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1. 发明申请

US20170096214A1 VORTEX GENERATOR ARRANGEMENT, FLOW CONTROL SYSTEM AND METHOD FOR CONTROLLING A FLOW ON A RUDDER SURFACE 审中-公开
公开(公告)号：US20170096214A1
公开(公告)日：2017-04-06
申请号：US15274197
申请日：2016-09-23
申请人： Airbus Operations GmbH
发明人： Bruno Stefes , Wolfgang Eilken , Erich Paul
IPC分类号： B64C23/06 , B64C13/16 , B64C5/06
CPC分类号： B64C23/06 , B64C5/06 , B64C9/02 , B64C13/16 , Y02T50/162
摘要： A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed.

2. 发明申请

US20160229526A1 VORTEX GENERATOR ARRANGEMENT 审中-公开
标题翻译： VORTEX发电机装置
公开(公告)号：US20160229526A1
公开(公告)日：2016-08-11
申请号：US15015804
申请日：2016-02-04
申请人： Airbus Operations GmbH
发明人： Matthias Hegenbart , Wolfgang Eilken , Erich Paul , Bruno Stefes , Lena Duken
IPC分类号： B64C23/06 , B64C21/10
CPC分类号： B64C23/06 , B64C9/02 , B64C13/16 , B64C21/10 , Y02T50/162 , Y02T50/44
摘要： A vortex generator arrangement for an aircraft including a surface section, a flap element pivotable between a first position and a second position, a biasing arrangement biasing the flap element towards the second position, retaining devices retaining the flap element in the first or second position, and a release device releasing the flap element from the first retaining device. The biasing arrangement, the first retaining device and the second retaining device are configured such that the second retaining device automatically retains the flap element in the second position after the flap element has been pivoted by the biasing arrangement from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device automatically releases the flap element, which pivots against the force of the biasing arrangement into the first position and is automatically retained therein by the first retaining device.
摘要翻译：一种用于飞行器的涡流发生器装置，其包括表面部分，在第一位置和第二位置之间可枢转的挡板元件，偏置装置，其将所述翼片元件偏压朝向所述第二位置，将所述翼片元件保持在所述第一或第二位置，以及从所述第一保持装置释放所述襟翼元件的释放装置。偏置装置，第一保持装置和第二保持装置构造成使得第二保持装置在折板元件已经被偏置装置从第一位置枢转到第二位置之后自动将挡板元件保持在第二位置。一旦扭矩超过预定值，第二保持装置就会自动释放挡板元件，该挡片元件抵抗偏置装置的力转动到第一位置，并被第一保持装置自动保持在其中。

3. 发明授权

US10543908B2 Vortex generator arrangement for an aircraft 有权
公开(公告)号：US10543908B2
公开(公告)日：2020-01-28
申请号：US15365133
申请日：2016-11-30
申请人： Airbus Operations GmbH
发明人： Bruno Stefes , Wolfgang Eilken , Erich Paul
IPC分类号： B64C23/06 , B64C3/00 , B64C5/02 , B64C9/00 , B64C9/14
摘要： A vortex generator arrangement for an aircraft, a flow control system and an aircraft comprising such vortex generator arrangement. The arrangement includes a surface portion facing a first region of space to constitute a flow surface, a vortex generating element, an element support structure connected to the element, a mounting structure. The element support structure and the element together are rotatable between first and second positions and a biasing device, retainer and release are provided. The rotational axis extends transversely with respect to the surface portion. The projection of the element onto a projection plane is smaller in the first rotational position than in the second rotational position, the projection plane extending perpendicularly to a tangent plane of the surface portion at a reference point of the surface portion and to a predetermined direction parallel to the extension of the tangent plane.

4. 发明授权

US10279894B2 Vortex generator arrangement, flow control system and method for controlling a flow on a rudder surface 有权
公开(公告)号：US10279894B2
公开(公告)日：2019-05-07
申请号：US15274197
申请日：2016-09-23
申请人： Airbus Operations GmbH
发明人： Bruno Stefes , Wolfgang Eilken , Erich Paul
IPC分类号： B64C23/06 , B64C9/02 , B64C13/16 , B64C5/06
摘要： A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed.

5. 发明授权

US10202187B2 Vortex generator arrangement 有权
公开(公告)号：US10202187B2
公开(公告)日：2019-02-12
申请号：US15015804
申请日：2016-02-04
申请人： Airbus Operations GmbH
发明人： Matthias Hegenbart , Wolfgang Eilken , Erich Paul , Bruno Stefes , Lena Duken
IPC分类号： B64C23/06 , B64C9/02 , B64C13/16 , B64C21/10
摘要： A vortex generator arrangement for an aircraft including a surface section, a flap element pivotable between a first position and a second position, a biasing arrangement biasing the flap element towards the second position, retaining devices retaining the flap element in the first or second position, and a release device releasing the flap element from the first retaining device. The biasing arrangement, the first retaining device and the second retaining device are configured such that the second retaining device automatically retains the flap element in the second position after the flap element has been pivoted by the biasing arrangement from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device automatically releases the flap element, which pivots against the force of the biasing arrangement into the first position and is automatically retained therein by the first retaining device.

6. 发明申请

US20170152025A1 VORTEX GENERATOR ARRANGEMENT FOR AN AIRCRAFT 审中-公开
公开(公告)号：US20170152025A1
公开(公告)日：2017-06-01
申请号：US15365133
申请日：2016-11-30
申请人： Airbus Operations GmbH
发明人： Bruno Stefes , Wolfgang Eilken , Erich Paul
IPC分类号： B64C23/06 , B64C9/00 , B64C9/14 , B64C3/00 , B64C5/02
摘要： A vortex generator arrangement for an aircraft, a flow control system and an aircraft comprising such vortex generator arrangement. The arrangement includes a surface portion facing a first region of space to constitute a flow surface, a vortex generating element, an element support structure connected to the element, a mounting structure. The element support structure and the element together are rotatable between first and second positions and a biasing device, retainer and release are provided. The rotational axis extends transversely with respect to the surface portion. The projection of the element onto a projection plane is smaller in the first rotational position than in the second rotational position, the projection plane extending perpendicularly to a tangent plane of the surface portion at a reference point of the surface portion and to a predetermined direction parallel to the extension of the tangent plane.

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