16 ,  F16C11/06 ,  F16D3/46 ,  F16D3/00

    CPC分类号： F16D3/46 ,  F16C11/06 ,  Y10T403/32041 ,  Y10T403/32181 ,  Y10T403/32786

    摘要： A universal joint having first and second shaft members respectively including a pair of yoke portions and a ball member disposed between the first and second shaft members for movably interconnecting the same. The respective first and second shaft members are constituted by two separate half-elements together with forming the respective pair of yoke portions. Base seats respectively having a truncated cone shape are provided in mutually opposing faces of the yoke portions such that each virtual cone has a virtual vertex having an angle of substantially 90 degrees and at the same time the virtual vertexes of the cones are substantially in contact with each other, the base seats respectively defining arc faces in mutually opposing surfaces thereof. And, the arc faces respectively have a central axis in a direction transverse to the shaft members and are formed by a part of a peripheral face of a virtual cylinder having the same diameter as the ball member which is rotatably supported between these arc faces.

    摘要翻译： 一种万向接头，其具有分别包括一对轭部的第一和第二轴构件和设置在第一和第二轴构件之间用于可动地互连的球构件。 相应的第一和第二轴构件由两个单独的半元件构成，并且形成相应的一对轭部。 分别具有截头圆锥形状的底座设置在轭部的相互相对的面中，使得每个虚拟锥体具有基本上为90度的角度的虚拟顶点，并且同时，锥体的虚拟顶点基本上与 彼此相对，基座分别在相互相对的表面中限定弧面。 并且，弧面分别在与轴构件横向的方向上具有中心轴线，并且由虚拟圆柱体的外周面的一部分形成，该虚拟圆柱体的圆周直径与可旋转地支撑在这些圆弧面之间的球部件的直径相同。

    Side thruster valve and side thruster device
    9.
    发明授权
    Side thruster valve and side thruster device 有权

    公开(公告)号：US06986246B2

    公开(公告)日：2006-01-17

    申请号：US10441039

    申请日：2003-05-20

    申请人： Toshiharu Fujita

    发明人： Toshiharu Fujita

    IPC分类号： F02K1/18

    CPC分类号： F02K9/92 ,  F02K9/32 ,  F02K9/44 ,  F02K9/88

    摘要： A side thruster valve of an aerospace craft is improved to reduce torque of a servo-motor, etc. needed for nozzle opening and closing to thereby realize a compact and light weight device. The side thruster valve comprises a valve plug having its back directed to an axis of the aerospace craft and independently movable between a fully opened position and a fully closed position of the valve plug in a plane orthogonal to the axis of the aerospace craft, an actuating means for moving the valve plug in an axial direction of the valve plug and an elastic member for activating the valve plug in the axial direction of the valve plug. In a side thruster device comprising a plurality of the side thruster valves, the side thruster valves are arranged independently of each other to thereby broaden freedom of combustion control and improve fuel consumption.