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1. 发明授权

US06336060B1 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
标题翻译：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。

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