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11. 发明授权

US09592901B2 Multi-directional load joint system 有权
标题翻译：多向负载接头系统
公开(公告)号：US09592901B2
公开(公告)日：2017-03-14
申请号：US14594292
申请日：2015-01-12
申请人： Textron Innovations Inc.
发明人： John R. McCullough , David Gordon Carlson , James Donn Hethcock , Paul K. Oldroyd , Carl A. May
IPC分类号： B64C1/12 , B29D99/00 , B64C1/06 , F16B5/01 , F16B5/12 , F16B17/00 , B29C65/50 , B29C65/56 , B29C65/00 , B29L31/30 , B64C1/00 , B29C65/48
CPC分类号： B64C1/12 , B29C65/4835 , B29C65/5021 , B29C65/5057 , B29C65/5078 , B29C65/5085 , B29C65/562 , B29C66/1122 , B29C66/1142 , B29C66/1162 , B29C66/1282 , B29C66/12881 , B29C66/43441 , B29C66/721 , B29C66/72525 , B29C66/8416 , B29D99/001 , B29L2031/3076 , B64C1/06 , B64C2001/0072 , F16B5/01 , F16B5/12 , F16B17/00 , Y02T50/43 , Y10T29/49622 , Y10T403/70
摘要： A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.
摘要翻译：结构接头包括具有第一基部和第一腿部的第一构件。结构接头还包括具有第二基部和第二基部的第二构件。第一基部和第二基部在重叠部分处连接在一起。第一腿部分和第二腿部部分形成用于结构上结合到结构构件的空腔。

12. 发明申请

US20170066520A1 INTEGRATED RIBS FOR CENTRAL WING BOX 审中-公开
标题翻译：中央礼盒集成RIBS
公开(公告)号：US20170066520A1
公开(公告)日：2017-03-09
申请号：US15255639
申请日：2016-09-02
申请人： AIRBUS OPERATIONS (S.A.S.)
发明人： Denis SOULA , Matthieu PLET , Javier MAQUEDA LAHOZ
IPC分类号： B64C3/18 , B64F5/00 , B64C3/22
CPC分类号： B64C3/187 , B64C1/06 , B64C1/26 , B64C3/185 , B64C3/22
摘要： A central wing box for an aircraft, including a top panel, a bottom panel, a front spar, a rear spar, and at least one secondary rib. A secondary rib includes two stiffeners, a first stiffener extending adjacent to the top panel and to one of the front spar and the rear spar, and a second stiffener extending adjacent to the bottom panel and to the other of the front spar and the rear spar. A reduced number of components can be employed, thereby simplifying the construction of the central wing box of an aircraft, particularly the installation of the secondary ribs.
摘要翻译：一种用于飞行器的中央翼盒，包括顶板，底板，前翼梁，后翼梁和至少一个副肋。辅助肋包括两个加强件，第一加强件，其邻近顶板延伸并且与前翼梁和后翼梁中的一个相邻延伸;以及第二加强件，其相邻于底板延伸并延伸到前翼梁和后翼梁中的另一个。可以采用减少数量的部件，从而简化飞行器的中央翼盒的结构，特别是辅助肋的安装。

13. 发明授权

US09561698B2 Shape morphing fuselage for an aerocar 有权
标题翻译：形状变形机身为气溶胶
公开(公告)号：US09561698B2
公开(公告)日：2017-02-07
申请号：US14577861
申请日：2014-12-19
申请人： Toyota Motor Engineering & Manufacturing North America, Inc.
发明人： Umesh N. Gandhi , Taewoo Nam
IPC分类号： B60F5/02 , B64C3/56 , B64C1/06
CPC分类号： B60F5/02 , B64C1/06 , B64C3/56 , B64C37/00
摘要： A shape morphing fuselage and method of transitioning an aerocar from a land mode to a flight mode are disclosed. The fuselage includes a plurality of flexible frame members and tensile skin extending between the plurality of flexible frame members as well as an actuation system configured to bend the plurality of flexible frame members between a contracted configuration associated with a flight mode and an expanded configuration associated with a land mode. The fuselage can also include a hatch pivotable about an axis of one of the flexible frame members in the expanded configuration and configured to open for deployment and retraction of wings for the aerocar.
摘要翻译：公开了一种形状变形机身和将气溶胶从陆地模式转换到飞行模式的方法。机身包括多个柔性框架构件和在多个柔性框架构件之间延伸的拉伸表皮，以及构造成在与飞行模式相关联的收缩构型和与飞行模式相关联的扩展构型之间弯曲多个柔性框架构件的致动系统土地模式。机身还可以包括可在扩展构型中围绕一个柔性框架构件的轴线枢转的舱口，并且构造成用于打开用于气瓶的翼的展开和收回。

14. 发明申请

US20170030399A1 TIE ROD AND METHOD FOR MANUFACTURING A TIE ROD 审中-公开
标题翻译： TIE ROD及其制造方法
公开(公告)号：US20170030399A1
公开(公告)日：2017-02-02
申请号：US15221218
申请日：2016-07-27
申请人： AIRBUS OPERATIONS GMBH
发明人： Inge SANDERS , Nabankele-Martial SOMDA , Anna WENGORRA , Bastian SCHAEFER
IPC分类号： F16C7/02 , B64C1/06 , B29C67/00 , B22F3/105 , B33Y80/00 , B23K26/342 , B23K26/00 , E04C3/02 , B33Y10/00
CPC分类号： F16C7/02 , B22F3/1055 , B22F2301/052 , B22F2998/10 , B23K26/0006 , B23K26/342 , B23K2101/06 , B23K2103/10 , B23K2103/16 , B23K2103/42 , B23K2103/50 , B29C64/153 , B29K2307/04 , B29L2031/06 , B33Y10/00 , B33Y80/00 , B64C1/06 , E04C3/02 , F16C2220/24 , F16C2300/02
摘要： A tie rod includes an elongate tie rod body of substantially uniform cross-section, the tie rod body comprising at least eight columns that run parallel to each other and are placed in a circumferential formation around a central axis of the tie rod.
摘要翻译：拉杆包括具有基本均匀横截面的细长拉杆主体，拉杆主体包括至少八个彼此平行延伸的柱，并且围绕拉杆的中心轴线放置在周向地层中。

15. 发明申请

US20170001701A1 System for Embedded Removable Aperture 有权
标题翻译：嵌入式可拆卸孔径系统
公开(公告)号：US20170001701A1
公开(公告)日：2017-01-05
申请号：US14755818
申请日：2015-06-30
申请人： Andrew J. Osvog
发明人： Andrew J. Osvog
IPC分类号： B64C1/06 , B64C3/18 , B64C3/00
CPC分类号： B64C1/06 , B64C1/36 , B64C3/00 , B64C3/185 , B64C3/20 , B64C2211/00 , H01Q1/287
摘要： A system includes a septum sleeve, an aperture fitting, and a removable aperture. The septum sleeve is substantially hollow and is configured to be positioned at least partially within a core of an assembly of an aircraft. The aperture fitting is configured to provide an interface to mechanically fasten the removable aperture. The removable aperture is configured to contain one or more electronic components and to be removably positioned at least partially within the septum sleeve.
摘要翻译：系统包括隔膜套筒，孔口配件和可拆卸孔。隔膜套筒基本上是中空的，并且构造成至少部分地定位在飞行器的组件的芯部内。孔口配件被配置为提供用于机械地固定可移除孔的界面。可拆卸的孔被构造成包含一个或多个电子部件，并且可移除地至少部分地定位在隔膜套筒内。

16. 发明申请

US20160375977A1 APPARATUSES AND METHODS FOR FLEXURALLY CONTROLLING ELONGATED STRUCTURES 审中-公开
标题翻译：用于柔性控制延长结构的装置和方法
公开(公告)号：US20160375977A1
公开(公告)日：2016-12-29
申请号：US14750244
申请日：2015-06-25
申请人： The Boeing Company
发明人： Richard William Siers
IPC分类号： B64C1/06
CPC分类号： B64C1/06 , B64C1/064 , B64C1/065 , B64C3/182 , B64C3/185 , B64C3/38
摘要： A flexurally controlled system (100) comprises an elongated structure (102), a tendon (112) attached to the elongated structure (102), and an actuator (118) operable to apply a tensile load to the tendon (112). The actuator (118) is operable to apply the tensile load to the tendon (112) when at least one of the first side (108) of the elongated structure (102) is under a first tensile stress or the second side (110) of the elongated structure is under a first compressive stress. The actuator is also operable to apply no load to the tendon (112) when the first side (108) and the second side (110) of the elongated structure (102) are not under stress. The tendon (112) is non-coaxial with a central axis (122) of the elongated structure (102) and is aligned with at least one region of the elongated structure (102).
摘要翻译：弯曲控制系统（100）包括细长结构（102），连接到细长结构（102）的腱（112）和可操作以将拉伸载荷施加到腱（112）的致动器（118）。当细长结构（102）的第一侧（108）中的至少一个处于第一拉伸应力或第二侧面（110）处时，致动器（118）可操作以将拉伸载荷施加到腱（112）细长结构处于第一压缩应力下。当细长结构（102）的第一侧（108）和第二侧（110）不受应力时，致动器还可操作以在钢筋（112）上施加无载荷。腱（112）与细长结构（102）的中心轴线（122）不同轴并且与细长结构（102）的至少一个区域对准。

17. 发明申请

US20160332392A1 METHOD OF FORMING COMPOSITE STRUCTURES 审中-公开
标题翻译：形成复合结构的方法
公开(公告)号：US20160332392A1
公开(公告)日：2016-11-17
申请号：US15153216
申请日：2016-05-12
申请人： AIRBUS OPERATIONS LIMITED
发明人： Jonathan PRICE , Steven EVANS
IPC分类号： B29C70/34 , B29C70/38 , B29C70/08
CPC分类号： B29C70/34 , B29C53/382 , B29C70/08 , B29C70/30 , B29C70/382 , B29L2031/3076 , B29L2031/3085 , B32B3/00 , B32B3/04 , B32B27/00 , B32B27/06 , B32B27/12 , B32B37/06 , B32B37/10 , B32B2305/00 , B32B2305/72 , B32B2307/50 , B32B2405/00 , B32B2597/00 , B32B2605/18 , B64C1/06 , B64C3/00 , B64C3/18 , B64C5/02 , B64C2001/0072 , C08J5/042 , C08J5/24 , C08J2300/22 , C08J2300/24 , C08J2363/00 , Y02T50/43
摘要： A method of forming composite components is described in which a composite lay-up is created using varying fibre types across the lay-up. This can adapt the lay-up to forming processes in regions of the lay-up to be formed and uses fibre types which give the greatest strength benefits in areas which do not need to be formed. Regions not requiring forming may have binders in them activated prior to a forming step or steps, after which the formed regions may be impregnated with a matrix and the component cured.
摘要翻译：描述了形成复合部件的方法，其中使用跨越层叠的不同纤维类型产生复合层叠。这样可以适应形成层叠区域的成型工艺，并且使用在不需要形成的区域中具有最大强度优点的纤维类型。不需要成形的区域可以在其形成步骤或步骤之前具有活化的粘合剂，然后可以用基质浸渍所形成的区域，并使组分固化。

18. 发明申请

US20160244141A1 SINGLE PIECE FUSELAGE BARREL 有权
标题翻译：单条FUSELAGE BARREL
公开(公告)号：US20160244141A1
公开(公告)日：2016-08-25
申请号：US15145987
申请日：2016-05-04
申请人： The Boeing Company
发明人： Francis E. Andrews , Max U. Kismarton , William J. Koch, IV
IPC分类号： B64C1/06 , B29C70/20 , B29C70/30 , B64F5/00 , B64C1/12
CPC分类号： B64C1/06 , B29C70/202 , B29C70/30 , B29C70/44 , B29K2105/108 , B29K2105/246 , B29K2105/253 , B29K2307/04 , B29K2309/08 , B29K2995/0089 , B29L2031/3082 , B64C1/068 , B64C1/12 , B64C2001/0072 , B64F5/10 , Y02T50/43
摘要： In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.
摘要翻译：根据本发明，提供一种飞机无脊椎机身结构，其包括具有多个树脂浸渍的皮肤纤维的冲击兼容外皮，其形成外皮表面，内无脊髓皮肤表面和皮肤厚度。包括多个加强件，每个加强件均包括多个树脂浸渍的加强纤维，其集成到内部无脊椎皮肤结构中。多个树脂浸渍的皮肤纤维不与多个树脂浸渍的加强纤维对准。

19. 发明申请

US20160244140A1 JOINT, AND AIRCRAFT STRUCTURE 审中-公开
标题翻译：联合和飞机结构
公开(公告)号：US20160244140A1
公开(公告)日：2016-08-25
申请号：US14908743
申请日：2014-05-20
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Toshio ABE , Kiyoka TAKAGI , Takayuki KOYAMA , Kazuaki KISHIMOTO , Kouichi SAITO , Takashi ISHIDA
IPC分类号： B64C1/06 , B29C65/78 , B29C65/00 , F16B11/00
CPC分类号： B64C1/06 , B29C65/48 , B29C65/7808 , B29C65/7814 , B29C66/12441 , B29C66/12443 , B29C66/12449 , B29C66/43441 , B29C66/7212 , B29K2307/04 , B29L2031/3076 , F16B11/006
摘要： Provided is a joint and an aircraft structure wherein it is possible to position a member relative to a preform with high accuracy. A groove into which a plate member (30) is inserted is formed in a pi-shaped joint (20) provided on the preform (21), and the preform (21) and the plate member (30) are connected by being bonded. Moreover, a fitting shape (32A-1) into which the plate member (30) is fitted is formed on the pi-shaped joint (20) on the whole groove bottom face. Additionally, a fitting shape (32A-2) into which the plate member (30) is fitted is formed on a portion of the groove bottom face. Furthermore, fitting shapes (32B-1, 32B-2), into which the groove bottom face that is formed on the pi-shaped joint (20) is fitted, are formed on the surface of the plate material (30) that is fitted with the pi-shaped joint (20).
摘要翻译：提供了一种联合和飞机结构，其中可以高精度地相对于预成型件定位构件。在设置在预成型体（21）上的一个弯曲形状的接头（20）中形成插入有板件（30）的槽，预成型件（21）和板件（30）通过接合连接。此外，在整个槽底面上的pi形接头（20）上形成有安装板构件（30）的嵌合形状（32A-1）。此外，在槽底面的一部分上形成有嵌合板构件（30）的嵌合形状（32A-2）。此外，在嵌合的p型接头（20）上形成的槽底面的嵌合形状（32B-1,32B-2）形成在安装的板材（30）的表面上与π形接头（20）。

20. 发明申请

US20160152315A1 AIRCRAFT FUSELAGE FRAME 审中-公开
标题翻译：飞机融合框架
公开(公告)号：US20160152315A1
公开(公告)日：2016-06-02
申请号：US14952376
申请日：2015-11-25
申请人： Airbus Operations S.L. , Airbus Operations SAS
发明人： Esteban MARTINO GONZALEZ , Diego FOLCH CORTES , Pablo GOYA ABAURREA , Angel PASCUAL FUERTES , Sandra LINARES MENDOZA , Julien GUILLEMAUT , Eric BOUCHET , Jerome COLMAGRO , Jonathan BLANC
IPC分类号： B64C1/06 , B64C3/32 , B64C1/12
CPC分类号： B64C1/061 , B64C1/06 , B64C1/12 , B64C1/16 , B64C1/26 , B64C3/32
摘要： An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.
摘要翻译：一种包括适于位于机身周边内的中心元件的飞行器机身框架，以及从作为提升表面的纵向结构的一部分的中心元件的两侧突出到机身的周边外侧的两个侧向延伸部。中心元件和两个横向延伸部被配置为一体的部件。

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