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1. 发明授权

US10259163B2 Method and system for adapting a 3D printing model 有权
公开(公告)号：US10259163B2
公开(公告)日：2019-04-16
申请号：US14947600
申请日：2015-11-20
申请人： Airbus Operations GmbH
发明人： Wolfgang Eilken , Memis Tiryaki , Henning Felgenhauer
IPC分类号： B29C67/00 , B29C64/386 , G06T19/20 , B33Y10/00 , B33Y50/00
摘要： A method for adapting a 3D printing model includes calculating a layer representation model on the basis of a 3D object model of an object; determining a plurality of overhang regions in the layer representation model where the boundary edges of first layers extend over the boundary edges of second layers, the first layers being directly adjacent and subsequent to the second layers when going into the build-up direction of the layer representation model; determining a local overhang angle in each of the plurality of overhang regions; adapting the layer representation model by re-defining the boundary edges of layers in the overhang regions so that the local overhang angle remains below a predetermined overhang threshold angle; and outputting the adapted layer representation model as 3D printing model to the 3D printing apparatus.

2. 发明授权

US09669928B2 Multipart fastening device for fastening a device to a reinforcing element and to the outer skin of a vehicle 有权
公开(公告)号：US09669928B2
公开(公告)日：2017-06-06
申请号：US14935507
申请日：2015-11-09
申请人： Airbus Operations GmbH
发明人： Wolfgang Eilken , Memis Tiryaki , Michael Sauer
IPC分类号： B60P7/08 , B64D9/00
CPC分类号： B64D9/00 , B60P7/0807 , F16B5/04 , Y02T50/46
摘要： This relates to a multi-part attachment device for attaching a device to a stiffening element and to an outer skin of a vehicle. The multi-part attachment device comprises a base body having an angular profile for attaching the attachment device to the stiffening element and to the outer skin of the vehicle. Furthermore, the multi-part attachment device comprises an upper part with a lug, wherein the upper part is attached to the base body. This also relates to a method for attaching a device to a stiffening element and to an outer skin of a vehicle as well as to an aircraft with a multi-part attachment device.

3. 发明申请

US20200094969A1 Rail Systems for Fixing Fittings in a Cabin of a Vehicle 审中-公开
公开(公告)号：US20200094969A1
公开(公告)日：2020-03-26
申请号：US16574607
申请日：2019-09-18
申请人： Airbus Operations GmbH
发明人： Sven Werner , Andre Zybala , Wolfgang Eilken , Memis Tiryaki
IPC分类号： B64D11/06
摘要： A rail system for fixing fittings in a cabin of a vehicle includes a first elongate rail body with a fixing side for fixing to a vehicle structure, an opposite support side with a support surface for receiving fittings, and a rail cross-section extending between the fixing side and the support side, and several fixing inserts which can be fixed along the support surface. The rail cross-section has two mutually opposing legs which are spaced apart from each other and run perpendicularly to the support surface, and the fixing inserts are configured so as not to protrude beyond the support surface.

4. 发明授权

US10046846B2 Method for manufacturing a shell component for an aircraft or spacecraft 有权
公开(公告)号：US10046846B2
公开(公告)日：2018-08-14
申请号：US14617389
申请日：2015-02-09
申请人： Airbus Operations GmbH
发明人： Stefan Brunner , Wolfgang Schulze , Memis Tiryaki , Wolfgang Eilken
IPC分类号： B64G1/22 , B64C1/12 , B64C1/06 , B64C3/26 , B64F5/10
CPC分类号： B64C1/12 , B23P2700/01 , B64C1/068 , B64C3/26 , B64F5/10 , B64G1/22 , Y10T29/49622 , Y10T29/5397
摘要： A method of manufacturing a shell component for an aircraft or spacecraft includes positioning a skin panel, which includes a skin of the aircraft or spacecraft and first and second stringers stiffening the skin, opposite a frame having first and second mouseholes for receiving the first and second stringers, elastically bending the skin panel, inserting the first stringer into the first mousehole, and releasing the elastic bend to insert the second stringer into the second mousehole.

5. 发明申请

US20160229520A1 VERTICAL STABILIZER FOR AN AIRCRAFT 审中-公开
标题翻译：用于航空器的垂直稳定器
公开(公告)号：US20160229520A1
公开(公告)日：2016-08-11
申请号：US15015783
申请日：2016-02-04
申请人： Airbus Operations GmbH
发明人： Memis Tiryaki , Matthias Hegenbart , Wolfgang Eilken , Michael Sauer
IPC分类号： B64C9/04 , B64C23/06
CPC分类号： B64C9/04 , B64C9/02 , B64C13/16 , B64C23/06 , Y02T50/162
摘要： A vertical stabilizer for an aircraft, including a fin, pivotable rudder, rudder adjustment arrangement, and vortex generator arrangement having on each side of the fin a turbulence generation element, each turbulence generation element disposed in a surface section of the fin and mounted moveably between a first, retracted position, where it is retracted into an interior space of the fin, and a second, extended position, where it projects at least partially outwardly from the fin transversely with respect to the surface section, and a turbulence generation element adjustment arrangement which is coupled to the rudder. The turbulence generation element adjustment arrangement engages the turbulence generation elements to move them. In a range of angular positions of the rudder, the turbulence generation element adjustment arrangement is inoperative for causing a movement of the turbulence generation elements out of the first position.
摘要翻译：一种用于飞行器的垂直稳定器，包括翅片，可枢转方向舵，舵调节装置和涡流发生器装置，其在翅片的每一侧具有湍流发生元件，每个湍流发生元件设置在翅片的表面部分中并且可移动地安装在第一缩回位置，其中缩回到翅片的内部空间中，以及第二延伸位置，其中它们相对于表面部分横向地从翅片至少部分地向外突出，并且湍流产生元件调节装置它与方向舵相连。湍流发生元件调节装置与湍流发生元件接合以使它们移动。在舵的角度位置的范围内，湍流发生元件调节装置不起作用，以使湍流发生元件移动到第一位置之外。

6. 发明申请

US20200086967A1 Floor System For A Vehicle 审中-公开
公开(公告)号：US20200086967A1
公开(公告)日：2020-03-19
申请号：US16571398
申请日：2019-09-16
申请人： Airbus Operations GmbH
发明人： Memis Tiryaki , Sven Werner , Torsten Noebel , Andre Zybala , Wolfgang Eilken
IPC分类号： B64C1/18 , B64C1/20
摘要： A floor system for creating a floor in an interior of a vehicle has base part and a floor panel. The base part having a trough-shaped depression and the floor panel are attached to a floor support structure and together provide a customary installation height and also cavities for accommodating installation objects.

7. 发明授权

US10486789B2 Fuselage structure and method for manufacturing a fuselage structure 有权
公开(公告)号：US10486789B2
公开(公告)日：2019-11-26
申请号：US15203948
申请日：2016-07-07
申请人： Airbus Operations GmbH
发明人： Wolfgang Eilken , Memis Tiryaki , Anton Arosenko
IPC分类号： B64C1/10 , B64C1/06
CPC分类号： B64C1/10 , B64C1/061 , B64C1/064 , B64C1/065
摘要： A fuselage structure includes a pressure bulkhead and a frame being arranged behind the pressure bulkhead. The fuselage structure includes a first beam element with a first cantilever and a second cantilever, while the first beam element extends in a vertical direction of the fuselage structure. The first cantilever and the second cantilever protrude from the first beam element in a first direction toward the frame. The first direction of both cantilevers is inclined at a first angle with respect to a longitudinal direction of the fuselage structure. An aircraft with a fuselage structure and a method for manufacturing a fuselage structure are also described.

8. 发明授权

US10464659B2 Vertical stabilizer for an aircraft 有权
公开(公告)号：US10464659B2
公开(公告)日：2019-11-05
申请号：US15015783
申请日：2016-02-04
申请人： Airbus Operations GmbH
发明人： Memis Tiryaki , Matthias Hegenbart , Wolfgang Eilken , Michael Sauer
IPC分类号： B64C9/04 , B64C9/02 , B64C13/16 , B64C23/06
摘要： A vertical stabilizer for an aircraft, including a fin, pivotable rudder, rudder adjustment arrangement, and vortex generator arrangement having on each side of the fin a turbulence generation element, each turbulence generation element disposed in a surface section of the fin and mounted moveably between a first, retracted position, where it is retracted into an interior space of the fin, and a second, extended position, where it projects at least partially outwardly from the fin transversely with respect to the surface section, and a turbulence generation element adjustment arrangement which is coupled to the rudder. The turbulence generation element adjustment arrangement engages the turbulence generation elements to move them. In a range of angular positions of the rudder, the turbulence generation element adjustment arrangement is inoperative for causing a movement of the turbulence generation elements out of the first position.

9. 发明申请

US20190118926A1 FUSELAGE STRUCTURE FOR AN AIRCRAFT, AND AIRCRAFT 审中-公开
公开(公告)号：US20190118926A1
公开(公告)日：2019-04-25
申请号：US16156582
申请日：2018-10-10
申请人： Airbus Operations GmbH
发明人： Memis Tiryaki , Hermann Benthien , Wolfgang Eilken
IPC分类号： B64C1/10 , B64C1/06
摘要： A fuselage structure for an aircraft, comprising a fuselage vessel and a pressure bulkhead arranged in an end region of the fuselage vessel and having a central region extending in a planar manner and a connection region adjoining the central region in a radial direction and surrounding the central region and being secured to the fuselage vessel. The pressure bulkhead divides the fuselage vessel with respect to the longitudinal direction into a first region for subjecting to an internal pressure and a second region for subjecting to an external pressure which is lower than the internal pressure. The central region of the pressure bulkhead has an arching in the direction of the first region of the fuselage vessel.

10. 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。

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