-
1.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。
-
2.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。
-
3.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。
-
4.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。
-
5.发明申请公开(公告)号：US20110263044A1
公开(公告)日：2011-10-27
申请号：US13056355
申请日：2008-07-22
申请人： Ulrich Reidt , Alois Friedberger , Christoph Heller , Thomas Ziemann , Harald Waltenberger , Günter Müller
发明人： Ulrich Reidt , Alois Friedberger , Christoph Heller , Thomas Ziemann , Harald Waltenberger , Günter Müller
IPC分类号： G01N33/53
CPC分类号： B03C1/286 , B03C1/288 , B03C2201/18 , B03C2201/26 , C12M47/02 , G01N1/2202 , G01N1/2273 , G01N1/4077 , G01N35/0098
摘要： An apparatus and a method for automatic detection of particles, in particular, biological particles such as micro-organisms. The apparatus has a device for binding the particles to separating particles which can be bound selectively to the particles. The apparatus further includes a separating device for extraction of the separating particles with bound particles from a collecting fluid, and a detection unit for detecting a number and/or concentration of the particles separated in this manner. The device for binding the particles to the separating particles includes a collecting device for collecting a collecting fluid including the separating particles and the particles that are provided by a particle-fluid mixture.
摘要翻译： 用于自动检测颗粒的设备和方法，特别是生物颗粒如微生物。 该装置具有用于将颗粒结合到可以选择性地结合到颗粒的分离颗粒的装置。 该装置还包括用于从收集流体中提取具有结合颗粒的分离颗粒的分离装置和用于检测以这种方式分离的颗粒的数量和/或浓度的检测单元。 用于将颗粒结合到分离颗粒的装置包括用于收集包括分离颗粒和由颗粒 - 流体混合物提供的颗粒的收集流体的收集装置。
-
6.发明申请High Temperature Pressure Sensor Element, Particularly for Measuring Pressures Inside Jet Engines, Method for the Production Thereof and Component for Jet Engines 有权高温压力传感器元件，特别是用于喷射发动机内部的测量压力，其生产方法和喷射发动机部件公开(公告)号：US20090183573A1
公开(公告)日：2009-07-23
申请号：US12281946
申请日：2007-03-01
申请人： Soeren Fricke , Gerhard Mueller , Alois Friedberger , Eberhard Rose , Thomas Ziemann , Ulrich Schmid , Dimitri Telitschkin , Stefan Ziegenhagen
发明人： Soeren Fricke , Gerhard Mueller , Alois Friedberger , Eberhard Rose , Thomas Ziemann , Ulrich Schmid , Dimitri Telitschkin , Stefan Ziegenhagen
CPC分类号： G01L9/0051 , G01L19/04 , G01L23/18 , Y10T29/49826
摘要： A high-temperature pressure sensor element for power units includes a substrate, in which an interior space is developed, a deformable membrane, which separates the interior space from the exterior space in order to deform when the exterior pressure changes, and a strain measuring element, which is arranged on the membrane, for measuring the deformation of the membrane. The substrate, the membrane, and the strain measuring element are manufactured from the same high-temperature-stable material, such as an alloy. By way of example a nickel base alloy may be used. A component for a power unit, such as a turbine blade for an airplane or rocket engine, includes an integrated high-temperature pressure sensor element of this type.
摘要翻译： 用于动力单元的高温压力传感器元件包括其中内部空间被展开的基板，可变形的膜，其将内部空间与外部空间分离以在外部压力变化时变形，并且应变测量元件 ，其布置在膜上，用于测量膜的变形。 基板，膜和应变测量元件由相同的高温稳定材料如合金制造。 作为示例，可以使用镍基合金。 用于动力单元的部件，例如用于飞机或火箭发动机的涡轮机叶片，包括这种类型的集成的高温压力传感器元件。
-
7.发明申请METHOD AND DEVICE FOR DETECTING EXPLOSIVE-SUBSTANCE PARTICLES IN A GAS FLOW 审中-公开用于检测气体流中爆炸性物质颗粒的方法和装置公开(公告)号：US20130199271A1
公开(公告)日：2013-08-08
申请号：US13809413
申请日：2011-06-17
CPC分类号： G01N1/4005 , G01N1/2205 , G01N1/2214 , G01N1/40 , G01N1/405 , G01N33/0057 , G01N2001/022
摘要： A method for detecting explosive substance particles in a gas flow includes passing the gas flow through an adsorption net for a specified time period so as to adsorb explosive-substance particles in the gas flow on the adsorption net. The adsorption not includes a microfilter having a pore size that is smaller than the particle size of the explosive-substance particles. The adsorption net is heated to a heating temperature so as to desorb the explosive-substance particles from the adsorption net. A gas flow comprising the desorbed explosive-substance particles is supplied to a detector so as to detect the explosive-substance particles.
摘要翻译： 用于检测气体流中的爆炸物质颗粒的方法包括使气流通过吸附网一段特定的时间段，以便吸附在吸附网上的气流中的爆炸性物质颗粒。 吸附不包括孔径小于爆炸性物质粒子的粒径的微过滤器。 吸附网被加热到加热温度，以便从吸附网解吸爆炸物质颗粒。 将包含解吸的爆炸性物质颗粒的气流供给检测器，以检测爆炸性物质颗粒。
-
8.发明授权High temperature pressure sensor element, particularly for measuring pressures inside jet engines, method for the production thereof and component for jet engines 有权高温压力传感器元件，特别用于测量喷气发动机内部的压力，其生产方法和喷气发动机部件公开(公告)号：US08001844B2
公开(公告)日：2011-08-23
申请号：US12281946
申请日：2007-03-01
申请人： Soeren Fricke , Gerhard Mueller , Alois Friedberger , Eberhard Rose , Thomas Ziemann , Ulrich Schmid , Dimitri Telitschkin , Stefan Ziegenhagen
发明人： Soeren Fricke , Gerhard Mueller , Alois Friedberger , Eberhard Rose , Thomas Ziemann , Ulrich Schmid , Dimitri Telitschkin , Stefan Ziegenhagen
IPC分类号： G01L13/02
CPC分类号： G01L9/0051 , G01L19/04 , G01L23/18 , Y10T29/49826
摘要： A high-temperature pressure sensor element for power units includes a substrate, in which an interior space is developed, a deformable membrane, which separates the interior space from the exterior space in order to deform when the exterior pressure changes, and a strain measuring element, which is arranged on the membrane, for measuring the deformation of the membrane. The substrate, the membrane, and the strain measuring element are manufactured from the same high-temperature-stable material, such as an alloy. By way of example a nickel base alloy may be used. A component for a power unit, such as a turbine blade for an airplane or rocket engine, includes an integrated high-temperature pressure sensor element of this type.
摘要翻译： 用于动力单元的高温压力传感器元件包括其中内部空间被展开的基板，可变形的膜，其将内部空间与外部空间分离以在外部压力变化时变形，并且应变测量元件 ，其布置在膜上，用于测量膜的变形。 基板，膜和应变测量元件由相同的高温稳定材料如合金制造。 作为示例，可以使用镍基合金。 用于动力单元的部件，例如用于飞机或火箭发动机的涡轮机叶片，包括这种类型的集成的高温压力传感器元件。
-
公开(公告)号：US20120171661A1
公开(公告)日：2012-07-05
申请号：US13383167
申请日：2010-07-06
申请人： Ulrich Reidt , Alois Friedberger , Christoph Heller , Hero Brahms
发明人： Ulrich Reidt , Alois Friedberger , Christoph Heller , Hero Brahms
CPC分类号： G01N33/54333
摘要： The invention discloses a method for detecting at least one antigen, comprising the following steps: providing magnetic beads, which are coated with antibodies specific for at least one antigen to be detected; bringing the magnetic beads in contact with a washing buffer that comprises at least 8% BSA and incubating the mixture with a sample; isolating the magnetic beads by means of a magnetic separator; and detecting the antigens bound to the magnetic beads by the antibodies. Washing buffers, primers, kits and devices that can be used for said method are also disclosed.
摘要翻译： 本发明公开了一种用于检测至少一种抗原的方法，包括以下步骤：提供用针对待检测的至少一种抗原特异的抗体包被的磁珠; 使磁珠与包含至少8％BSA的洗涤缓冲液接触并将混合物与样品一起孵育; 通过磁选机隔离磁珠; 并通过抗体检测与磁珠结合的抗原。 还公开了可用于所述方法的洗涤缓冲液，底漆，试剂盒和装置。
-
公开(公告)号：US20120052251A1
公开(公告)日：2012-03-01
申请号：US13318670
申请日：2010-04-28
申请人： Christoph Heller , Ulrich Reidt , Alois Friedberger , Karin Bauer
发明人： Christoph Heller , Ulrich Reidt , Alois Friedberger , Karin Bauer
IPC分类号： B32B3/30 , B01J31/02 , B01J37/02 , B32B3/26 , C12N9/00 , B32B9/04 , B32B5/16 , B01J35/02 , C09K3/18
CPC分类号： B08B17/06 , F03D80/40 , F05B2230/90 , Y02E10/72 , Y02E10/722 , Y02P70/523 , Y10T428/24612 , Y10T428/249978 , Y10T428/25
摘要： The invention relates to a self-cleaning self-regenerating surface structure and/or a self-cleaning self-regenerating coating. For improving the cleaning function, the invention proposes a self-regenerating surface structure, especially coating, comprising biocatalytic and/or anti-icing molecules on an exposed surface of said surface structure, especially coating, and biocatalytic and/or anti-icing molecules embedded or contained in said surface structure, especially coating. Further, the invention relates to an object provided with such surface structure or coating and a method for producing the same.
摘要翻译： 本发明涉及自清洁自再生表面结构和/或自清洁自再生涂层。 为了改善清洁功能，本发明提出了一种自再生表面结构，特别是涂层，其包括在所述表面结构的暴露表面上的生物催化和/或防冰分子，特别是涂层，以及嵌入的生物催化和/或防冰分子 或包含在所述表面结构中，特别是涂层。 此外，本发明涉及具有这种表面结构或涂层的物体及其制造方法。
-
-
-
-
-
-
-
-
-
搜索结果
29 条记录 (耗时 0.019 秒)
