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1. 发明授权

US5866813A Transportable three-dimensional calibration wind tunnel system, verification method of flight control system using said system and flight simulator using said system 失效
标题翻译：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
公开(公告)号：US5866813A
公开(公告)日：1999-02-02
申请号：US751478
申请日：1996-11-18
申请人： Teruomi Nakaya , Osamu Okamoto , Naoaki Kuwano , Seizo Suzuki , Shuichi Sasa , Hidehiko Nakayasu , Masakazu Sagisaka
发明人： Teruomi Nakaya , Osamu Okamoto , Naoaki Kuwano , Seizo Suzuki , Shuichi Sasa , Hidehiko Nakayasu , Masakazu Sagisaka
IPC分类号： G09B9/00 , B64F5/00 , G01M9/02 , G01M9/06 , G09B9/08
CPC分类号： G01M9/065 , G01M9/06
摘要： 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.
摘要翻译：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。

2. 发明授权

US5627311A Transportable three-dimensional calibration wind tunnel system, verification method of flight control system and flight simulator using same 失效
标题翻译：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
公开(公告)号：US5627311A
公开(公告)日：1997-05-06
申请号：US517969
申请日：1995-08-22
申请人： Teruomi Nakaya , Osamu Okamoto , Naoaki Kuwano , Seizo Suzuki , Shuichi Sasa , Hidehiko Nakayasu , Masakazu Sagisaka
发明人： Teruomi Nakaya , Osamu Okamoto , Naoaki Kuwano , Seizo Suzuki , Shuichi Sasa , Hidehiko Nakayasu , Masakazu Sagisaka
IPC分类号： G09B9/00 , B64F5/00 , G01M9/02 , G01M9/06 , G01M9/04 , G01M17/00
CPC分类号： G01M9/065 , G01M9/06
摘要： 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.
摘要翻译：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。

3. 发明授权

US5756891A Verification method of a flight control system using a transportable wind tunnel 失效
标题翻译：使用可运输风洞的飞行控制系统的验证方法
公开(公告)号：US5756891A
公开(公告)日：1998-05-26
申请号：US751477
申请日：1996-11-18
申请人： Teruomi Nakaya , Osamu Okamoto , Naoaki Kuwano , Seizo Suzuki , Shuichi Sasa , Hidehiko Nakayasu , Masakazu Sagisaka
发明人： Teruomi Nakaya , Osamu Okamoto , Naoaki Kuwano , Seizo Suzuki , Shuichi Sasa , Hidehiko Nakayasu , Masakazu Sagisaka
IPC分类号： G09B9/00 , B64F5/00 , G01M9/02 , G01M9/06 , G05D1/08
CPC分类号： G01M9/065 , G01M9/06
摘要： 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.
摘要翻译：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。

4. 发明授权

US5797105A Air active control aircraft using three dimensional true airspeed detection system 失效
标题翻译：空中主动控制飞机采用三维真空速度检测系统
公开(公告)号：US5797105A
公开(公告)日：1998-08-18
申请号：US975110
申请日：1997-11-20
申请人： Teruomi Nakaya , Osamu Okamoto , Naoaki Kuwano , Seizo Suzuki , Shuichi Sasa , Hidehiko Nakayasu , Masakazu Sagisaka
发明人： Teruomi Nakaya , Osamu Okamoto , Naoaki Kuwano , Seizo Suzuki , Shuichi Sasa , Hidehiko Nakayasu , Masakazu Sagisaka
IPC分类号： G01P5/16 , B64C13/18 , G01P5/165 , G01P13/02 , G05D1/06 , G05D1/08 , G05D1/10 , G06F165/00
CPC分类号： G01P5/165 , G01P13/025 , G05D1/0638 , G05D1/0816
摘要： An air active control aircraft having an air three-dimensional true airspeed detection system composed of an air data sensor probe in the form of a truncated pyramid-shape Pitot probe and an air flight velocity operation processor for calculating an air flight velocity vector from three-dimensional air pressure information detected by the air data sensor probe, airframe motion detection sensors for detecting an airframe motion, and an on-board control computer for generating a flight control law. The on-board control computer inputs an air flight velocity vector signal obtained from the air flight velocity vector device into a control-surface control system in parallel with airframe motion detection sensor signals, and presumes a flight motion induced by a change in air to generate the flight control law for quickly carrying out air flight stability control.
摘要翻译：一种具有空气三维真空速检测系统的空气动力控制飞机，其特征在于，包括以截锥形的皮托特探针形式的空气数据传感器探头和用于从三角锥形皮托探针的空中飞行速度矢量计算的空中飞行速度运算处理器，由空气数据传感器探测器检测的三维空气压力信息，用于检测机身运动的机身运动检测传感器，以及用于产生飞行控制定律的车载控制计算机。车载控制计算机将从空中飞行速度矢量装置获得的空中飞行速度矢量信号输入到与机身运动检测传感器信号并联的控制表面控制系统中，并且假定由空气变化引起的飞行运动产生飞行控制法快速执行飞行稳定性控制。

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