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公开(公告)号：US20220258858A1
公开(公告)日：2022-08-18
申请号：US17564297
申请日：2021-12-29
发明人： Rupert PFALLER , Tobias RIES
摘要： The present disclosure relates to a rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a shrouded duct that is arranged in the aft region and that forms an inner air duct, wherein the shrouded duct is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft; and a propeller that is at least configured to propel the rotary wing aircraft in the forward flight condition; wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller is rotatably mounted to the shrouded duct such that the circular propeller disc is at least essentially arranged inside of the inner air duct.
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2.发明申请FLEXBEAM UNIT FOR A HINGELESS OR A HINGE AND BEARINGLESS MULTI-BLADE ROTOR OF A ROTARY WING AIRCRAFT 有权用于无缝或铰链和无轴承的旋转臂旋转机的旋转机组公开(公告)号：US20150197333A1
公开(公告)日：2015-07-16
申请号：US14594601
申请日：2015-01-12
发明人： Rupert PFALLER
IPC分类号： B64C27/33
CPC分类号： B64C27/33
摘要： A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, said flexbeam unit comprising a plurality of flexbeam elements that define a predetermined number of torsion elements and a ring-shaped connection zone for attachment to a rotor hub associated with a rotor shaft of said multi-blade rotor, each flexbeam element passing said ring-shaped connection zone in a tangential manner and uninterruptedly connecting a first torsion element to a second torsion element of said predetermined number of torsion elements, wherein each flexbeam element overlaps at least one in the circumferential direction of said ring-shaped connection zone immediately following flexbeam element and is overlapped by at least one in the circumferential direction of said ring-shaped connection zone immediately preceding flexbeam element.
摘要翻译： 一种用于旋转翼飞行器的多叶片转子的挠性束单元，所述柔性梁单元包括限定预定数量的扭转元件的多个挠性梁元件和用于连接到与转子轴相关联的转子毂的环形连接区域 所述多叶片转子中的每个柔性束元件以切向方式通过所述环形连接区域，并且将第一扭转元件不间断地连接到所述预定数量的扭转元件的第二扭转元件，其中每个柔性梁元件与至少一个 所述环形连接区域的圆周方向紧接在柔性束元件之后，并且在紧邻柔性梁元件之前的所述环形连接区域的圆周方向上至少一个重叠。
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公开(公告)号：US20140234104A1
公开(公告)日：2014-08-21
申请号：US14180419
申请日：2014-02-14
发明人： Rupert PFALLER , Bernhard ENENKL
IPC分类号： B64C27/615
CPC分类号： B64C27/615 , B64C27/72 , B64C2027/7283 , Y02T50/34
摘要： A rotor blade (1) with an exterior shell (20) extending in a span and chord wise direction and at least one control flap (4) extending in essentially span wise direction to said exterior shell (20). Load transmission means inside said blade chamber (7) comprise piling type housings (13) respectively with one actuator (8, 9), one flap drive (10, 11) and a longitudinal girder (15). Said at least one piling type housing (13) comprises at least one upper strap (14) and at least one lower strap (14) oriented essentially in said chord direction in between said longitudinal girder (15) on the one side and the support for said at least one actuator (8, 9) on the other side, each of said upper and lower straps (14) being symmetric aligned in chord direction relative to at least two pivot bearings (35, 36). Said upper and lower straps (14) are stiff in chord direction and flexible in span wise direction.
摘要翻译： 具有沿跨度和弦向延伸的外壳（20）的转子叶片（1）和至少一个沿基本跨度方向延伸到所述外壳（20）的控制翼片（4）。 所述叶片室（7）内的载荷传递装置包括分别具有一个致动器（8,9），一个翼片驱动器（10,11）和纵向梁（15）的堆叠型壳体（13）。 所述至少一个打桩式壳体（13）包括至少一个上带（14）和至少一个下带（14），所述至少一个下带（14）基本上在所述弦方向上位于所述一侧的所述纵梁（15）和所述支撑件之间， 所述至少一个致动器（8,9）位于另一侧，所述上带和下带（14）中的每一个相对于至少两个枢转轴承（35,36）在弦方向上对称排列。 所述上带和下带（14）在弦方向上是刚性的，并且跨越方向是柔性的。
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公开(公告)号：US20220154762A1
公开(公告)日：2022-05-19
申请号：US17445321
申请日：2021-08-18
发明人： Rupert PFALLER , Moritz BUESING
摘要： A drive shaft made from composite materials that comprises a hollow body and a flange that is integrally formed with the hollow body. The hollow body is adapted to rotating around an associated rotation axis and is made of a first composite material. The flange is made of a second composite material and arranged at an axial end of the hollow body. The flange comprises at least two separate plates that branch out from the hollow body at the axial end. The flange further comprises a mounting section that is configured to be mounted to an external component and comprises a plurality of holes that is adapted to accommodate coupling means.
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公开(公告)号：US20190112039A1
公开(公告)日：2019-04-18
申请号：US16143531
申请日：2018-09-27
摘要： A multirotor aircraft with an airframe and at least one wing that is mounted to the airframe, the at least one wing being provided with at least four thrust producing units that are arranged in spanwise direction of the at least one wing, wherein each one of the at least four thrust producing units comprises at least one rotor assembly that is accommodated in an associated shrouding, the associated shrouding being integrated into the at least one wing, wherein the associated shrouding defines an air duct that is axially delimited by an air inlet region and an air outlet region, wherein the air inlet region exhibits in circumferential direction of the air duct at least two different aerodynamic profiles.
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6.发明申请FLEXBEAM UNIT FOR A BEARINGLESS OR A HINGE AND BEARINGLESS MULTI-BLADE ROTOR OF A ROTARY WING AIRCRAFT 审中-公开用于无轴承的弹性单元或旋转式飞行器的铰链和无轴承多叶轮转子公开(公告)号：US20150197334A1
公开(公告)日：2015-07-16
申请号：US14595547
申请日：2015-01-13
发明人： Rupert PFALLER
摘要： A flexbeam unit comprising a plurality of flexbeam elements, each defining a load passing member that is attachable to a rotor hub associated with a rotor shaft of said multi-blade rotor, said plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of said multi-blade rotor, wherein at least one of the predetermined number of torsion elements comprises at least one first flexbeam element defining a first longitudinal direction and at least one second flexbeam element defining a second longitudinal direction, wherein said at least one first and second flexbeam elements are interconnected by a beam connector in a direction transverse to said first and/or second longitudinal directions.
摘要翻译： 柔性梁单元，其包括多个柔性梁元件，每个柔性梁单元限定可连接到与所述多叶片转子的转子轴相关联的转子毂的载荷通过构件，所述多个挠性梁元件限定可连接的预定数量的扭转元件 与所述多叶片转子的相关联的转子叶片，其中所述预定数量的扭转元件中的至少一个包括限定第一纵向方向的至少一个第一柔性梁元件和限定第二纵向方向的至少一个第二弹性梁元件，其中， 至少一个第一和第二柔性元件通过横梁与横向于所述第一和/或第二纵向方向的梁连接器相互连接。
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公开(公告)号：US20230024261A1
公开(公告)日：2023-01-26
申请号：US17574734
申请日：2022-01-13
发明人： Rupert PFALLER , Tobias RIES
摘要： A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a propeller that is at least configured to propel the rotary wing aircraft in forward flight condition, wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and a shrouded duct that is arranged in the aft region and that forms an inner air duct which accommodates at least partly the propeller, wherein the shrouded duct comprises a yaw and pitch stability enhancement unit for improving yaw and pitch stability of the rotary wing aircraft in the forward flight condition.
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公开(公告)号：US20220185467A1
公开(公告)日：2022-06-16
申请号：US17445323
申请日：2021-08-18
发明人： Rupert PFALLER , Tobias RIES
摘要： A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, and a stabilizer arrangement that is arranged at the rear section in the aft region, wherein the rear section extends between the front section and the stabilizer arrangement and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.
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公开(公告)号：US20220185466A1
公开(公告)日：2022-06-16
申请号：US17377538
申请日：2021-07-16
发明人： Rupert PFALLER , Tobias RIES
摘要： A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, wherein the rear section extends between the front section and the aft region, the rotary wing aircraft comprising: a propeller that is rotatably mounted at the rear section in the aft region, a main rotor that is rotatably mounted at the front section, and a source of asymmetry that is connected to the front section such that the front section comprises at least in sections an asymmetrical cross-sectional profile in direction of the associated roll axis, wherein the source of asymmetry is configured to generate sideward thrust for main rotor anti-torque from main rotor downwash.
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公开(公告)号：US20220185465A1
公开(公告)日：2022-06-16
申请号：US17376576
申请日：2021-07-15
发明人： Rupert PFALLER , Tobias RIES
摘要： A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, the rotary wing aircraft comprising: a main rotor that is rotatably mounted at the front section, a shrouded duct that is arranged in the aft region, and a propeller that is rotatably mounted to the shrouded duct, wherein the rear section extends between the front section and the shrouded duct and comprises an asymmetrical cross-sectional profile in direction of the associated roll axis.
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