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    Verification method of a flight control system using a transportable wind tunnel
    11.
    发明授权
    Verification method of a flight control system using a transportable wind tunnel 失效
    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。

    Three-dimensional free motion apparatus
    12.
    发明授权
    Three-dimensional free motion apparatus 失效
    三维自由运动装置

    公开(公告)号：US5501114A

    公开(公告)日：1996-03-26

    申请号：US191125

    申请日：1994-02-03

    申请人： Osamu Okamoto ,  Teruomi Nakaya

    发明人： Osamu Okamoto ,  Teruomi Nakaya

    IPC分类号： G09B9/00 ,  B64G7/00

    CPC分类号： B64G7/00

    摘要： A floating board is installed on a surface table through an extremely low friction plane sliding and supporting mechanism, such as using a gas bearing, of two-dimensional 3 freedom to thereby constitute a plane sliding mechanism portion, and a vertical sliding shaft tube supported to be enable translation in a vertical direction and connected to a balance belt for applying a balance weight is provided on the floating board through an extremely low friction vertical shaft sliding and supporting mechanism, such as a bas bearing, to thereby constitute a vertical shaft sliding mechanism portion. Further, a spherical shaft is installed above the vertical sliding shaft tube of the vertical shaft sliding mechanism portion through an extremely low friction 3-freedom rotational and supporting mechanism, such as using a gas bearing, to thereby constitute a 3-axis turning rotational mechanism portion, and a specimen model loading portion is provided on the spherical shaft to thereby obtain a three-dimensional free motion apparatus that can be applied to an agravic environment simulation experimental apparatus, an evaluation and test apparatus for a flexible-article handling work robot, and the like, in which as a whole, the 3-axis translation and the motion function of 3-axis turning 6-freedom can be secured in the extremely low friction state.

    摘要翻译： 通过诸如使用气体轴承的极低摩擦平面滑动和支撑机构来安装浮动板，其具有二维3自由度，从而构成平面滑动机构部分，以及垂直滑动轴管，其被支撑到 通过极低摩擦的垂直轴滑动和支撑机构（诸如底座轴承）在浮动板上提供垂直方向的平移和连接到用于施加平衡重的平衡皮带，从而构成垂直轴滑动机构 一部分。 此外，通过诸如使用气体轴承的极低摩擦的3自由度的旋转和支撑机构，在立轴滑动机构部分的垂直滑动轴管上方安装球轴，由此构成3轴转动旋转机构 部分，并且在球面轴上设置样本模型加载部，从而获得可应用于柔性物品处理作业机器人的恶劣环境模拟实验装置，评价和测试装置的三维自由运动装置， 其中整体上可以在极低的摩擦状态下确保3轴转动6自由度的3轴平移和运动功能。

    Superprecision positioning device
    14.
    发明授权
    Superprecision positioning device 失效
    超精密定位装置

    公开(公告)号：US4749898A

    公开(公告)日：1988-06-07

    申请号：US13523

    申请日：1987-02-11

    申请人： Seizo Suzuki ,  Teruomi Nakaya ,  Yoshio Hayashi

    发明人： Seizo Suzuki ,  Teruomi Nakaya ,  Yoshio Hayashi

    IPC分类号： H02K15/16 ,  B23Q1/54 ,  B25J9/10 ,  B25J9/14 ,  F16C23/10 ,  G05D3/00 ,  H01L21/00 ,  H01L41/09 ,  H02K7/075

    CPC分类号： H01L21/67138 ,  B23Q1/5481 ,  B25J9/105 ,  B25J9/108 ,  B25J9/14 ,  F16C23/10 ,  H02K7/075 ,  H02N2/0095 ,  Y10T74/2111

    摘要： A superprecision positioning device includes an output shaft rotor, a plurality of eccentric shaft rotors including an inner eccentric shaft rotor and an outer eccentric shaft rotor, and a bearing base cylinder, electrically rotating and driving mechanism portions being provided between the eccentric shaft rotor and the output shaft rotor, and between the outer eccentric shaft rotor and the bearing base cylinder, respectively, whereby the eccentric shaft rotors and the output shaft rotor may be independently rotated and controlled. With this arrangement, movement in three degrees of freedom may be achieved by translational movement and rotation of the output shaft in a two-dimensional surface, and if an axially movable support shaft is inserted in the output shaft, an article being positioned may be moved with four degrees of freedom in total, providing superprecision positioning in units of 1/10 micron.

    摘要翻译： 超精度定位装置包括输出轴转子，包括内偏心轴转子和外偏心轴转子的多个偏心轴转子和轴承基座圆筒，电旋转和驱动机构部分设置在偏心轴转子和 输出轴转子和外偏心轴转子与轴承座圆筒之间，由此能够独立地旋转和控制偏心轴转子和输出轴转子。 通过这种布置，可以通过在二维表面中的输出轴的平移运动和旋转来实现三自由度的运动，并且如果轴向可移动的支撑轴插入输出轴中，则定位的物品可以移动 总共具有四个自由度，以1/10微米的单位提供超精密定位。

    High-altitude capable wide velocity range flight velocity vector measurement probe and measurement system
    15.
    发明授权
    High-altitude capable wide velocity range flight velocity vector measurement probe and measurement system 有权
    高空能力宽速度范围飞行速度矢量测量探头和测量系统

    公开(公告)号：US07480548B2

    公开(公告)日：2009-01-20

    申请号：US11224030

    申请日：2005-09-13

    申请人： Masashi Shigemi ,  Akira Koike ,  Makoto Ueno ,  Tomonari Hirotani ,  Teruomi Nakaya ,  Hiroshi Wakai ,  Toru Iwata

    发明人： Masashi Shigemi ,  Akira Koike ,  Makoto Ueno ,  Tomonari Hirotani ,  Teruomi Nakaya ,  Hiroshi Wakai ,  Toru Iwata

    IPC分类号： G01P5/165 ,  G01P5/175

    CPC分类号： G01P5/175 ,  G01C5/005 ,  G01P5/16 ,  G01P13/025

    摘要： It is an object of the present invention to solve the problem of a drop in precision in conventional systems using a square pyramid type five-hole probe due to the drop in atmospheric pressure in high altitude ranges, and to provide a wide velocity range flight velocity vector measurement system that can prevent a drop in measurement precision. Furthermore, it is also an object of the present invention to provide a method for eliminating the effects of detection fluctuations caused by adhering water droplets, ice particles or dust in a wide velocity range flight velocity vector measurement system. The flight velocity vector measurement probe of the present invention comprises means in which a static pressure hole is formed in the tube wall surface of the probe, so that a static pressure value is obtained from the pressure detected by this static pressure hole, the Mach number M is calculated on the basis of an equation approximated by a fourth-order polynomial of the static pressure/total pressure signal and the angle of attack, and in cases where an abnormal detection value is detected, this is replaced by the preceding detection value.

    摘要翻译： 本发明的一个目的是解决由于在高海拔范围内的大气压力下降而使用方形棱锥型五孔探针的常规系统的精度下降的问题，并且提供宽的速度范围飞行速度 矢量测量系统，可以防止测量精度下降。 此外，本发明的另一个目的是提供一种消除在宽速度范围飞行速度矢量测量系统中粘附水滴，冰粒或灰尘引起的检测波动的影响的方法。 本发明的飞行速度矢量测量探头包括在探针的管壁表面中形成静压孔的装置，从而由​​该静压孔检测到的压力获得静压值，马赫数 基于由静压/总压力信号的四次多项式近似的方程式计算出M，并且在检测到异常检测值的情况下，将其替换为前一检测值。

    Arithmetic processing method and system in a wide velocity range flight velocity vector measurement system using a square truncated pyramid-shape five-hole pitot probe
    17.
    发明授权
    Arithmetic processing method and system in a wide velocity range flight velocity vector measurement system using a square truncated pyramid-shape five-hole pitot probe 有权
    算术处理方法和系统在宽速度范围内飞行速度矢量测量系统采用方形截头棱锥形五孔皮托探测器

    公开(公告)号：US06336060B1

    公开(公告)日：2002-01-01

    申请号：US09661411

    申请日：2000-09-13

    申请人： Masashi Shigemi ,  Teruomi Nakaya ,  Shigemi Shindo ,  Minoru Takizawa ,  Takeshi Ohnuki

    发明人： Masashi Shigemi ,  Teruomi Nakaya ,  Shigemi Shindo ,  Minoru Takizawa ,  Takeshi Ohnuki

    IPC分类号： G01C2110

    CPC分类号： G01P13/025 ,  G01P5/165

    摘要： An arithmetic processing method and system in a wide velocity range flight velocity vector measurement system using a square truncated pyramid-shape five-hole Pitot probe. Approximation equations that determine attack angle &agr; and sideslip angle &bgr; in the form of third-order equations concerning attack angle pressure coefficient C&agr; and sideslip angle pressure coefficient C&bgr;, which are known numbers, are expressed in the form of a polynomial equation concerning Mach number M, where the coefficients are obtained from a lookup table. Coefficient calculations in the polynomial equation, and attack angle a and sideslip angle &bgr;, calculations may be performed as simple calculations by specifying and applying known numbers into the approximation equation without solving third-order equations, with calibration coefficients that form the basis of coefficient calculation with the polynomial equation first being stored in memory in advance as a table for each wide velocity range on the basis of wind tunnel testing. A Mach number may be calculated instantly from a lookup table by specifying Mach pressure coefficient CM and angle to airflow pressure coefficient C&ggr;. Wide velocity range flight velocity vector measurement with a high update rate which is capable of real time response in flight control as demanded by aircraft is obtained.

    摘要翻译： 一种使用方形截头棱锥形五孔皮托探测器的宽速度范围飞行速度矢量测量系统中的算术处理方法和系统。 确定攻角α和侧滑角β的近似方程式以关于马赫数M的多项式方程式的形式表示为关于攻角角压力系数Calpha和侧滑角压力系数Cbeta的三阶方程形式 ，其中系数是从查找表获得的。 多项式方程中的系数计算和攻角α和侧滑角β可以通过在不求解三阶方程的情况下通过将已知数字指定和应用已知的数字作为简单的计算来执行计算，其中校准系数构成系数计算的基础 其中多项式方程首先作为基于风洞测试的每个宽速度范围的表预先存储在存储器中。 可以通过指定马赫压力系数CM和与气流压力系数Cgam的角度从查找表立即计算马赫数。 获得具有高飞行速度矢量测量的高速更新速率，能够根据飞机所要求的飞行控制中的实时响应。

    Flight velocity vector measuring system in wide velocity region using truncated pyramid-shape probe
    18.
    发明授权
    Flight velocity vector measuring system in wide velocity region using truncated pyramid-shape probe 失效
    飞行速度矢量测量系统在宽速度区域使用截头棱锥形探针

    公开(公告)号：US06176130B1

    公开(公告)日：2001-01-23

    申请号：US09004272

    申请日：1998-01-08

    申请人： Teruomi Nakaya ,  Naoaki Kuwano ,  Seigou Nakamura ,  Asao Hanzawa

    发明人： Teruomi Nakaya ,  Naoaki Kuwano ,  Seigou Nakamura ,  Asao Hanzawa

    IPC分类号： G01C2100

    CPC分类号： G01P5/165 ,  G01P13/025

    摘要： A flight velocity vector measuring system in a wide velocity region in which an attack angle pressure coefficient C&agr; of air current, a sideslip angle pressure coefficient C&bgr; and an air current angle pressure coefficient C&ggr; are obtained from five pressure information detected by a square truncated pyramid-shape probe. The aforementioned pressure coefficients, pressure calibration coefficients with respect to a Mach number M, an attack angle &agr; and a sideslip angle &bgr; every velocity region obtained by dividing the wide velocity region into a plurality of regions stored in advance in the calculation processor, and a Mach number M, an attack angle &agr; and a sideslip angle &bgr; of unknown quantity constitute a calculation processing expression comprising a polynomial approximation to call the pressure calibration coefficients in the velocity region, and flight velocity vectors (M, &agr;, &bgr;) are calculated by the polynomial approximation.

    摘要翻译： 在宽速度区域中的飞行速度矢量测量系统，其中从由截顶棱锥形截面检测到的五个压力信息获得空气流的攻角角压力系数Calpha，侧滑角压力系数Cbeta和气流角压力系数C gamma， 形状探针。 上述压力系数，相对于马赫数M的压力校准系数，通过将宽速度区域划分为预先存储在计算处理器中的多个区域而获得的每个速度区域的攻角α和侧滑角β，以及 马赫数M，未知量的攻角α和侧滑角β构成计算处理表达式，其包括用于调用速度区域中的压力校准系数的多项式近似，并且飞行速度矢量（M，α，β）由 多项式近似。

    Truncated pyramid-shape multi-hole pitot probe and flight velocity detection system using said truncated pyramid-shape multi-hole pitot probe
    19.
    发明授权
    Truncated pyramid-shape multi-hole pitot probe and flight velocity detection system using said truncated pyramid-shape multi-hole pitot probe 失效
    截锥金字塔形多孔皮托探头和飞行速度检测系统采用截头棱锥形多孔皮托探针

    公开(公告)号：US5423209A

    公开(公告)日：1995-06-13

    申请号：US249068

    申请日：1994-05-25

    申请人： Teruomi Nakaya ,  Masao Ebihara ,  Yoshio Hayashi ,  Seizo Suzuki ,  Naoaki Kuwano ,  Asao Hanzawa ,  Takashi Saitow ,  Mitsuo Usami ,  Toru Iwata

    发明人： Teruomi Nakaya ,  Masao Ebihara ,  Yoshio Hayashi ,  Seizo Suzuki ,  Naoaki Kuwano ,  Asao Hanzawa ,  Takashi Saitow ,  Mitsuo Usami ,  Toru Iwata

    IPC分类号： G01F1/46 ,  G01P5/16 ,  G01P5/165 ,  G01P13/02 ,  G01C21/00

    CPC分类号： G01F1/46 ,  G01P13/025 ,  G01P5/165

    摘要： A flight velocity detection system using a truncated pyramid-shape multi-e Pitot probe in which an extreme end portion has a truncated pyramid-shape, a cylindrical hole is provided at the apex thereof, a total pressure tube of a smaller diameter than that of the cylindrical hole is secured at a position by a predetermined length determined by a relationship with the diameter of the cylindrical hole from the extreme end of the cylindrical hole, and groups of pressure holes comprised of a plurality of pressure holes are arranged in each of the truncated pyramid surfaces of the truncated pyramid shape. Items of pressure information detected by the probe are input into a velocity vector processor to convert them into electric signals, and signals are processed using pressure coefficients of the holes of the probe with respect to the velocity vector stored in advance in the velocity vector processor to calculate flight velocity vector (V, .alpha., .beta.) with respect to the probe axis from the pressure information and air density.

    摘要翻译： 使用截头棱锥形多孔皮托探头的飞行速度检测系统，其顶端具有截头棱锥形，圆柱形孔设置在其顶点，直径小于 圆柱形孔被固定在与圆柱形孔的前端与圆柱形孔的直径关系确定的预定长度的位置处，并且由多个压力孔组成的一组压力孔布置在 截头棱锥形截面金字塔表面。 由探头检测到的压力信息的项目被输入到速度矢量处理器中以将它们转换为电信号，并且使用相对于预先存储在速度矢量处理器中的速度向量的探针的孔的压力系数来处理信号， 从压力信息和空气密度计算相对于探针轴的飞行速度矢量（V，α，β）。