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    • 6. 发明授权
    • Docking and active damping device for space structures
    • 空间结构的对接和主动阻尼装置
    • US5005786A
    • 1991-04-09
    • US402586
    • 1989-09-05
    • Osamu OkamotoTeruomi NakayaSeizo SuzukiNaoaki KuwanoYoshinori SakaiHiroshi OdaMasao UegusaGoji Iba
    • Osamu OkamotoTeruomi NakayaSeizo SuzukiNaoaki KuwanoYoshinori SakaiHiroshi OdaMasao UegusaGoji Iba
    • B64G1/38B64G1/64F16F15/02
    • B64G1/646
    • A docking and active damping device for space structures is provided, in a docking portion of one space structure to be docked, with a positioning device in which an output rotor can be moved and rotated within a two-dimensional plane by a composite rotation of one or more eccentric rotors capable of being independently driven and controlled by a direct drive motor and the output rotor, and a docking member having a docking ring and a latch mechanism are supported on the output rotor of the positioning device. A probe having a capture device capable of being protruded and driven in an axial direction by a linear motion is provided inwardly of the docking member, and the probe provides a 4-freedom movement according to a position of the passive side to capture and dock a drogue. The docking ring is supported through a strain sensor, a vibration of the passive side structure is detected, and the docking member is moved in a direction of suppressing the vibration to promptly suppress the vibration caused by disturbances from the inside and outside of the space structures.
    • 在一个待对接的一个空间结构的对接部分中提供用于空间结构的对接和主动阻尼装置,其具有定位装置,在该定位装置中,输出转子可以在二维平面内通过复合旋转 或更多的能够由直接驱动马达和输出转子独立驱动和控制的偏心转子,并且具有对接环和闩锁机构的对接构件被支撑在定位装置的输出转子上。 具有能够通过线性运动在轴向方向突出并被驱动的捕获装置的探针设置在对接构件的内部,并且探针根据被动侧的位置来捕获和对准一个4自由度的运动 流氓 对接环通过应变传感器支撑,检测到被动侧结构的振动,并且对接构件沿抑制振动的方向移动,以迅速地抑制由空间结构的内部和外部的干扰引起的振动 。
    • 7. 发明授权
    • Transportable three-dimensional calibration wind tunnel system,
verification method of flight control system using said system and
flight simulator using said system
    • 运输三维校准风洞系统,使用该系统的飞行控制系统的验证方法和使用该系统的飞行模拟器
    • US5866813A
    • 1999-02-02
    • US751478
    • 1996-11-18
    • Teruomi NakayaOsamu OkamotoNaoaki KuwanoSeizo SuzukiShuichi SasaHidehiko NakayasuMasakazu Sagisaka
    • Teruomi NakayaOsamu OkamotoNaoaki KuwanoSeizo SuzukiShuichi SasaHidehiko NakayasuMasakazu Sagisaka
    • G09B9/00B64F5/00G01M9/02G01M9/06G09B9/08
    • G01M9/065G01M9/06
    • A transportable three-dimensional calibration wind tunnel system is comprised of a small wind tunnel portion for creating a three-dimensional calibration air having a suitable wind velocity, and a two-axis rotational deformation device portion for causing said wind tunnel portion to effect a conical motion with a nozzle blow port being an apex to suitably change a flow angle. The two-axis rotational deformation device is comprised of a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and a .alpha.-angle rotational deformation device having a .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point. In a method for the verification of a flight control system of an aircraft using the transportable three-dimensional calibration wind tunnel system, the nozzle blow port of the three-dimensional calibration wind tunnel system is positioned at the extreme end of an air data sensor probe provided on the aircraft, and the three-dimensional calibration wind tunnel system and an on-board control computer of the aircraft are connected to an out-board control computer so that a suitable three-dimensional airflow is generated by the three-dimensional calibration wind tunnel system to verify the operation and function of the control surface in the stopped state on the ground.
    • 可移动的三维校准风洞系统包括用于产生具有合适风速的三维校准空气的小风洞部分和用于使所述风洞部分实现锥形的两轴旋转变形装置部分 具有喷嘴吹出口作为顶点的运动以适当地改变流动角度。 双轴旋转变形装置由具有被支撑为水平旋转的β角变形基体的β角旋转变形装置和具有被支撑为垂直旋转的α角变形基体的α角旋转变形装置 。 α角变形基底的旋转轴线,β角变形基底的旋转轴线和小风洞部分的中心轴线被布置成使得它们在一个点处相交。 在使用可运输的三维校准风洞系统验证飞机的飞行控制系统的方法中,三维校准风洞系统的喷嘴吹出口位于空气数据传感器探头的末端 飞机上提供的三维校准风洞系统和飞机的车载控制计算机连接到外板控制计算机,从而通过三维校准风产生合适的三维气流 隧道系统验证控制面在地面停止状态下的运行和功能。
    • 8. 发明授权
    • Transportable three-dimensional calibration wind tunnel system,
verification method of flight control system and flight simulator using
same
    • 可移动三维校准风洞系统,飞行控制系统验证方法和飞行模拟器使用相同
    • US5627311A
    • 1997-05-06
    • US517969
    • 1995-08-22
    • Teruomi NakayaOsamu OkamotoNaoaki KuwanoSeizo SuzukiShuichi SasaHidehiko NakayasuMasakazu Sagisaka
    • Teruomi NakayaOsamu OkamotoNaoaki KuwanoSeizo SuzukiShuichi SasaHidehiko NakayasuMasakazu Sagisaka
    • G09B9/00B64F5/00G01M9/02G01M9/06G01M9/04G01M17/00
    • G01M9/065G01M9/06
    • A transportable three-dimensional calibration wind tunnel system consists of a small wind tunnel portion for creating a three-dimensional airflow having a suitable wind velocity, and a two-axis rotational deformation device portion for causing the wind tunnel portion to effect a conical motion with a nozzle blow port being in close proximity to an apex to suitably change a flow angle. The two-axis rotational deformation device includes a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and an .alpha.-angle rotational deformation device having an .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point. When verifying a flight control system of an aircraft using the transportable three-dimensional calibration wind tunnel system, the nozzle blow port of the three-dimensional calibration wind tunnel system is positioned at the extreme end of an air data sensor probe provided on the aircraft, and the three-dimensional calibration wind tunnel system and an on-board control computer of the aircraft are connected to an out-board control computer so that a suitable three-dimensional airflow is generated by the three-dimensional calibration wind tunnel system to verify the operation and function of the control surface in the stopped state on the ground.
    • 可移动的三维校准风洞系统由用于产生具有合适风速的三维气流的小风洞部分和用于使风洞部分进行锥形运动的双轴旋转变形装置部分组成, 喷嘴吹出口靠近顶点以适当地改变流动角度。 双轴旋转变形装置包括具有被支撑为水平旋转的β角变形基体的β角转动变形装置,以及被支撑为垂直旋转的α角变形基体的α角旋转变形装置。 α角变形基底的旋转轴线,β角变形基底的旋转轴线和小风洞部分的中心轴线被布置成使得它们在一个点处相交。 当使用可运输的三维校准风洞系统验证飞行器的飞行控制系统时,三维校准风洞系统的喷嘴吹出口位于设置在飞行器上的空气数据传感器探头的最末端, 并将飞机的三维校准风洞系统和车载控制计算机连接到外板控制计算机,以便通过三维校准风洞系统产生合适的三维气流,以验证 控制面在地面停止状态下的操作和功能。
    • 10. 发明授权
    • Verification method of a flight control system using a transportable
wind tunnel
    • 使用可运输风洞的飞行控制系统的验证方法
    • US5756891A
    • 1998-05-26
    • US751477
    • 1996-11-18
    • Teruomi NakayaOsamu OkamotoNaoaki KuwanoSeizo SuzukiShuichi SasaHidehiko NakayasuMasakazu Sagisaka
    • Teruomi NakayaOsamu OkamotoNaoaki KuwanoSeizo SuzukiShuichi SasaHidehiko NakayasuMasakazu Sagisaka
    • G09B9/00B64F5/00G01M9/02G01M9/06G05D1/08
    • G01M9/065G01M9/06
    • A transportable three-dimensional calibration wind tunnel system consisting of a small wind tunnel portion for creating a three-dimensional airflow having a suitable wind velocity, and a two-axis rotational deformation device portion for causing the wind tunnel portion to effect a conical motion with a nozzle blow port being in close proximity to an apex to suitably change a flow angle. The two-axis rotational deformation device includes a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and an .alpha.-angle rotational deformation device having an .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point. When verifying a flight control system of an aircraft using the transportable three-dimensional calibration wind tunnel system, the nozzle blow port of the three-dimensional calibration wind tunnel system is positioned at the extreme end of an air data sensor probe provided on the aircraft, and the three-dimensional calibration wind tunnel system and an on-board control computer of the aircraft are connected to an out-board control computer so that a suitable three-dimensional airflow is generated by the three-dimensional calibration wind tunnel system to verify the operation and function of the control surface in the stopped state on the ground.
    • 一种可移动的三维校准风洞系统,包括用于产生具有合适风速的三维气流的小风洞部分和用于使风洞部分进行圆锥运动的双轴旋转变形装置部分, 喷嘴吹出口靠近顶点以适当地改变流动角度。 双轴旋转变形装置包括具有被支撑为水平旋转的β角变形基体的β角转动变形装置,以及被支撑为垂直旋转的α角变形基体的α角旋转变形装置。 α角变形基底的旋转轴线,β角变形基底的旋转轴线和小风洞部分的中心轴线被布置成使得它们在一个点处相交。 当使用可运输的三维校准风洞系统验证飞行器的飞行控制系统时,三维校准风洞系统的喷嘴吹出口位于设置在飞行器上的空气数据传感器探头的最末端, 并将飞机的三维校准风洞系统和车载控制计算机连接到外板控制计算机,以便通过三维校准风洞系统产生合适的三维气流,以验证 控制面在地面停止状态下的操作和功能。