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公开(公告)号：US20100181415A1
公开(公告)日：2010-07-22
申请号：US12666421
申请日：2008-06-05
申请人： Andree Altmikus , Markus Bauer , Boris Grohmann , Stephan Mangelsdorf , Christoph Maucher , Rupert Pfaller , Elif Ahci
发明人： Andree Altmikus , Markus Bauer , Boris Grohmann , Stephan Mangelsdorf , Christoph Maucher , Rupert Pfaller , Elif Ahci
CPC分类号： B64C27/473 , B64C27/615 , B64C2027/7283 , Y02T50/34
摘要： The invention relates to a rotor blade (20), especially for a rotary wing aircraft. The invention is characterized in that an aerodynamically effective rotor blade profile with a profile nose region (21), a profile base body (20a) with a profile core, an upper and lower cover skin (30) that envelops the profile core (22), and a profile rear edge region (23) with a rear edge (40) and a reversibly bendable supporting member (26) that can be attached with the first end to the end region of the profile base body (20a) pointing toward the rear edge (40) and projects with the second end freely out of the profile base body (20a) and its end region toward the rear edge (40) and forms a movable rotor blade flap (24), and several actuators (35) that are dynamically connected to the projecting second end of the reversibly bendable supporting member (26) and an arc-shaped flap deflection can be initiated via the change in length of the actuators, the second end of the reversibly bendable supporting member (26) that forms the rotor blade flap (24) viewed in the direction of the span (S) being divided by notches (34) into several segments to which at least one actuator (35) at a time is assigned.
摘要翻译： 本发明涉及一种转子叶片（20），特别是用于旋翼飞机。 本发明的特征在于，具有轮廓鼻部区域（21），具有轮廓芯的轮廓基体（20a），包围轮廓芯（22）的上部和下部覆盖皮肤（30））的空气动力学有效的转子叶片轮廓， ，以及具有后边缘（40）和可逆弯曲的支撑构件（26）的型材后边缘区域（23），其可以将第一端附接到指向后侧的型材基体（20a）的端部区域 边缘（40）并且其第二端自由地突出到轮廓基体（20a）之外并且其端部区域朝向后边缘（40）突出并且形成可动转子叶片挡板（24），并且几个致动器（35） 动态地连接到可逆弯曲的支撑构件（26）的突出的第二端，并且可以经由致动器的长度的改变来启动弧形的翼片偏转，形成可逆弯曲支撑构件的可逆弯曲的支撑构件（26）的第二端 转子叶片翼片（24）沿sp方向观察 一个（S）被切口（34）划分成多个段，至少一个致动器（35）一次分配给该段。
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公开(公告)号：US08727265B2
公开(公告)日：2014-05-20
申请号：US13440160
申请日：2012-04-05
申请人： Andree Altmikus , Marius Bebesel
发明人： Andree Altmikus , Marius Bebesel
CPC分类号： B64C27/82 , B64C39/008 , B64C2027/8236
摘要： The invention is related to a helicopter (10) comprising a main rotor (12), a cycloidal rotor (14) and a rotating cylinder (18). The rotating cylinder (18) extends along a longitudinal axis of a tail boom (13). The cycloidal rotor (14) extends at least partly along said same tail boom (13) and rotates outside the rotating cylinder (18).
摘要翻译： 本发明涉及包括主转子（12），摆线转子（14）和旋转圆筒（18）的直升机（10）。 旋转圆筒（18）沿尾梁（13）的纵向轴线延伸。 摆线转子（14）至少部分地沿着所述相同的尾部悬臂（13）延伸并旋转到旋转圆筒（18）的外部。
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公开(公告)号：US08162607B2
公开(公告)日：2012-04-24
申请号：US12158928
申请日：2006-12-08
IPC分类号： B64C27/615
CPC分类号： B64C27/615 , B64C2027/7283 , B64C2027/7288 , Y02T50/34
摘要： A rotor blade including a rotor blade profile including a profile tip region, a profile trailing edge region including a trailing edge and a profile body having a profile core. A covering skin including an upper skin and a lower skin encase the profile core. A reversibly bendable flexural actuator including a first actuator end disposed at the trailing edge region of the rotor blade profile and a second actuator end projecting past the profile body toward the trailing edge. The second actuator end forms part of the trailing edge region and forms a movable rotor blade flap, the movable rotor blade flap being deformable into an arc-shaped rotor blade flap deflection upon a bending of the flexural actuator.
摘要翻译： 一种转子叶片，其包括转子叶片轮廓，该转子叶片轮廓包括轮廓顶端区域，轮廓后缘区域，包括后缘和具有轮廓芯的轮廓体。 包括上皮和下皮的覆盖皮包围型芯。 一种可逆地弯曲的弯曲致动器，包括设置在转子叶片轮廓的后缘区域的第一致动器端部和向轮廓体朝向后缘突出的第二致动器端部。 第二致动器端部构成后缘区域的一部分并且形成可动转子叶片挡板，可动转子叶片挡板可变形成在弯曲致动器的弯曲时偏转的弧形转子叶片。
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公开(公告)号：US20090269198A1
公开(公告)日：2009-10-29
申请号：US12158928
申请日：2006-12-08
IPC分类号： F01D5/00
CPC分类号： B64C27/615 , B64C2027/7283 , B64C2027/7288 , Y02T50/34
摘要： A rotor blade including a rotor blade profile including a profile tip region, a profile trailing edge region including a trailing edge and a profile body having a profile core. A covering skin including an upper skin and a lower skin encase the profile core. A reversibly bendable flexural actuator including a first actuator end disposed at the trailing edge region of the rotor blade profile and a second actuator end projecting past the profile body toward the trailing edge. The second actuator end forms part of the trailing edge region and forms a movable rotor blade flap, the movable rotor blade flap being deformable into an arc-shaped rotor blade flap deflection upon a bending of the flexural actuator.
摘要翻译： 一种转子叶片，其包括转子叶片轮廓，该转子叶片轮廓包括轮廓顶端区域，轮廓后缘区域，包括后缘和具有轮廓芯的轮廓体。 包括上皮和下皮的覆盖皮包围型芯。 一种可逆地弯曲的弯曲致动器，包括设置在转子叶片轮廓的后缘区域的第一致动器端部和向轮廓体朝向后缘突出的第二致动器端部。 第二致动器端部构成后缘区域的一部分并且形成可动转子叶片挡板，可动转子叶片挡板可变形成在弯曲致动器的弯曲时偏转的弧形转子叶片。
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公开(公告)号：US20080226448A1
公开(公告)日：2008-09-18
申请号：US12048480
申请日：2008-03-14
申请人： Andree Altmikus , Rupert Pfaller , Bernhard Enenkl
发明人： Andree Altmikus , Rupert Pfaller , Bernhard Enenkl
IPC分类号： B64C27/467 , B64C27/615
CPC分类号： B64C27/001
摘要： An aerodynamic profile includes a main profile body defining a profile depth direction and being shear-flexible in the profile depth direction, a tension-stiff and compression-stiff upper covering skin, a tension-stiff and compression-stiff lower covering skin, wherein the upper and lower covering skins envelope the main profile body, a bearingless and hingeless rear profile deformation region disposed at a rear edge region, and at least one actuator disposed in the main profile body. The at least one actuator is configured to initiate a flexural motion of the main profile body resulting in a curvature of the upper and lower covering skins and to deform the rear profile deformation region and so as to yield a flap deflection directed opposite to a direction of the flexural motion.
摘要翻译： 空气动力学轮廓包括限定轮廓深度方向并且在轮廓深度方向上具有剪切柔性的主轮廓体，张力刚性和压缩刚性的上覆盖皮肤，张紧刚性和压缩刚性的下覆盖皮肤，其中 上部和下部覆盖皮肤包围主轮廓体，设置在后边缘区域的无轴承和无铰链后轮廓变形区域，以及设置在主轮廓体中的至少一个致动器。 所述至少一个致动器被配置为启动主轮廓体的弯曲运动，导致上部和下部覆盖皮肤的曲率，并且使后部轮廓变形区域变形，并产生相对于 弯曲运动。
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公开(公告)号：US20120256042A1
公开(公告)日：2012-10-11
申请号：US13440160
申请日：2012-04-05
申请人： Andree Altmikus , Marius Bebesel
发明人： Andree Altmikus , Marius Bebesel
IPC分类号： B64C27/82
CPC分类号： B64C27/82 , B64C39/008 , B64C2027/8236
摘要： The invention is related to a helicopter (10) comprising a main rotor (12), a cycloidal rotor (14) and a rotating cylinder (18). The rotating cylinder (18) extends along a longitudinal axis of a tail boom (13). The cycloidal rotor (14) extends at least partly along said same tail boom (13) and rotates outside the rotating cylinder (18).
摘要翻译： 本发明涉及包括主转子（12），摆线转子（14）和旋转圆筒（18）的直升机（10）。 旋转圆筒（18）沿尾梁（13）的纵向轴线延伸。 摆线转子（14）至少部分地沿着所述相同的尾部悬臂（13）延伸并旋转到旋转圆筒（18）的外部。
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公开(公告)号：US08215908B2
公开(公告)日：2012-07-10
申请号：US12048480
申请日：2008-03-14
申请人： Andree Altmikus , Rupert Pfaller , Bernhard Enenkl
发明人： Andree Altmikus , Rupert Pfaller , Bernhard Enenkl
CPC分类号： B64C27/001
摘要： An aerodynamic profile includes a main profile body defining a profile depth direction and being shear-flexible in the profile depth direction, a tension-stiff and compression-stiff upper covering skin, a tension-stiff and compression-stiff lower covering skin, wherein the upper and lower covering skins envelope the main profile body, a bearingless and hingeless rear profile deformation region disposed at a rear edge region, and at least one actuator disposed in the main profile body. The at least one actuator is configured to initiate a flexural motion of the main profile body resulting in a curvature of the upper and lower covering skins and to deform the rear profile deformation region and so as to yield a flap deflection directed opposite to a direction of the flexural motion.
摘要翻译： 空气动力学轮廓包括限定轮廓深度方向并且在轮廓深度方向上具有剪切柔性的主轮廓体，张力刚性和压缩刚性的上覆盖皮肤，张紧刚性和压缩刚性的下覆盖皮肤，其中 上部和下部覆盖皮肤包围主轮廓体，设置在后边缘区域的无轴承和无铰链后轮廓变形区域，以及设置在主轮廓体中的至少一个致动器。 所述至少一个致动器被配置为启动主轮廓体的弯曲运动，导致上部和下部覆盖皮肤的曲率，并且使后部轮廓变形区域变形，并产生相对于 弯曲运动。
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