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    METHOD FOR DETERMINING REDUCTION FACTOR OF AXIAL LOAD BEARING CAPACITY OF A CYLINDRICAL SHELL STRUCTURE IN A ROCKET
    1.
    发明授权
    METHOD FOR DETERMINING REDUCTION FACTOR OF AXIAL LOAD BEARING CAPACITY OF A CYLINDRICAL SHELL STRUCTURE IN A ROCKET 有权

    公开(公告)号：EP2983099B1

    公开(公告)日：2018-11-28

    申请号：EP14779155.2

    申请日：2014-02-12

    Applicant: Dalian University of Technology

    Inventor： WANG, Bo ,  HAO, Peng ,  LI, Gang ,  TIAN, Kuo ,  MENG, Zeng ,  DU, Kaifan ,  ZHOU, Yan ,  ZHANG, Xi ,  TANG, Xiaohan ,  WANG, Bin ,  LUO, Hongzhi

    IPC: G06F17/50 ,  B64C1/06 ,  G01M99/00

    CPC classification number: G01M99/007 ,  B64C1/068 ,  G06F17/5018 ,  G06F2217/16 ,  G06F2217/46 ,  Y02T90/50

    Abstract: A method for determining a reduction factor of a bearing capacity of an axial load cylindrical shell structure relates to stability checking of main bearing strength thin-walled members of aerospace and architectural structures. Different from experiment experience-based conventional defect sensitivity evaluating method represented by NASA SP-8007, a depression defect is introduced in a manner of applying a radial disturbance load. First, an influence rule of a depression defect amplitude of a single point to an axial load bearing capacity is analyzed by using numerical values, so as to determine a load amplitude range; then, defect sensitivity analysis is performed on depression defects of multiple points; then, experiment design sampling is performed by using load amplitude values and load position distribution as design variables; and finally, based on optimizing technologies such as an enumeration method, a genetic algorithm and a surrogate model, the most disadvantageous disturbance load of the multiple points that limits the defect amplitude is searched for, and a reduction factor of the bearing capacity of the axial load cylindrical shell structure is determined, so as to establish a more physical method for evaluating the defect sensitivity and the bearing performance of the axial load cylindrical shell structure.

    ASSEMBLY BODY MANUFACTURING DEVICE AND ASSEMBLY BODY MANUFACTURING METHOD
    4.
    发明公开
    ASSEMBLY BODY MANUFACTURING DEVICE AND ASSEMBLY BODY MANUFACTURING METHOD 审中-公开
    组装身体制造装置和组装身体制造方法

    公开(公告)号：EP3284559A1

    公开(公告)日：2018-02-21

    申请号：EP16832752.6

    申请日：2016-07-19

    Applicant: Mitsubishi Heavy Industries, Ltd.

    Inventor： TOMBE, Toshihiro ,  GOTO, Takuya ,  INAGAKI, Takahiro ,  HIRAI, Makoto ,  GOTO, Naoki ,  MIZUKAMI, Masanobu ,  NAKAMURA, Katsumi

    IPC: B23P19/00 ,  B23P19/04 ,  B25J13/00 ,  B64F5/00

    CPC classification number: B25J9/1694 ,  B21J15/142 ,  B23P19/10 ,  B23P2700/01 ,  B25J9/0093 ,  B25J13/00 ,  B25J13/086 ,  B64C1/061 ,  B64C1/064 ,  B64C1/068 ,  B64C1/069 ,  B64C3/18 ,  B64F5/00 ,  B64F5/10 ,  G05B19/402 ,  G05B19/41805

    Abstract: When a long shaped member is to be held, in order to hold the long shaped member in the original shape of the long shaped member at a precise position without using a jig for immobilization, a long member assembling device (1) is provided with: multiple hand parts (8) that hold a long member (10); arm parts (9) and trunk parts (12) that move the hand parts (8) to adjust the po - sitions of the hand parts (8) holding the long member (10); a storage unit having stored therein the original shape of the long member (10); and a control unit (30) that, on the basis of the original shape of the long member (10) stored in the storage unit, drives the arm parts (9) and the trunk parts (12) to adjust the position of the multiple hand parts (8) holding the long member (10) such that the shape of the long member (10) held by the hand parts (8) matches the original shape of the long member (10) stored in the storage unit.

    Abstract translation: 在保持长条状构件的情况下，为了将长条状构件保持原来的长条状的构件在精密的位置而不使用固定用夹具，长构件组装装置（1）具备： 容纳长构件（10）的多个手部件（8）; 臂部分9和主体部分12，它们移动手部分8以调整保持长部分10的手部分8的位置; 存储单元，其中存储了所述长构件（10）的原始形状; 和控制单元（30），其基于存储在存储单元中的长构件（10）的原始形状来驱动臂部分（9）和主干部分（12）以调整多重 （8）保持长构件（10），使得由手部（8）保持的长构件（10）的形状与存储在存储单元中的长构件（10）的原始形状匹配。

    ROTATABLE SYSTEM FOR REMOVING GAS FROM A SEALANT
    6.
    发明公开
    ROTATABLE SYSTEM FOR REMOVING GAS FROM A SEALANT 审中-公开

    公开(公告)号：EP3213802A3

    公开(公告)日：2017-11-22

    申请号：EP16204424.2

    申请日：2016-12-15

    Applicant: The Boeing Company

    Inventor： Podnar, Gregg W.

    IPC: B01D19/00 ,  B05C5/02 ,  B05C17/005 ,  B64C1/06 ,  B64C3/00 ,  B64D37/02

    CPC classification number: B01D19/0052 ,  B01D19/0026 ,  B05C5/02 ,  B05C5/0225 ,  B05C17/005 ,  B05C17/00579 ,  B64C1/068 ,  B64C3/00 ,  B64D37/02 ,  B64F5/0009

    Abstract: Systems for removing gas from a sealant and transferring gas-less sealant to an applicator are provided. The system may comprise: a rotatable chamber (102) including: a first opening (104) for receiving sealant; a hollow conduit (106) arranged such that when gas accumulates in the center of the rotatable chamber when the rotatable chamber is rotating, the gas is ventable from the rotatable chamber; a second opening (108) for receiving gas-less sealant from the rotatable chamber after the gas is vented from the hollow conduit; and a motor (110) operatively configured to rotate the rotatable chamber; and a gas-less sealant applicator (112) in fluid communication with the second opening of the rotatable chamber such that gas-less sealant released by the second opening is flowable into the applicator. The system may also include a robot arm (304) including an end effector with a sealant dispensing nozzle. A method for applying sealant to an aircraft structure is also provided.

    STIFFENED FUSELAGE COMPONENT AS WELL AS METHOD AND APPARATUS FOR MANUFACTURING A STIFFENED FUSELAGE COMPONENT
    8.
    发明公开
    STIFFENED FUSELAGE COMPONENT AS WELL AS METHOD AND APPARATUS FOR MANUFACTURING A STIFFENED FUSELAGE COMPONENT 审中-公开
    加筋船体部件及其方法和设备用于制造部件加固船体

    公开(公告)号：EP3109152A1

    公开(公告)日：2016-12-28

    申请号：EP15173538.8

    申请日：2015-06-24

    Applicant: Airbus Operations GmbH

    Inventor： Joern, Dr. Paul

    IPC: B64C1/08 ,  B29C70/44 ,  B29D99/00

    CPC classification number: B64C1/068 ,  B29B11/06 ,  B29C65/601 ,  B29D99/0014 ,  B29D99/0021 ,  B29K2307/04 ,  B29K2663/00 ,  B29K2671/00 ,  B29L2031/3082 ,  B64C1/08 ,  B64C1/12 ,  B64C2001/0045 ,  B64C2001/0072 ,  Y02T50/43

    Abstract: A stiffened fuselage component (10) made of a fiber reinforced composite material, in particular for use in an aircraft, comprises a skin element (12) and a plurality of elongated stiffening elements (18) forming a stiffening element pattern comprising a plurality of node points (20) and being attached to an inner surface (16) of the skin element (12), wherein at least some of the node points (20) are defined by an intersection of at least two stiffening elements (18) at an acute angle or an obtuse angle, and wherein at least some of the elongated stiffening elements (18) are shaped so as to define an internal cavity (22) delimited by an inner surface (24) of the stiffening elements (18) and covered by the skin element (12).

    Abstract translation: 钢筋制成的纤维的硬挺机身部件（10）的复合材料，特别是用于在飞机上使用，包括形成包含节点的多个A加强元件图案的皮肤元件（12）和细长的加强元件的多个（18） 点（20）和附连到在皮肤元件的内表面（16）（12）worin至少一些节点的点（20）通过在至少两个加强元件（18）的相交处定义急性 角或钝角，且worin至少一些所述细长加强元件（18）被成形为在由分隔内部空腔（22）中的加强元件（18）的内表面（24），以限定和由覆盖 皮肤元件（12）。

    Composite barrel sections for aircraft fuselages and methods for manufacturing such barrel sections
    9.
    发明授权
    Composite barrel sections for aircraft fuselages and methods for manufacturing such barrel sections 有权
    复合汽缸零件飞机机身和方法用于生产这样的气缸部

    公开(公告)号：EP2394909B1

    公开(公告)日：2016-12-28

    申请号：EP11174903.2

    申请日：2005-03-28

    Applicant: The Boeing Company

    Inventor： Biornstad, Robert D. ,  Blankinship, Bruce C. ,  George, Terry ,  Ingram, William H.

    IPC: B64C1/12 ,  B64C1/06 ,  B64C1/00 ,  B29C53/58 ,  B29C70/86 ,  B29D99/00 ,  B29C70/32 ,  B29C70/44 ,  B29C70/38

    CPC classification number: B64C1/068 ,  B29C53/587 ,  B29C70/32 ,  B29C70/382 ,  B29C70/44 ,  B29D99/0014 ,  B29L2031/3082 ,  B64C1/12 ,  Y02T50/43 ,  Y10T428/24636

    Abstract: Composite sections for aircraft fuselages and methods and systems for manufacturing such sections are disclosed herein. A composite section configured in accordance with one embodiment of the invention includes a skin and at least first and second stiffeners. The skin can include a plurality of unidirectional fibers forming a continuous surface extending 360 degrees about an axis. The first stiffener can include a first flange portion bonded to an interior surface of the skin and a first raised portion projecting inwardly and away from the interior surface of the skin. The second stiffener can include a second flange portion bonded to the interior surface of the skin and a second raised portion projecting inwardly and away from the interior surface of the skin. A method for manufacturing a section of a fuselage in accordance with one embodiment of the invention includes positioning a plurality of uncured stiffeners on a mandrel assembly. The method can further include applying a plurality of fiber tows around the plurality of uncured stiffeners on the mandrel assembly.

    Abstract translation: 用于飞机机身和方法和系统制造研究部综合部是在光盘游离缺失。 在雅舞蹈配置成与本发明的一个实施例的复合部分包括皮肤和至少第一和第二加劲肋。 皮肤可包括形成一个连续的表面延伸360度关于轴线的单向纤维的复数。 第一加强件可包括结合到所述皮肤的内表面的第一凸缘部分和从所述皮肤的内表面向内并离开伸出的第一凸起部分。 第二加强件可以包括粘结到皮肤的内表面的第二凸缘部以及从皮肤的内表面向内并离开伸出的第二凸起部分。 一种用于制造在雅舞蹈与本发明的一个实施例的机身的部分方法包括在芯轴组件定位未固化的加强件的复数。 该方法可以包括施加纤维束的另外的多个围绕所述心轴组件未固化的加强件的多元性。

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