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    AIRCRAFT FOR PERFORMING OBSERVATIONS IN THE STRATOSPHERE
    1.
    发明申请
    AIRCRAFT FOR PERFORMING OBSERVATIONS IN THE STRATOSPHERE 审中-公开

    公开(公告)号：WO2020171722A1

    公开(公告)日：2020-08-27

    申请号：PCT/PL2020/000019

    申请日：2020-02-19

    Applicant: INSTYTUT LOTNICTWA

    Inventor： ŻURAWSKI, Rafał

    IPC: B64C39/02 ,  B64D37/04 ,  B64D47/08 ,  B64C1/26

    Abstract: Aircraft is equipped with a telescope built in the fuselage (1) with the initial angular mirror (2) installed in the open part of the fuselage (1) and the main mirror (7) installed in the cylindrical part of the fuselage. The open part of the fuselage (1) represents an open observation cavity with the base made of the bottom arc section of the fuselage (1) rigidly connected with the nose (2) of the aircraft, main mirror (7) is permanently fixed at the end of the cylindrical part of the fuselage (1) at the tail (5) and the initial angular mirror (2) is rotary fixed to the nose (3). Axis of rotation of the initial angular mirror (2) overlaps the longitudinal axis (12) of the aircraft and optical axis of the main mirror (7), the bottom arc section of the fuselage (1) has a recess (13) for observation of the earth, and the lifting surface (6) is releasably fixed to the cylindrical part of the fuselage (1).

    BEFESTIGUNGSEINHEIT ZUM BEWEGLICHEN BEFESTIGEN EINER LUFTFAHRZEUGKOMPONENTE AN EINER TRAGSTRUKTUR EINES LUFTFAHRZEUGS
    2.
    发明申请
    BEFESTIGUNGSEINHEIT ZUM BEWEGLICHEN BEFESTIGEN EINER LUFTFAHRZEUGKOMPONENTE AN EINER TRAGSTRUKTUR EINES LUFTFAHRZEUGS 审中-公开

    公开(公告)号：WO2019025343A1

    公开(公告)日：2019-02-07

    申请号：PCT/EP2018/070556

    申请日：2018-07-30

    Applicant: AIRBUS OPERATIONS GMBH

    Inventor： SEITZ, Philipp ,  BAJORAT, Falk ,  BOCEK, Martin

    IPC: B64C9/02 ,  B64C1/26

    Abstract: Die Erfindung betrifft eine Befestigungseinheit (100) zum beweglichen Befestigen einer Luftfahrzeugkomponente (300) an einer Tragstruktur (400) eines Luftfahrzeugs (500). Die Befestigungseinheit (100) weist ein Anschlusselement (5) mit einer Ausnehmung (5a) auf. Die Befestigungseinheit (100) weist ferner einen ersten Tragarm (1) mit einem ersten Ende (1a) zum Verbinden mit der Tragstruktur (400) des Luftfahrzeugs (500) und einem zweiten Ende (1b) zum Verbinden mit dem Anschlusselement (5) auf. Die Befestigungseinheit (100) weist ferner einen zweiten Tragarm (2) mit einem ersten Ende (2a) zum Verbinden mit der Tragstruktur (400) des Luftfahrzeugs (500) und einem zweiten Ende (2b) zum Verbinden mit dem Anschlusselement (5) auf. Der erste Tragarm (1) und der zweite Tragarm (2) sind derart angeordnet, dass ein Abstand (d) zwischen dem ersten Ende (1a) des ersten Tragarms (1) und dem ersten Ende (2a) des zweiten Tragarms (2) größer ist als ein Abstand (e) zwischen dem zweiten Ende (1b) des ersten Tragarms (1) und dem zweiten Ende (2b) des zweiten Tragarms (2). Der erste Tragarm (1) ist zumindest teilweise mittels eines Umformverfahrens hergestellt. Die Erfindung betrifft ferner die Verwendung einer Befestigungseinheit (100) zur Befestigung eines Seitenruders (300) an einer Tragstruktur (400) eines Luftfahrzeugs (500) sowie ein Verfahren zum Bereitstellen einer beweglichen Befestigung einer Luftfahrzeugkomponente (300) an einer Tragstruktur (400) eines Luftfahrzeugs.

    AIRCRAFT WING UNIT WITH UPPER WING SKIN DEFINING PRESSURE FLOOR
    3.
    发明申请
    AIRCRAFT WING UNIT WITH UPPER WING SKIN DEFINING PRESSURE FLOOR 审中-公开

    公开(公告)号：WO2018203191A1

    公开(公告)日：2018-11-08

    申请号：PCT/IB2018/052912

    申请日：2018-04-26

    Applicant: BOMBARDIER INC. ,  SHORT BROTHERS PLC

    Inventor： MURPHY, Michael ,  ARAUJO, Jack ,  SHUM, Gary ,  BRADLEY, George

    IPC: B64C1/26 ,  B64C3/00

    Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

    AIRCRAFT WING UNIT WITH PRESSURE FENCE
    4.
    发明申请
    AIRCRAFT WING UNIT WITH PRESSURE FENCE 审中-公开

    公开(公告)号：WO2018203189A1

    公开(公告)日：2018-11-08

    申请号：PCT/IB2018/052906

    申请日：2018-04-26

    Applicant: BOMBARDIER INC. ,  SHORT BROTHERS PLC

    Inventor： MURPHY, Michael ,  ARAUJO, Jack ,  SHUM, Gary ,  BRADLEY, George

    IPC: B64C3/58 ,  B64C1/26 ,  B64C1/06

    Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

    MULTIPURPOSE AIRCRAFT
    5.
    发明申请
    MULTIPURPOSE AIRCRAFT 审中-公开
    多用途飞机

    公开(公告)号：WO2015115913A1

    公开(公告)日：2015-08-06

    申请号：PCT/NZ2015/000007

    申请日：2015-01-29

    Applicant: TULLY, Graham Phillip ,  HARTLEY, Paul Robert ,  GLOBAL AERIAL PLATFORMS LIMITED

    Inventor： TULLY, Graham Phillip ,  HARTLEY, Paul Robert ,  HEWSON, Alexander James

    IPC: B64C39/04 ,  B64C1/26 ,  B64C3/32

    CPC classification number: B64C1/26 ,  B64C3/32 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/021 ,  B64C2211/00

    Abstract: The invention relates to a multipurpose twin fuselage aircraft (17) that includes a central wing panel (1) which is releasably attached to each of the fuselages (12, 13) and is located between them. The central wing panel includes a nacelle (8) having a compartment for storage of various pieces of equipment and an engine (7) mounted on the front and/or rear of the central wing panel. In use the aircraft includes several interchangeable central wing panels, configured as determined by the nature of the task to be performed by the aircraft. Preferably the aircraft is an unmanned aerial system/drone. The central wing panels may be configured such that the nacelle and/or the compartment may be jettisoned during flight. In some embodiments the contents of the compartment may be jettisoned during flight.

    Abstract translation: 本发明涉及一种多用途双机身飞机（17），其包括可释放地附接到每个机身（12,13）并且位于它们之间的中央翼板（1）。 中央翼板包括具有用于存储各种设备的隔间的机舱（8）和安装在中央翼板的前部和/或后部的发动机（7）。 在使用中，飞机包括若干可互换的中央翼板，其配置为由飞机执行的任务的性质决定。 飞机最好是无人机系统/无人机。 中央翼板可以被配置成使得在飞行期间机舱和/或隔间可以被抛弃。 在一些实施例中，隔间的内容物可能在飞行期间被抛弃。

    WING ROOT INSERT SYSTEM FOR AN AIRCRAFT FAMILY
    6.
    发明申请
    WING ROOT INSERT SYSTEM FOR AN AIRCRAFT FAMILY 审中-公开

    公开(公告)号：WO2014051923A1

    公开(公告)日：2014-04-03

    申请号：PCT/US2013/057168

    申请日：2013-08-28

    Applicant: THE BOEING COMPANY

    Inventor： REA, Perry Nicholas

    IPC: B64C1/26

    CPC classification number: B64C1/26 ,  Y10T29/49622

    Abstract: A single, common, fuselage and wing design of an aircraft structure provides for two different aircraft models or configurations. A fuselage (12) has a center section cutout area (212). Each wing (16) has an airfoil over substantially its entire span. In one configuration (2A), a center section component (212), such as a wingbox, is inserted into the center section cutout and the wings are connected to opposing sides of the center section component by a side-of-body join. In another configuration (2B), the wings are moved inwardly, joined to the fuselage, and also joined to each other in a centerline join at the centerline (218) of the aircraft wherein a portion (16A) of the airfoil of each wing is then inside the fuselage. Different flaps (210, 220), spacers (222), and/or different engine mount locations (402, 404) may be provided for the wings for the two configurations.

    Abstract translation: 飞机结构的单一，通用，机身和机翼设计提供两种不同的飞机型号或配置。 机身（12）具有中心部分切断区域（212）。 每个翼（16）在其整个跨度上具有翼型件。 在一个构造（2A）中，诸如翼盒的中心部分部件（212）插入到中心部分切口中，并且翼通过身体侧面连接连接到中心部分部件的相对侧。 在另一配置（2B）中，机翼向内移动，与机身相连，并且在飞行器的中心线（218）处以中心线连接处彼此接合，其中每个机翼的翼型部分（16A） 然后在机身内。 可以为这两种配置的翼提供不同的翼片（210,220），间隔件（222）和/或不同的发动机安装位置（402,404）。

    DISPOSITIF D'ECLISSAGE A TENUE MECANIQUE AMELIOREE
    8.
    发明申请
    DISPOSITIF D'ECLISSAGE A TENUE MECANIQUE AMELIOREE 审中-公开
    具有改进的机械保持的鱼类联合装置

    公开(公告)号：WO2012098331A2

    公开(公告)日：2012-07-26

    申请号：PCT/FR2012/050102

    申请日：2012-01-17

    Applicant: AIRBUS OPERATIONS ,  GUILLEMAUT, Julien ,  GALLANT, Guillaume

    Inventor： GUILLEMAUT, Julien ,  GALLANT, Guillaume

    IPC: B64C1/26

    CPC classification number: B64C1/26 ,  F16B5/02 ,  Y10T403/74

    Abstract: L'invention concerne un dispositif d'éclissage destiné à solidariser des premier et second éléments (1, 2) de structure d'un aéronef l'un à l'autre, comportant deux éclisses (20, 30) disposées de part et d'autre des éléments de structure (1, 2) et fixées à ceux-ci par un ensemble d'organes traversants (11) de fixation d'éclisse. Selon l'invention, le dispositif d'éclissage comporte au moins une plaque intermédiaire d'éclissage (40, 50) qui est disposée entre l'une desdites éclisses (20, 30) et lesdits éléments (1, 2) de structure que ladite plaque intermédiaire recouvre en partie, et qui est fixée à ces derniers par un ensemble d' organes traversants (11) de fixation de plaque intermédiaire qui inclut ledit ensemble d'organes traversants (11) de fixation d'éclisse.

    Abstract translation: 本发明涉及一种用于将飞行器的第一和第二结构元件（1,2）彼此固定的鱼接头装置，所述装置包括布置在结构元件（1,2）两侧的两个鱼板（20,30） 并通过一组用于固定鱼板的横向构件（11）固定在其上。 根据本发明，鱼接头装置包括至少一个中间鱼接头板（40,50），其设置在所述鱼板（20,30）中的一个和所述中间部分地覆盖的所述结构元件（1,2）之间 并通过一组用于固定中间板的横向构件（11）固定，包括用于固定鱼板的一组横梁（11）。

    WING SPAR SPLICE JOINT
    10.
    发明申请
    WING SPAR SPLICE JOINT 审中-公开

    公开(公告)号：WO2011071939A3

    公开(公告)日：2011-08-04

    申请号：PCT/US2010059322

    申请日：2010-12-07

    Applicant: GLOBAL AEROSYSTEMS LLC ,  DASCHEL STEPHEN ,  RHODEN CHARLES ,  HENRY RANDY ,  THIBAUT RUSSELL

    Inventor： DASCHEL STEPHEN ,  RHODEN CHARLES ,  HENRY RANDY ,  THIBAUT RUSSELL

    IPC: B64C1/26 ,  B64C3/18

    CPC classification number: B64C3/185 ,  B64C1/26

    Abstract: A wing spar joint is provided for coupling the inboard ends of a right wing spar and a left wing spar. The wing spar joint comprises a forward fitting ( 62 ), an aft fitting ( 50, 52 ), a spar cap a lower chord fitting ( 64 ) and a strap member ( 100 ). A first plurality of fasteners secure the forward fitting and the aft fitting together through a web portion ( 38 ) of the wing spars. A second plurality of fasteners secure the upper spar cap, the lower spar cap and the forward fitting together through upper chords of the wing spars. A third plurality of fasteners secure the lower chord fitting, the strap member and the forward fitting together through lower chords of the wing spars. The forward fitting, aft fitting, spar cap and strap member are thus secured together with the wing spars to form a rigid connecting joint at the inboard ends of the wing spars.

    Abstract translation: 提供翼梁接头用于联接右翼翼梁和左翼翼梁的内侧端部。 翼梁接头包括前配件（62），后配件（50,52），翼梁帽，下弦配件（64）和带构件（100）。 第一多个紧固件通过翼片的腹板部分（38）将前配件和后部固定在一起。 第二多个紧固件通过翼翼的上部弦杆固定上翼梁帽，下翼梁帽和前配件。 第三多个紧固件通过翼翼的下弦固定下弦杆配件，带构件和前配件。 因此，前配件，后配件，翼梁帽和带构件与翼梁一起固定在翼翼的内侧端部处形成刚性连接接头。

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