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1. 发明申请

WO2007085378A2 MINIMIZING DYNAMIC STRUCTURAL LOADS OF AN AIRCRAFT 审中-公开
标题翻译：最小化飞机的动态结构载荷
公开(公告)号：WO2007085378A2
公开(公告)日：2007-08-02
申请号：PCT/EP2007000445
申请日：2007-01-19
申请人： AIRBUS FRANCE , WILDSCHEK ANDREAS , MAIER RUDOLF , HOFFMANN FALK , JEANNEAU MATTHIEU , AVERSA NICKY
发明人： WILDSCHEK ANDREAS , MAIER RUDOLF , HOFFMANN FALK , JEANNEAU MATTHIEU , AVERSA NICKY
IPC分类号： G05D1/00
CPC分类号： G05D1/0066
摘要： Minimizing dynamic structural loads of an aircraft (2), introduced by an external excitation (1 ), which, comprises generating a signal (x) indicative of the external excitation (1 ); deriving signals (y) of pre-controlling for actuating control elements of the aircraft (2) from said excitation indicating signal (x) in accordance with a pre-controlling rule, so as to reduce the dynamic structural loads introduced to the aircraft (2); generating an error signal (e, e*) representing performance of said pre-controlling; optimizing the pre-controlling rule by said error signal (e, e*) and/or said excitation indicating signal (x) so as to minimize the dynamic structural loads.
摘要翻译：最小化由外部激励（1）引入的飞行器（2）的动态结构负载，其包括产生指示外部激励（1）的信号（x）; 根据预先控制的规则从所述激励指示信号（x）导出用于致动飞行器（2）的控制元件的预控制信号（y），以便减少引入飞行器的动态结构负载（2 ）; 产生表示所述预控制性能的误差信号（e，e *）; 通过所述误差信号（e，e *）和/或所述激励指示信号（x）优化预控制规则，以使动态结构负载最小化。

2. 发明申请

WO2009013318A3 TEST ARRANGEMENT COMPRISING A TEST MODEL THAT HAS AT LEAST ONE CONTROL ELEMENT, AND AN ASSOCIATED METHOD 审中-公开
标题翻译：与至少一个控制综合试验模型和实验设计相关的方法
公开(公告)号：WO2009013318A3
公开(公告)日：2009-05-07
申请号：PCT/EP2008059667
申请日：2008-07-23
申请人： EADS DEUTSCHLAND GMBH , MAIER RUDOLF , WILDSCHEK ANDREAS
发明人： MAIER RUDOLF , WILDSCHEK ANDREAS
IPC分类号： G01M9/08
CPC分类号： G01M9/06
摘要： The invention relates to a test arrangement (10) having a test model (20), to which a flow (S) can be applied for flow-dynamic analysis and which has at least one control element (22, 23, 24, 25, 26) which essentially influences the flow behaviour of the test model (20). A flow setting device (60), which is arranged upstream of the test model (20) and is intended to influence the flow (S), and a sensor system (80) for detecting the flow (S) which is applied to the test model (20) are also provided, wherein the control element (22, 23, 24, 25, 26) can be adjusted on the basis of at least one value which is determined by the sensor system (80) and/or on the basis of the setting of the flow setting device (60). The invention also relates to such a method and to an actuator for use in such an arrangement or such a method.
摘要翻译：本发明涉及一种测试装置（10）与可以在用于流体动力分析被作用有流动（S）和所述至少一个实验模型（20）的流动行为的实验模型（20）被基本上影响控制元件（22，23，24，25 ，26）。用于在所述流（S），影响用于检测实验模型（20）的流动（S）和一传感器（80），其作用。此外，实验模型的上游（20）被布置流量调节装置（60），其中所述控制元件（22，23，，26）的至少一个（来自传感器80）确定的值和/或（取决于流量调节的设定的功能装置60）是可调节的24，25日此外，本发明涉及这样一种方法和在这样的布置或该方法中使用的致动器。

3. 发明申请

WO2009013323A3 AERODYNAMIC PROFILE, ACTUATOR FOR USE THEREIN AND TEST MODEL PROVIDED THEREWITH 审中-公开
标题翻译：空气动力学外形，在其中使用致动器和提供的测试模型
公开(公告)号：WO2009013323A3
公开(公告)日：2009-04-02
申请号：PCT/EP2008059673
申请日：2008-07-23
申请人： EADS DEUTSCHLAND GMBH , WILDSCHEK ANDREAS
发明人： WILDSCHEK ANDREAS
IPC分类号： B64C9/00 , B64C13/50 , B64C23/00 , B64C27/615 , H01L41/08
CPC分类号： B64C27/615 , B64C9/02 , B64C2027/7283 , H01L41/094 , Y02T50/34
摘要： The invention relates to an aerodynamic profile (400) which is provided on a side to be directed away from an incident flow (S) with a rear edge region (410) forming a rear edge (412). To make it possible for the rear edge (412) to combine a simple structure and extreme miniaturizability with the ability to be displaced or deformed so that even rapid adjustments are allowed, it is proposed that an actuator (418), which comprises a material or element (432) which can be contracted or expanded in a controlled manner, is provided inside the rear edge region (410) so that the rear edge (412) and/or the rear edge region (410) can be positionally modified and/or deformed at least partially.
摘要翻译：本发明涉及在事件流（S）abzuwendenden侧形成的后缘（412）后缘区域（410）具有的一个的空气动力学轮廓（400）。位移或变形，以用于以简单的结构和极端的小型化的高速控制所述后缘（412），所以建议的致动器（418）具有受控收缩或膨胀的材料或元件（432），后缘区域内（410）被设置用于在所述后缘（412）和/或后缘区域（410）的位置和/或变形的至少部分的变化。

4. 发明申请

WO2012168086A2 METHOD AND APPARATUS FOR MINIMIZING DYNAMIC STRUCTURAL LOADS OF AN AIRCRAFT 审中-公开
标题翻译：用于最小化飞机动态结构载荷的方法和装置
公开(公告)号：WO2012168086A2
公开(公告)日：2012-12-13
申请号：PCT/EP2012059718
申请日：2012-05-24
申请人： EADS DEUTSCHLAND GMBH , WILDSCHEK ANDREAS
发明人： WILDSCHEK ANDREAS
CPC分类号： B64C13/16 , G05D1/00 , G05D1/0066 , G05D1/0204 , G05D1/0623
摘要： The invention provides a method of dynamically alleviating loads generated on an aircraft (2) by a disturbance of gust and/or turbulence, the method comprising the steps of: on a flight of the aircraft (2), a monitoring is applied for automatically detecting a disturbance due to gust and/or turbulence and determining an incidence angle or angle of attack of the disturbance; when a disturbance due to gust and/or turbulence is detected, automatically generating control commands (36; 32, 38, 40, 42) for deflecting control surfaces dependent on the incidence angle or angle of attack; and applying the control commands (36; 32, 38, 40, 42) to deflect the control surfaces. For optimizing the performance, it is proposed to conduct at least one of the following step sequences A) and/or B): A) adapting the control commands (36; 32, 38, 40, 42) not only to the amount of the incidence angle or angle of attack but also to the gust length in order to adapt the deflection of the control surfaces both to the incidence angle or angle of attack and the gust length; and/or B) generating first control commands (y, 34; 32, 38) for first control surfaces and second control commands (36; 32, 38, 40, 42) for second control surfaces, comparing the incidence angle or angle of attack with a predetermined value and generating the first control commands (y, 34; 32, 38) to actuate the first control surface until the incidence angle reaches this predetermined value and generating the second control commands (36; 32, 38, 40, 42) to add a deflection of the second control surfaces when the incidence angle or angle of attack is above the predetermined value.
摘要翻译：本发明提供了一种通过由阵风和/或湍流扰动来动态地减轻在飞机（2）上产生的载荷的方法，所述方法包括以下步骤：在飞机（2）的飞行中，应用监测来自动检测由于阵风和/或湍流引起的扰动并确定扰动的入射角或迎角; 当检测到由于阵风和/或湍流引起的干扰时，根据入射角或迎角自动产生用于偏转控制面的控制命令（36; 32,38,40,42）; 以及施加所述控制命令（36; 32,38,40,42）以偏转所述控制表面。为了优化性能，建议进行以下步骤序列A）和/或B）中的至少一个：A）使控制命令（36; 32,38,40,42）不仅适应于入射角或迎角，也是阵风长度，以使控制表面的偏转适应入射角或迎角和阵风长度; 和/或B）为第一控制表面产生第一控制命令（y，34; 32,38）和用于第二控制表面的第二控制命令（36; 32,38,40,42），比较入射角或迎角具有预定值并产生第一控制命令（y，34; 32,38）来致动第一控制表面，直到入射角达到该预定值并产生第二控制命令（36; 32,38,40,42）当入射角或迎角高于预定值时，增加第二控制表面的偏转。

5. 发明申请

WO2009013326A2 INDUCTIVE GUST SENSOR 审中-公开
标题翻译：电感式楼层传感器
公开(公告)号：WO2009013326A2
公开(公告)日：2009-01-29
申请号：PCT/EP2008059676
申请日：2008-07-23
申请人： EADS DEUTSCHLAND GMBH , STEIGENBERGER JOSEF , WILDSCHEK ANDREAS
发明人： STEIGENBERGER JOSEF , WILDSCHEK ANDREAS
IPC分类号： G01P13/02
CPC分类号： G01P13/025 , B64C13/16 , B64D43/02 , G01D5/2013 , G01P13/02
摘要： The invention relates to a wind vane element (10) having a wind vane (12), which is oriented according to the wind direction, and having a rotation angle sensor (18) which provides an angular position of the wind vane (12) as a measurement signal, wherein the rotation angle sensor (18) operates in a contactless manner.
摘要翻译：本发明涉及一种具有一个导叶（12），其与风向对准，具有旋转角度传感器（18）的风力叶片构件（10），其提供所述风力叶片（12），为测量信号的角位置，其中，所述旋转角度传感器（18）无接触地进行操作。

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