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1.发明授权Aerodynamic profile for aircraft and wind power stations and method of measuring the thickness of ice on an aerodynamic profile 有权飞机和风力发电站的空气动力学特性以及测量空气动力学特性中冰的厚度的方法公开(公告)号：US08434365B2
公开(公告)日：2013-05-07
申请号：US12280770
申请日：2007-02-26
CPC分类号： B64D15/20 , F03D80/40 , G01B17/025 , Y02E10/72
摘要： An aerodynamically shaped profile member for aircraft and wind power stations includes, for example, phased-array ultrasonic generator arrangement arranged therein. During operation of the profile member, the ultrasonic generator emits ultrasonic waves in a targeted manner in multiple directions to determine a profile of the thickness of an ice layer on the surface of the aerodynamic profile. The structure may be, for example, a composite fiber material arranged around a foam core, with the ultrasonic generator arrangement being laminated into the composite fiber material. For measurement of the ice thickness, ultrasonic waves are transmitted in a targeted manner to different positions of the surface of the aerodynamic profile, and the ultrasonic waves reflected on the interfaces of the ice layer are detected. At least one region of the surface is scanned by means of the targeted ultrasonic waves, to determine an ice thickness profile.
摘要翻译： 用于飞机和风力发电站的空气动力学形状的构件包括例如布置在其中的相控阵超声波发生器装置。 在轮廓构件的操作期间，超声波发生器以多个方向以目标方式发射超声波，以确定空气动力学轮廓表面上的冰层的厚度分布。 该结构可以是例如布置在泡沫芯周围的复合纤维材料，其中超声波发生器装置被层压到复合纤维材料中。 为了测量冰厚度，超声波以目标方式传播到空气动力学轮廓表面的不同位置，并且检测在冰层的界面上反射的超声波。 通过目标超声波扫描表面的至少一个区域，以确定冰厚度分布。
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2.发明申请Aerodynamic Profile for Aircraft and Wind Power Stations and Method of Measuring the Thickness of Ice on an Aerodynamic Profile 有权飞机和风力发电站的空气动力学参数和测量空气动力学剖面上的冰厚度的方法公开(公告)号：US20090189020A1
公开(公告)日：2009-07-30
申请号：US12280770
申请日：2007-02-26
IPC分类号： B64D15/20
CPC分类号： B64D15/20 , F03D80/40 , G01B17/025 , Y02E10/72
摘要： An aerodynamically shaped profile member for aircraft and wind power stations includes, for example, phased-array ultrasonic generator arrangement is arranged therein. During operation of the profile member, the ultrasonic generator emits ultrasonic waves in a targeted manner in multiple directions to determine a profile of the thickness of an ice layer on the surface of the aerodynamic profile. The structure may be, for example, a composite fiber material arranged around a foam core, with the ultrasonic generator arrangement being laminated into the composite fiber material. For measurement of the ice thickness, ultrasonic waves are transmitted in a targeted manner to different positions of the surface of the aerodynamic profile, and the ultrasonic waves reflected on the interfaces of the ice layer are detected. At least one region of the surface is scanned by means of the targeted ultrasonic waves, to determine an ice thickness profile.
摘要翻译： 用于飞机和风力发电站的空气动力学形状的构件包括例如相关阵列超声波发生器装置。 在轮廓构件的操作期间，超声波发生器以多个方向以目标方式发射超声波，以确定空气动力学轮廓表面上的冰层的厚度分布。 该结构可以是例如布置在泡沫芯周围的复合纤维材料，其中超声波发生器装置被层压到复合纤维材料中。 为了测量冰厚度，超声波以目标方式传播到空气动力学轮廓表面的不同位置，并且检测在冰层的界面上反射的超声波。 通过目标超声波扫描表面的至少一个区域，以确定冰厚度分布。
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3.发明授权Integrated sensor for airfoils of aircraft, particularly of airplanes and helicopters, as well as rotor blades and airplane airfoil 失效用于飞机，特别是飞机和直升机，以及转子叶片和飞机机翼的翼型的集成传感器公开(公告)号：US07726200B2
公开(公告)日：2010-06-01
申请号：US11591585
申请日：2006-11-02
IPC分类号： G01M5/00
CPC分类号： G01L19/0084 , B64D43/00 , G01L19/003 , G01L19/0038 , G01L19/0636 , G01L19/147
摘要： An integratable sensor for an airfoil of an aircraft such as an airplane and a helicopter comprises a sensor capsule, in whose inner chamber a measuring element for measuring an environmental parameter is situated. A capsule carrier is implemented to accommodate and removably attach the sensor capsule and is integratable in an airfoil of an airplane or a helicopter. Elastic contact elements are used for secure electrical connection of the sensor capsule to the capsule carrier. The sensor capsule is replaceable, while the capsule carrier is permanently integrated in the airfoil, in particular in a rotor blade. The measuring element is, for example, a pressure sensor.
摘要翻译： 用于诸如飞机和直升机的飞机的翼型的可整合传感器包括传感器胶囊，其内室中设置有用于测量环境参数的测量元件。 实施胶囊载体以容纳和可移除地附接传感器囊，并且可与飞机或直升机的翼型集成。 弹性接触元件用于传感器胶囊与胶囊载体的牢固电连接。 传感器胶囊是可替换的，而胶囊载体永久地集成在翼型件中，特别是在转子叶片中。 测量元件例如是压力传感器。
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4.发明申请Integrated Sensor For Airfoils of Aircraft, Particularly Of Airplanes and Helicopters, As Well As Rotor Blades and Airplane Airfoil 失效飞机，特别是飞机和直升机的翼型集成传感器，以及转子叶片和飞机机翼公开(公告)号：US20070186672A1
公开(公告)日：2007-08-16
申请号：US11591585
申请日：2006-11-02
IPC分类号： G01M5/00
CPC分类号： G01L19/0084 , B64D43/00 , G01L19/003 , G01L19/0038 , G01L19/0636 , G01L19/147
摘要： An integratable sensor for an airfoil of an aircraft such as an airplane and a helicopter comprises a sensor capsule, in whose inner chamber a measuring element for measuring an environmental parameter is situated. A capsule carrier is implemented to accommodate and removably attach the sensor capsule and is integratable in an airfoil of an airplane or a helicopter. Elastic contact elements are used for secure electrical connection of the sensor capsule to the capsule carrier. The sensor capsule is replaceable, while the capsule carrier is permanently integrated in the airfoil, in particular in a rotor blade. The measuring element is, for example, a pressure sensor.
摘要翻译： 用于诸如飞机和直升机的飞机的翼型的可整合传感器包括传感器胶囊，其内室中设置有用于测量环境参数的测量元件。 实施胶囊载体以容纳和可移除地附接传感器囊，并且可与飞机或直升机的翼型集成。 弹性接触元件用于传感器胶囊与胶囊载体的牢固电连接。 传感器胶囊是可替换的，而胶囊载体永久地集成在翼型件中，特别是在转子叶片中。 测量元件例如是压力传感器。
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