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1. 发明申请

US20090001223A1 Flexible Control Surface for an Aircraft 审中-公开
标题翻译：灵活的飞机控制面
公开(公告)号：US20090001223A1
公开(公告)日：2009-01-01
申请号：US12158405
申请日：2006-12-20
申请人： Boris Grohmann , Peter Konstanzer , Thomas Lorkowski
发明人： Boris Grohmann , Peter Konstanzer , Thomas Lorkowski
IPC分类号： B64C3/48
CPC分类号： B64C3/48 , B64C3/50 , B64C9/00
摘要： A flexible control surface (1; 11, 14) comprises at least two actuators (3), which act on the control surface (1; 11, 14) at different points of action (2) which are offset laterally with respect to the circulating-flow direction (6) with respect to one another. The at least two actuators (3) are designed such that the points of action (2) can be deflected differently when the actuators (3) are operated at the same time. It is thus possible to elastically deform the control surface (1; 11, 14), in particular along the span width direction (9), without kinks, in which case it is possible to achieve uniform transitions along the control surface laterally with respect to the flow direction (6). The invention makes it possible to reduce vortices and noise induced by the control surface.
摘要翻译：柔性控制表面（1; 11,14）包括至少两个致动器（3），其在不同的作用点（2）处作用在控制表面（1; 11,14）上，所述不同的作用点（2）相对于循环 - 流方向（6）。至少两个致动器（3）被设计成使得当致动器（3）同时操作时，作用点（2）可以被不同地偏转。因此，可以使控制表面（1; 11,14）特别是沿着跨度宽度方向（9）弹性变形，而不会扭结，在这种情况下，可以相对于侧面沿着控制表面实现均匀的过渡流动方向（6）。本发明使得可以减少由控制表面引起的涡流和噪声。

2. 发明授权

US07880366B2 Three-dimensional stack-type piezo element and piezoelectric actuator having such a stack-type piezo element 有权
标题翻译：具有这种堆叠型压电元件的三维堆叠型压电元件和压电致动器
公开(公告)号：US07880366B2
公开(公告)日：2011-02-01
申请号：US12158617
申请日：2006-12-08
申请人： Boris Grohmann , Peter Konstanzer , Stefan Storm
发明人： Boris Grohmann , Peter Konstanzer , Stefan Storm
IPC分类号： H01L41/08
CPC分类号： B64C3/48 , H01L41/0831 , H01L41/0833 , H01L41/094 , H01L41/098 , Y10T29/42
摘要： A three-dimensional stack-type piezo element has at least one surface that is shaped perpendicular to layer planes of the stack, so that, at least in sections, it is not parallel to a stacking direction of the piezo element.
摘要翻译：三维堆叠型压电元件具有至少一个垂直于堆叠层的平面形状的表面，使得至少在部分中它不平行于压电元件的层叠方向。

3. 发明申请

US20090079301A1 Three-Dimensional Stack-Type Piezo Element and Piezoelectric Actuator Having Such a Stack-Type Piezo Element 有权
标题翻译：具有这种堆叠型压电元件的三维堆叠型压电元件和压电致动器
公开(公告)号：US20090079301A1
公开(公告)日：2009-03-26
申请号：US12158617
申请日：2006-12-08
申请人： Boris Grohmann , Peter Konstanzer , Stefan Storm
发明人： Boris Grohmann , Peter Konstanzer , Stefan Storm
IPC分类号： H01L41/083 , H01L41/22
CPC分类号： B64C3/48 , H01L41/0831 , H01L41/0833 , H01L41/094 , H01L41/098 , Y10T29/42
摘要： A three-dimensional stack-type piezo element has at least one surface that is shaped perpendicular to layer planes of the stack, so that, at least in sections, it is not parallel to a stacking direction of the piezo element.
摘要翻译：三维堆叠型压电元件具有至少一个垂直于堆叠层的平面形状的表面，使得至少在部分中它不平行于压电元件的层叠方向。

4. 发明授权

US08151946B2 Rotor brake for a rotary-wing aircraft 有权
标题翻译：旋翼机的转子制动器
公开(公告)号：US08151946B2
公开(公告)日：2012-04-10
申请号：US12100741
申请日：2008-04-10
申请人： Andreas Doleschel , Peter Konstanzer
发明人： Andreas Doleschel , Peter Konstanzer
IPC分类号： F16D55/22
CPC分类号： B64C27/12
摘要： A rotor brake for a rotary-wing aircraft includes a rotor shaft, a braking-force actuator configured to be hydraulically actuated, a braking-force pick-up element connected to the rotor shaft and operationally connected to the braking-force actuator, an electromechanical piston control element, and a first hydraulic line connecting the electromechanical piston control element to the braking-force actuator so that the braking-force actuator can be actuated electrohydraulically by the electromechanical piston control element.
摘要翻译：用于旋转翼飞行器的转子制动器包括转子轴，构造为液压致动的制动力致动器，连接到转子轴并且可操作地连接到制动力致动器的制动力拾取元件，机电活塞控制元件和将机电活塞控制元件连接到制动力致动器的第一液压管线，使得制动力致动器可以由机电活塞控制元件电液动地致动。

5. 发明申请

US20080315725A1 Force Generator 审中-公开
标题翻译：力发电机
公开(公告)号：US20080315725A1
公开(公告)日：2008-12-25
申请号：US12097726
申请日：2006-12-01
申请人： Peter Konstanzer , Stefan Storm
发明人： Peter Konstanzer , Stefan Storm
IPC分类号： H01L41/08
CPC分类号： F16F7/1011 , F16F15/28
摘要： A force generator is configured for attachment to a structure in order to controllably introduce vibrational forces into the structure in order to influence the vibration thereof. The force generator encompasses a flexural arm that is fastenable at least at one end to the structure; and an inertial mass that is coupled to the flexural arm remotely from the fastening end of the flexural arm; the flexural arm being equipped with at least one electromagnetic transducer, and a driving system being provided for the transducer, which system is set up such that by driving the transducer, it warps the flexural arm with the inertial mass and the transducer, and thereby displaces the inertial mass, in such a way that vibrational forces of variable amplitude, phase, and frequency are introducible into the structure.
摘要翻译：力发生器构造成用于附接到结构，以便可控制地将振动力引入结构中，以便影响其振动。力发生器包括至少在一端到达结构的可固定的弯曲臂; 以及从弯曲臂的紧固端远离耦合到弯曲臂的惯性质量块; 所述弯曲臂配备有至少一个电磁换能器，以及为所述换能器提供的驱动系统，所述驱动系统被设置成使得通过驱动所述换能器，所述驱动系统通过所述惯性质量块和所述换能器使所述弯曲臂翘曲，惯性质量，使得可变振幅，相位和频率的振动力被引入到结构中。

6. 发明申请

US20060273690A1 Structure element for an aircraft 失效
标题翻译：飞机的结构要素
公开(公告)号：US20060273690A1
公开(公告)日：2006-12-07
申请号：US11333676
申请日：2006-01-17
申请人： Eckart Frankenberger , Peter Konstanzer
发明人： Eckart Frankenberger , Peter Konstanzer
IPC分类号： H01L41/08
CPC分类号： B64C1/06 , B64C1/18 , B64C1/40
摘要： Nowadays floor structures in the fuselage of aeroplanes, which floor structures comprise transverse floor girders, are usually connected to the frame on the right and left by means of rivets and are in turn supported vertically downward by the frame by way of Samer rods. According to one embodiment of the present invention a structural element for an aircraft is stated, comprising an active element and a passive element. In this way additional stiffening of the fuselage, a reduction in fuselage deformation, or active vibration dampening can be provided without additional weight.
摘要翻译：如今，飞机机身的地板结构，地板结构包括横向地板桁架，通常通过铆钉在右边和左边连接到框架上，并且通过三角杆由框架垂直向下支撑。根据本发明的一个实施例，描述了一种用于飞机的结构元件，包括有源元件和无源元件。以这种方式，可以提供机身附加的加强，机身变形的减少或主动减振，而不需要额外的重量。

7. 发明申请

US20120174699A1 DEVICE FOR ADAPTIVE BALANCING OF ROTARY DEVICES 审中-公开
标题翻译：旋转装置自适应平衡装置
公开(公告)号：US20120174699A1
公开(公告)日：2012-07-12
申请号：US13343218
申请日：2012-01-04
申请人： Falk Hoffmann , Peter Konstanzer , Peter Znika
发明人： Falk Hoffmann , Peter Konstanzer , Peter Znika
IPC分类号： F16F15/36 , B64C11/00
CPC分类号： B64C27/001 , B64C11/008 , B64C2027/003 , F16F15/366 , Y10T74/2114
摘要： A rotary device associated with drive means. The rotary device comprises a shaft and/or a hub and balancing means for balancing its rotational motion. The balancing means has a hollow chamber surrounding the hub and a solid/fluidic material with thixotropic properties, which fills partly the hollow chamber.
摘要翻译：与驱动装置相关联的旋转装置。旋转装置包括轴和/或轮毂以及用于平衡其旋转运动的平衡装置。平衡装置具有围绕毂的中空室和具有触变特性的固体/流体材料，其部分地填充中空室。

8. 发明授权

US07598657B2 Structure element for an aircraft 失效
标题翻译：飞机的结构要素
公开(公告)号：US07598657B2
公开(公告)日：2009-10-06
申请号：US11333676
申请日：2006-01-17
申请人： Eckart Frankenberger , Peter Konstanzer
发明人： Eckart Frankenberger , Peter Konstanzer
IPC分类号： H01L41/08
CPC分类号： B64C1/06 , B64C1/18 , B64C1/40
摘要： Nowadays floor structures in the fuselage of airplanes, which floor structures comprise transverse floor girders, are usually connected to the frame on the right and left by means of rivets and are in turn supported vertically downward by the frame by way of Samer rods. According to one embodiment of the present invention a structural element for an aircraft is stated, comprising an active element and a passive element. In this way additional stiffening of the fuselage, a reduction in fuselage deformation, or active vibration dampening can be provided without additional weight.
摘要翻译：如今，飞机机身的地板结构，地板结构包括横向地板桁架，通常通过铆钉在右边和左边连接到框架上，并且通过三角杆由框架垂直向下支撑。根据本发明的一个实施例，描述了一种用于飞机的结构元件，包括有源元件和无源元件。以这种方式，可以提供机身附加的加强，机身变形的减少或主动减振，而不需要额外的重量。

9. 发明申请

US20080277213A1 ROTOR BRAKE FOR A ROTARY-WING AIRCRAFT 有权
标题翻译：旋转制动器用于旋转式飞机
公开(公告)号：US20080277213A1
公开(公告)日：2008-11-13
申请号：US12100741
申请日：2008-04-10
申请人： Andreas Doleschel , Peter Konstanzer
发明人： Andreas Doleschel , Peter Konstanzer
IPC分类号： F16D55/22
CPC分类号： B64C27/12
摘要： A rotor brake for a rotary-wing aircraft includes a rotor shaft, a braking-force actuator configured to be hydraulically actuated, a braking-force pick-up element connected to the rotor shaft and operationally connected to the braking-force actuator, an electromechanical piston control element, and a first hydraulic line connecting the electromechanical piston control element to the braking-force actuator so that the braking-force actuator can be actuated electrohydraulically by the electromechanical piston control element.
摘要翻译：用于旋转翼飞行器的转子制动器包括转子轴，构造为液压致动的制动力致动器，连接到转子轴并且可操作地连接到制动力致动器的制动力拾取元件，机电活塞控制元件和将机电活塞控制元件连接到制动力致动器的第一液压管线，使得制动力致动器可以由机电活塞控制元件电液动地致动。

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