公开(公告)号：EP3090939B1

公开(公告)日：2018-12-12

申请号：EP16168593.8

申请日：2016-05-06

Applicant: The Boeing Company

Inventor： GOLSHANY, Sina Sam ,  ERICKSON, Todd W ,  TRETOW, Paul R ,  HUNTLY, David M

IPC: B64C1/26 ,  B64C5/02

CPC classification number: B64C5/02 ,  B64C1/26 ,  F16F15/002 ,  F16F15/022 ,  F16F2228/066 ,  F16F2230/18

Abstract: Systems and methods provide for the mitigation of vibrational forces acting on a horizontal stabilizer (102) of an aircraft. According to one aspect, a damper (106) is coupled to a front portion of a horizontal stabilizer (102) to dampen vibrations in a first degree of freedom, with another damper (106) coupled to a mounting point (118) of the horizontal stabilizer (102) to dampen vibrations in a second degree of freedom. The dampers (106) may be passive, operating independently to mitigate vibrational forces, or active, applying a mitigating force to the horizontal stabilizer (102) based on real-time or estimated vibration states.

公开(公告)号：EP2825450B1

公开(公告)日：2018-07-25

申请号：EP13709224.3

申请日：2013-03-15

Applicant: Airbus Defence and Space GmbH

Inventor： BENTHIEN, Hermann ,  HAACK, Cord ,  POPPE, Andreas ,  BURRICHTER, Michael ,  ABRAHAM, Torsten ,  BRINCKMANN, Michael ,  DIERKER, Christoph ,  WERTH, Frank ,  BINDEWALD, Wulf

IPC: B64C1/26

CPC classification number: B64C1/068 ,  B64C1/26

Abstract: An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.

公开(公告)号：EP3025954B1

公开(公告)日：2018-03-07

申请号：EP14382475.3

申请日：2014-11-27

Applicant: Airbus Operations S.L. ,  AIRBUS OPERATIONS (SAS)

Inventor： Martino González, Esteban ,  Folch Cortés, Diego ,  Goya Abaurrea, Pablo ,  Pascual Fuertes, Ángel ,  Liñares Mendoza, Sandra ,  Gillemaut, Julien ,  Bouchet, Eric ,  Colmagro, Jérôme ,  Blanc, Jonathan

IPC: B64C1/06 ,  B64C1/16 ,  B64C1/26

CPC classification number: B64C1/061 ,  B64C1/06 ,  B64C1/12 ,  B64C1/16 ,  B64C1/26 ,  B64C3/32

Abstract: The invention refers to an aircraft fuselage frame (2) that comprises a central element (3) adapted to be located within the perimeter of the fuselage, and two lateral extensions (4) projecting outside the perimeter of the fuselage from both sides of the central element (3) that are a portion of a longitudinal structure of a lifting surface (1). Additionally the central element (3) and the two lateral extensions (4) being configured as an integrated piece.

公开(公告)号：EP2371705B1

公开(公告)日：2018-03-07

申请号：EP09812436.5

申请日：2009-12-17

Applicant: Airbus Operations, S.L.

Inventor： LLAMAS SANDÍN, Raúl Carlos ,  LUQUE BUZO, Miguel

IPC: B64C1/26 ,  B64C5/02

CPC classification number: B64C5/02 ,  B64C1/26

Abstract: Aircraft horizontal stabilizer surface (8) in which the sweep angle (40) of this surface (8), where this angle (40) is the one formed by the projection of the reference line of points located at 25% of the local chord (19) of the horizontal stabilizer surface (8) on a plane perpendicular to the aircraft plane of symmetry (21), and which also contains this plane to the flight direction of the aircraft with respect to the aircraft plane of symmetry (21), is less than 90 degrees, with this angle (40) being measured in the flight direction of the aircraft. In addition, the structural connection of this horizontal stabilizer surface (8) to the aircraft fuselage (1) is located at a closing frame (13) of this fuselage (1).

公开(公告)号：EP3287360A1

公开(公告)日：2018-02-28

申请号：EP17185973.9

申请日：2017-08-11

Applicant: The Boeing Company

Inventor： KISMARTON, Max U ,  MUNK, Clayton L

IPC: B64C3/18 ,  B64C1/26 ,  B64C3/26

CPC classification number: B64C3/182 ,  B29C70/00 ,  B29D99/0014 ,  B29L2031/3085 ,  B64C1/26 ,  B64C3/26 ,  B64F5/10

Abstract: Systems and methods are provided for integrating structural components of a wing box. One embodiment is a system that includes outboard planked stringers within an outboard section of a wing box and are co-cured with composite skin at the outboard section. Each outboard planked stringer of the outboard section includes planar layers of Carbon Fiber Reinforced Polymer (CFRP) that are parallel with the composite skin at the outboard section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distance along the composite skin at the outboard section. The system also includes center planked stringers within the center section and are co-cured with composite skin at the center section. Each center planked stringer of the center section includes planar layers of CFRP that are parallel with the composite skin at the center section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distance along the skin at the center section.

Abstract translation: 提供了用于集成翼盒的结构部件的系统和方法。 一个实施例是一种系统，其包括机翼箱的外侧部分内的外侧带翼纵梁并且在外侧部分与复合蒙皮共同固化。 外侧部分的每个外侧上颚纵梁包括与外侧部分处的复合蒙皮平行的碳纤维增强聚合物（CFRP）的平面层，纤维取向对准以承受施加到翼盒的张力和压力，并且每个延伸出 沿着外侧部分处的复合材料蒙皮具有不同的距离。 该系统还包括在中心部分的中心平面桁条，并且在中心部分与复合材料蒙皮共同固化。 中心部分的每个中心带有纵梁的中央部分包括与中心部分的复合表层平行的CFRP平面层，具有对齐的纤维取向以承受施加到翼盒上的张力和压缩，并且每个沿着表层延伸不同的距离 中心部分。

公开(公告)号：EP3260374A1

公开(公告)日：2017-12-27

申请号：EP17165840.4

申请日：2017-04-10

Applicant: The Boeing Company

Inventor： BEST, Steven A. ,  WISEMAN, Jesse Randal ,  VANVALKENBURGH, Hugh Christopher ,  LOWELL, John R.

IPC: B64D37/32

CPC classification number: B64C1/26 ,  B64C3/34 ,  B64D37/08 ,  B64D37/32 ,  B64F5/10

Abstract: A dry bay sealing assembly (100) is provided that includes a first end plate (150) and a second end plate (160) that are configured to be disposed on respective opposite first (128) and second sides (129) of a structural member (120) proximate to a joint (140) defined between the structural member and a fitting (110). The first end plate and the second end plate are configured to define an interior volume (180) therebetween containing at least a portion of a fastener (130) joining the structural member and the fitting. The first end plate and the second end plate are configured to cooperate with the structural member to seal the interior volume from an exterior volume (190).

Abstract translation: 提供一种干式隔间密封组件（100），该干式隔间密封组件（100）包括第一端板（150）和第二端板（160），所述第一端板和第二端板构造成设置在结构构件的相应相对的第一侧（128）和第二侧 （120）靠近在所述结构构件和配件（110）之间限定的接头（140）。 第一端板和第二端板构造成在其间限定包含连接结构构件和配件的紧固件（130）的至少一部分的内部容积（180）。 第一端板和第二端板构造成与结构构件协作以从外部容积（190）密封内部容积。

公开(公告)号：EP3219604A1

公开(公告)日：2017-09-20

申请号：EP16382110.1

申请日：2016-03-14

Applicant: Airbus Operations, S.L.

Inventor： ABELLÁN ALZALLLU, Felipe ,  RAMOS GUERRERO, Alberto ,  ÁVILA GUTIERREZ, Adolfo ,  MONJE MARTIN, Juan, Carlos

IPC: B64C1/26 ,  B64C5/02

CPC classification number: B64C1/068 ,  B64C1/061 ,  B64C1/065 ,  B64C1/26 ,  B64C5/02

Abstract: The present invention refers to a harness routing electrically connecting a rear fuselage section of an aircraft and a trimmable Horizontal Tail Plane (HTP) installed at this rear section. The aircraft rear section comprises a first clipping point wherein the harness is attached to a fuselage frame located in front of the torsion box front spar, and a second clipping point wherein the harness is attached to a front spar of the HTP torsion box. The second clipping point is located downstream the first clipping point from the fuselage towards the torsion box interior, and the harness passes through the front spar towards the interior of the torsion box downstream the second clipping point. The harness installation and routing is optimized, in order to reduce harness length and weight, but at the same time assuring that any damage to the harness cables are prevented during the entire aircraft operative life.

Abstract translation: 本发明涉及一种将飞机的后机身部分和安装在该后部的可修剪水平尾翼（HTP）电连接的线束布线。 飞行器后部包括第一剪辑点和第二剪辑点，其中，线束连接到位于扭力箱前翼梁前方的机身框架，其中，线束连接到HTP扭转箱的前翼梁。 第二剪切点位于从机身朝向扭转箱内部的第一剪切点的下游，并且该线束在第二剪切点下游经过前翼梁朝向扭转箱的内部。 线束的安装和布线经过优化，以减少线束长度和重量，但同时确保在整个飞机的使用寿命期间防止线束电缆损坏。

公开(公告)号：EP3191364A1

公开(公告)日：2017-07-19

申请号：EP15759481.3

申请日：2015-09-09

Applicant: Airbus Operations GmbH

Inventor： KLETTKE, Marcus

IPC: B64C3/38 ,  B64C3/44 ,  B64C13/40 ,  B64C1/26 ,  B64C3/16 ,  B64C3/56

CPC classification number: B64C3/38 ,  B64C1/26 ,  B64D41/00 ,  F15B11/10 ,  F15B2211/40

Abstract: The invention relates to an aircraft having a fuselage and wings connected thereto, wherein a support strut extends in each case between the fuselage and the wings, said support strut being connected both to the fuselage and the wing. The support strut comprises a hydraulic working cylinder that can be subjected with hydraulic fluid for pivoting the wing in a controlled manner.

Abstract translation: 本发明涉及一种具有机身和与其连接的机翼的飞机，其中支撑杆分别在机身和机翼之间延伸，所述支撑杆连接到机身和机翼。 支撑支柱包括液压工作缸，液压工作缸可受到用于以受控方式枢转机翼的液压流体。

公开(公告)号：EP2945860A4

公开(公告)日：2016-12-14

申请号：EP14779194

申请日：2014-01-15

Applicant: OTTO WILLIAM M

Inventor： OTTO WILLIAM M

IPC: B64C3/14

CPC classification number: B64C3/58 ,  B64C1/061 ,  B64C1/065 ,  B64C1/16 ,  B64C1/26 ,  B64C3/185 ,  B64C3/26 ,  B64C3/28 ,  B64C9/02 ,  B64C9/20 ,  B64C13/30 ,  B64C25/14 ,  B64C2025/125 ,  B64D33/04 ,  B64D33/10 ,  F16F3/04 ,  Y02T50/32 ,  Y02T50/44

公开(公告)号：EP3078586A1

公开(公告)日：2016-10-12

申请号：EP15382169.9

申请日：2015-04-08

Applicant: Airbus Operations S.L. ,  Airbus Operations (S.A.S.)

Inventor： Folch Cortes, Diego ,  Martino González, Esteban ,  Mariblanca Lopez, Jose Antonio ,  Diochon, Lionel

IPC: B64C1/10 ,  B64C1/26 ,  B64C5/02 ,  B64C5/06

CPC classification number: B64C1/26 ,  B64C1/10 ,  B64C5/02 ,  B64C5/06

Abstract: The invention provides an aircraft rear structure (10) comprising a substantially flat rear pressure bulkhead (11), with a first side and a second side, opposite to the first side. It also comprises a horizontal stabilizer (21) and a vertical stabilizer (1) which in turn comprises a first spar (2) and a second spar (3). The first spar (2) is attached to a first attachment zone (41) of the second side of the rear pressure bulkhead (11) by means of first attaching means (5, 6), and the second spar (3) is attached to a second attachment zone (42) of the second side of the rear pressure bulkhead (11) by means of second attaching means (7, 8). The second attachment zone (42) being different from the first attachment zone (41).

Abstract translation: 本发明提供了一种飞机后部结构（10），其包括基本平坦的后部压力隔板（11），其具有与第一侧相对的第一侧和第二侧。 它还包括水平稳定器（21）和垂直稳定器（1），所述垂直稳定器（1）又包括第一翼梁（2）和第二翼梁（3）。 第一翼梁（2）通过第一附接装置（5,6）附接到后压舱壁（11）的第二侧的第一附接区域（41），并且第二翼梁（3）附接到 所述后压舱壁（11）的第二侧的第二附接区（42）借助于第二附接装置（7,8）。 第二附接区域（42）不同于第一附接区域（41）。