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61. 发明申请

US20130054143A1 Real-Time Calculation of Total Longitudinal Force and Aerodynamic Drag Acting on a Rider on a Vehicle 审中-公开
标题翻译：实时计算车辆上的总纵向力和气动阻力作用
公开(公告)号：US20130054143A1
公开(公告)日：2013-02-28
申请号：US13695990
申请日：2011-05-05
申请人： Eric DeGolier
发明人： Eric DeGolier
IPC分类号： G01L1/00 , G06F19/00
CPC分类号： G01L1/247 , G01L5/13 , G01M9/06
摘要： A system and method of calculating under changing conditions in real-time aerodynamic drag acting on a rider on a vehicle. A computer receives a signal indicative of a force of the vehicle on the rider from at least one force sensor located at or near at least one point of contact between the rider and the vehicle. The computer determines aerodynamic drag acting on the rider on the vehicle from the received signal. These steps are repeated under changing conditions.
摘要翻译：一种在变化的条件下计算车辆上骑手的实时气动阻力的系统和方法。计算机从位于骑手与车辆之间的至少一个接触点处或附近的至少一个力传感器接收指示车辆在骑车人身上的力的信号。计算机根据接收到的信号确定作用在车辆上的乘客的气动阻力。在不断变化的条件下重复这些步骤。

62. 发明授权

US08386217B2 Method of determining a stiff value of an aerodynamic coefficient 有权
标题翻译：确定空气动力系数刚度值的方法
公开(公告)号：US08386217B2
公开(公告)日：2013-02-26
申请号：US12685924
申请日：2010-01-12
申请人： Benoit Calmels
发明人： Benoit Calmels
IPC分类号： G06F7/60 , G06F17/10
CPC分类号： G01M9/06
摘要： Method for determination of a rigid value of an aerodynamic coefficient of an aircraft, in which measurements are made in a wind tunnel on a model of the said aircraft and, on the basis of these measurements, at least one value, known as flexible model value, of this aerodynamic coefficient is determined, characterized in that a rigid value of the aerodynamic coefficient is calculated on the basis of the said flexible model value(s) and a correction taking into account the flexibility of the model. A plurality of flexible model values is determined on the basis of measurements made by varying the parameter q/E and maintaining the angle of incidence at a constant value, and the correction consists in an extrapolation operation providing a value of the aerodynamic coefficient corresponding to q/E=0. As a variant, a single flexible model is determined and the correction consists in adjusting the said value with the aid of a correction factor.
摘要翻译：用于确定飞机的空气动力系数的刚性值的方法，其中在所述飞行器的模型上的风洞中进行测量，并且在这些测量的基础上，至少一个称为柔性模型值的值确定该空气动力学系数，其特征在于，基于所述柔性模型值和考虑到模型的灵活性的校正来计算空气动力学系数的刚性值。基于通过改变参数q / E并将入射角保持在恒定值进行的测量来确定多个柔性模型值，并且校正包括提供与q相对应的空气动力系数的值的外插操作 / E = 0。作为变型，确定单个柔性模型，并且校正包括借助于校正因子来调整所述值。

63. 发明授权

US08255174B2 Method and device for determining critical buffeting loads on a structure of an aircraft 有权
标题翻译：用于确定飞机结构上的关键缓冲载荷的方法和装置
公开(公告)号：US08255174B2
公开(公告)日：2012-08-28
申请号：US12789309
申请日：2010-05-27
申请人： Guillermo Jenaro Rabadan , Juliane Havas , Stéphane Soumillon , Carole Despre-Flachard
发明人： Guillermo Jenaro Rabadan , Juliane Havas , Stéphane Soumillon , Carole Despre-Flachard
IPC分类号： G01L1/00
CPC分类号： G01M9/06 , G01M9/04 , G01M9/08
摘要： A method and device for determining critical buffeting loads on a structure of an aircraft is disclosed. The device (1) comprises means (2, UC) implementing a semi-empirical method for determining the critical loads generated by some buffeting on the structure of the airplane.
摘要翻译：公开了一种用于确定飞机结构上的临界缓冲载荷的方法和装置。装置（1）包括实现半经验方法的装置（2，UC），用于确定由飞机结构上的一些缓冲产生的临界负载。

64. 发明授权

US08061213B2 High temperature, high bandwidth pressure acquisition system 有权
标题翻译：高温，高带宽压力采集系统
公开(公告)号：US08061213B2
公开(公告)日：2011-11-22
申请号：US12321521
申请日：2009-01-22
申请人： Anthony D. Kurtz , Alexander A. Ned , Joseph Van DeWeert
发明人： Anthony D. Kurtz , Alexander A. Ned , Joseph Van DeWeert
IPC分类号： G01L9/06
CPC分类号： G01L9/00 , G01L9/065 , G01L15/00 , G01M9/06
摘要： A system for measuring a multiplicity of pressures as those experienced by a model in a wind tunnel is depicted. The system includes individual sensor devices which are connected to an Acquisition and Compensation electronics module. The individual sensor or transducer devices are semiconductor piezoresistive devices and are connected to the Acquisition and Compensation electronics module by means of a cable in a first embodiment. In an alternate embodiment the system uses connectors which connect each of the individual sensor devices to the Acquisition and Compensation electronics module via a mating connector located therein. The connectors may also include a memory which stores compensation coefficients associated with each of the various sensor devices. In this manner as described, the transducers which are small devices are connected via electrical lines or cables to the central Acquisition and Compensation electronics modules. This module houses electronics which digitally converts the data from the sensors and then compensates the data for temperature effects. The advantage of the system is that each individual sensor does not have any compensation and it can be made very small to operate at very high temperatures without any loss of accuracy. Thus, a large number of sensors can be utilized in a very small volume, even under extreme environmental conditions. It is noted that the Acquisition and Compensation electronics module can be located remotely in a safe environment outside of the wind tunnel and therefore respond extremely accurately to the pressure and temperatures subjected by the model in the wind tunnel.
摘要翻译：描绘了一种用于测量如风洞中的模型所经历的多种压力的系统。该系统包括连接到采集和补偿电子模块的各个传感器设备。单独的传感器或换能器装置是半导体压阻器件，并且在第一实施例中通过电缆连接到采集和补偿电子模块。在替代实施例中，系统使用通过位于其中的匹配连接器将各个传感器设备中的每一个连接到采集和补偿电子模块的连接器。连接器还可以包括存储器，其存储与各种传感器装置中的每一个相关联的补偿系数。以这种方式，小型设备的换能器通过电线或电缆连接到中央采集和补偿电子模块。该模块内置电子设备，数字转换传感器的数据，然后补偿温度影响的数据。该系统的优点是每个传感器不具有任何补偿，并且可以使其非常小以在非常高的温度下工作，而不会有任何的精度损失。因此，即使在极端的环境条件下，也可以以非常小的体积使用大量的传感器。需要注意的是，采集和补偿电子模块可以远程位于风洞外的安全环境中，因此对风洞中模型所承受的压力和温度非常准确地做出反应。

65. 发明申请

US20110268570A1 SYSTEM AND METHOD FOR CONTROLLING WIND TURBINE BLADES 有权
标题翻译：用于控制风力涡轮机叶片的系统和方法
公开(公告)号：US20110268570A1
公开(公告)日：2011-11-03
申请号：US12894453
申请日：2010-09-30
申请人： Jaikumar Loganathan , Subhrajit Dey , Klaus Ulrich Koegler , Manisekaran Santhanakrishnan
发明人： Jaikumar Loganathan , Subhrajit Dey , Klaus Ulrich Koegler , Manisekaran Santhanakrishnan
IPC分类号： F01D7/00
CPC分类号： G01M5/0016 , F03D7/0224 , F05B2220/709 , F05B2260/96 , G01L15/00 , G01M9/06 , Y02E10/723
摘要： A wind turbine system is presented. The wind turbine system includes a blade comprising an airfoil and a sensing device disposed on a surface of the airfoil, wherein the sensing device generates signals that are representative of pressure deflection on the surface of the airfoil. The wind turbine system further comprises a processing subsystem that receives location details of the sensing device and a transfer function corresponding to the airfoil, determines a location of a stagnation point on the surface of the airfoil based upon the signals and the location details, and determine an angle of attack (AOA) on the surface of the airfoil based upon the location of the stagnation point and the transfer function.
摘要翻译：介绍了风力发电机组系统。风力涡轮机系统包括叶片，其包括设置在翼型件的表面上的翼型件和感测装置，其中感测装置产生代表翼型件表面上的压力偏转的信号。风力涡轮机系统还包括处理子系统，其接收感测装置的位置细节和对应于翼型的传递函数，基于信号和位置细节确定翼型表面上的停滞点的位置，并且确定基于停滞点和传递函数的位置，在翼面的表面上的迎角（AOA）。

66. 发明授权

US07930073B2 Method and system for controlling airfoil actuators 有权
标题翻译：用于控制翼型执行器的方法和系统
公开(公告)号：US07930073B2
公开(公告)日：2011-04-19
申请号：US11159682
申请日：2005-06-23
申请人： Mark Glauser , Hiroshi Higuchi
发明人： Mark Glauser , Hiroshi Higuchi
IPC分类号： G05D1/08
CPC分类号： G01M9/065 , G01M9/06
摘要： A method of measuring the state of flow above an airfoil using an estimation of the velocity field based on a combination of Particle Image Velocimetry PIV and multiple surface pressure measurements processed through a POD/mLSE algorithm. Integral to the POD/mLSE algorithm is the estimation of the global POD coefficients. The utility of these time dependent coefficients, which are estimated from surface pressure only, are demonstrated in a simple proportional feedback loop (as the time series to drive the actuators) to keep the flow attached. This method requires realistic feedback flow control since surface measurements and not inflow measurements are required for practical applications. The estimation method works well with dynamic strain on flexible bodies and is not limited to estimation from pressure only.
摘要翻译：基于通过POD / mLSE算法处理的粒子图像测速PIV和多个表面压力测量的组合，使用基于速度场的估计来测量翼型上方的流动状态的方法。与POD / mLSE算法的一致性是估计全局POD系数。这些时间依赖系数的效用（仅从表面压力估计）在简单的比例反馈回路（作为驱动执行器的时间序列）中进行了演示，以保持流动的连接。该方法需要现实的反馈流量控制，因为实际应用需要表面测量而不是流入测量。估计方法对柔性体的动态应变效果良好，不限于压力估计。

67. 发明申请

US20100312497A1 METHOD AND DEVICE FOR DETERMINING CRITICAL BUFFETING LOADS ON A STRUCTURE OF AN AIRCRAFT 有权
标题翻译：用于确定飞机结构关键保压载荷的方法和装置
公开(公告)号：US20100312497A1
公开(公告)日：2010-12-09
申请号：US12789309
申请日：2010-05-27
申请人： Guillermo Jenaro Rabadan , Juliane Havas , Stephane Soumillon , Carole Despre-Flachard
发明人： Guillermo Jenaro Rabadan , Juliane Havas , Stephane Soumillon , Carole Despre-Flachard
IPC分类号： G01L1/00 , G06F19/00
CPC分类号： G01M9/06 , G01M9/04 , G01M9/08
摘要： A method and device for determining critical buffeting loads on a structure of an aircraft is disclosed. The device (1) comprises means (2, UC) implementing a semi-empirical method for determining the critical loads generated by some buffeting on the structure of the airplane.
摘要翻译：公开了一种用于确定飞机结构上的临界缓冲载荷的方法和装置。装置（1）包括实现半经验方法的装置（2，UC），用于确定由飞机结构上的一些缓冲产生的临界负载。

68. 发明申请

US20100222945A1 METHOD AND DEVICE FOR DETERMINING AERODYNAMIC CHARACTERISTICS OF AN AIRCRAFT 有权
标题翻译：用于确定飞机航行特征的方法和装置
公开(公告)号：US20100222945A1
公开(公告)日：2010-09-02
申请号：US12704661
申请日：2010-02-12
申请人： Hans-Gerd Giesseler , Wilfried Stegelmeier , Chloé Tauzin
发明人： Hans-Gerd Giesseler , Wilfried Stegelmeier , Chloé Tauzin
IPC分类号： G06F19/00
CPC分类号： G01M9/06
摘要： The present invention provides a device and method for determining aerodynamic characteristics of an aircraft, in particular a pitch moment coefficient at an ascending force of the aircraft without a horizontal tail plane of zero and an aerodynamic neutral point of the aircraft without a horizontal tail plane. In the method according to the invention, forces and mechanical flight parameters on aerofoils and a horizontal tail plane of the aircraft are detected at various detection instants during at least one non-stationary flight manoeuvre of the aircraft. In this case, a linear system of equations is formed, which comprises a pitch movement moment balance equation for each detection instant, the pitch movement moment balance equation having the detected forces and mechanical flight parameters. This linear system of equations is evaluated to calculate the aerodynamic characteristics.
摘要翻译：本发明提供一种用于确定飞行器的空气动力学特性的装置和方法，特别是在没有水平尾翼平面的情况下飞行器的上升力的俯仰力矩系数和没有水平尾翼平面的飞机的空气动力学中性点。在根据本发明的方法中，在飞行器的至少一次非平稳飞行操作期间，在各种检测时刻检测飞行器的机翼和水平尾翼面上的力和机械飞行参数。在这种情况下，形成线性方程式，其包括每个检测时刻的俯仰运动力矩平衡方程，具有检测力的俯仰运动力矩平衡方程和机械飞行参数。评估该线性方程组以计算空气动力特性。

69. 发明申请

US20090320582A1 Wind tunnel with a model arranged therein, particularly a model of an aircraft, for acquiring and evaluating a plurality of measuring data, as well as method 有权
标题翻译：具有布置在其中的模型的风洞，特别是飞行器的模型，用于获取和评估多个测量数据以及方法
公开(公告)号：US20090320582A1
公开(公告)日：2009-12-31
申请号：US11990350
申请日：2006-08-11
申请人： Uwe Milde
发明人： Uwe Milde
IPC分类号： G01M9/06
CPC分类号： G01M9/06
摘要： A wind tunnel with a model arranged therein, particularly a model of an aircraft, for acquiring and evaluating a plurality of measuring data, wherein the wind tunnel comprises at least one computer unit and at least one visual display terminal particularly at least one monitor, as well as at least one sensor for acquiring the measuring data. A plurality of measuring data of the wind tunnel, particularly measuring data on flow and/or pressure conditions on the model and/or in the region of the model, which data are determinable by the at least one sensor, can be processed in real time and with consideration of geometrical data of the model by the at least one computer unit and visualized on the at least one visual display terminal during a wind tunnel measurement.
摘要翻译：具有布置在其中的模型的风洞，特别是飞行器的模型，用于获取和评估多个测量数据，其中所述风洞包括至少一个计算机单元和至少一个视觉显示终端，特别是至少一个监视器，如以及用于获取测量数据的至少一个传感器。可以实时地处理风洞的多个测量数据，特别是测量关于模型上和/或模型区域中的流量和/或压力条件的数据，该数据可由该至少一个传感器确定并且考虑到至少一个计算机单元的模型的几何数据，并且在风洞测量期间在至少一个视觉显示终端上可视化。

70. 发明授权

US07634941B2 Sub-scale sonic boom modeling 有权
标题翻译：小型音响造型
公开(公告)号：US07634941B2
公开(公告)日：2009-12-22
申请号：US12010042
申请日：2008-01-18
申请人： Preston A. Henne , Donald C. Howe , Robert R. Wolz
发明人： Preston A. Henne , Donald C. Howe , Robert R. Wolz
IPC分类号： G01M9/00
CPC分类号： G01M9/06
摘要： A method for modeling the acoustic signature produced by an aircraft of interest flying at a particular supersonic Mach number/altitude operating point of interest. The method includes operating a sub-scale aircraft that is a sub-scale version of the aircraft of interest at a supersonic Mach number and at an altitude that are respectively different from the Mach number and the altitude associated with the operating point of interest. The Mach number and altitude at which the sub-scale aircraft is operated is selected such that peak overpressure generated by the sub-scale aircraft and time to rise to peak overpressure are the same as peak overpressure and time to rise to peak overpressure caused by operating the aircraft of interest at the operating point of interest.
摘要翻译：一种用于对由感兴趣的飞机在特定超音速马赫数/高度作业点处飞行产生的声学特征进行建模的方法。该方法包括以超音速马赫数和分别与马赫数和与感兴趣的运行点相关联的高度不同的高度操作作为感兴趣的飞机的子规模版本的次级飞行器。选择小型飞机运行的马赫数和高度，使得次级飞机产生的峰值超压和达到峰值超压的时间与峰值超压和上升到由运行引起的超压峰值的时间相同感兴趣的操作点的飞机。

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