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    Fuselage Skin Panel Connection System and Method for Connecting Skin Panels
    1.
    发明申请
    Fuselage Skin Panel Connection System and Method for Connecting Skin Panels 审中-公开

    公开(公告)号：US20180148153A1

    公开(公告)日：2018-05-31

    申请号：US15364473

    申请日：2016-11-30

    申请人： The Boeing Company

    发明人： Angelina M. Conti ,  Robert E. Grip ,  Ted K. Rothaupt

    IPC分类号： B64C1/12 ,  B64C1/06 ,  B64F5/00

    CPC分类号： B64C1/12 ,  B64C1/061 ,  B64C1/08 ,  B64F5/00

    摘要： An aircraft is provided. The aircraft includes truss elements configured to form a space frame fuselage, and skin panels connected with the truss elements and configured to form a skin over said space frame fuselage. The skin panels are movable relative to one another so as to prevent loading of the space frame fuselage from inducing loading in the skin. The aircraft includes a fitting. The fitting includes a first intermediate portion, a first outer portion, and a first inner portion. The first outer and inner portions are spaced apart from each other and interconnected by the first intermediate portion. The skin panels include first and second skin panels that are adjacent to each other. The first skin panel has a first end portion that is adjacent to a second end portion of the second skin panel. The fitting is positioned between the first and second skin panels such that the first and second end portions of the skin panels extend between the first inner and outer portions. The fitting is configured to enable the first and second skin panels to move towards each other along a first plane of first outer and inner surfaces of the first and second skin panels while constraining non-planar movement of the skin panels with respect to the first plane.

    COMPUTER-IMPLEMENTED METHOD FOR SPACE FRAME DESIGN, SPACE FRAME CONSTRUCTION KIT AND SPACE FRAME
    3.
    发明申请
    COMPUTER-IMPLEMENTED METHOD FOR SPACE FRAME DESIGN, SPACE FRAME CONSTRUCTION KIT AND SPACE FRAME 审中-公开

    公开(公告)号：US20180011965A1

    公开(公告)日：2018-01-11

    申请号：US15713572

    申请日：2017-09-22

    申请人： AUTODESK, INC.

    发明人： David Benjamin ,  Danil Nagy ,  Damon Lau ,  Dale Zhao

    IPC分类号： G06F17/50 ,  B64C1/08 ,  B64D11/00 ,  B64F5/00

    CPC分类号： G06F17/5086 ,  B64C1/08 ,  B64D11/0023 ,  B64F5/00 ,  Y02T50/46

    摘要： A computer-implemented method for space frame design involves constructing a load stress map in a geometrical boundary representation of a design space, defining attachment points and load application points in the design space, creating a starting network of interconnecting lines between each two of the attachment points and load application points in the design space, assigning load application factors to each line of the starting network of interconnecting lines based on values of the load stress map, generating potential space frame designs by culling different subsets of lines of the starting network of interconnecting lines for each potential space frame design according to variable culling parameters, evaluating the potential space frame designs with respect to optimization parameters, combining the culling parameters for the potential space frame designs the performance score of which is above a predefined performance threshold, and iterating the steps of generating potential space frame designs and evaluating the potential space frame designs on the basis of the combined culling parameters.

    Self-righting frame and aeronautical vehicle
    6.
    发明授权
    Self-righting frame and aeronautical vehicle 有权

    公开(公告)号：US09216808B2

    公开(公告)日：2015-12-22

    申请号：US14751104

    申请日：2015-06-25

    申请人： Gaofei Yan ,  James Dees

    发明人： Gaofei Yan ,  James Dees

    IPC分类号： B64C27/08 ,  B64C1/08 ,  B64C1/06 ,  B64C17/00 ,  A63H27/00

    CPC分类号： B64C1/061 ,  A63H15/06 ,  A63H27/12 ,  A63H30/04 ,  A63H33/005 ,  B64C1/00 ,  B64C1/08 ,  B64C17/00 ,  B64C27/10

    摘要： An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has an apex preferably at a top of a central vertical axis. The apex provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a supporting surface. The frame provides self-righting functionality and protection of elements carried therein.

    Self-righting frame and aeronautical vehicle
    7.
    发明授权
    Self-righting frame and aeronautical vehicle 有权
    自行车架和航空车辆

    公开(公告)号：US09067667B2

    公开(公告)日：2015-06-30

    申请号：US14022213

    申请日：2013-09-09

    申请人： Gaofei Yan ,  James Dees

    发明人： Gaofei Yan ,  James Dees

    IPC分类号： B64C27/08 ,  B64C1/00 ,  B64C27/10 ,  A63H27/00 ,  A63H33/00 ,  A63H30/04

    CPC分类号： B64C1/061 ,  A63H15/06 ,  A63H27/12 ,  A63H30/04 ,  A63H33/005 ,  B64C1/00 ,  B64C1/08 ,  B64C17/00 ,  B64C27/10

    摘要： An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has an apex preferably at a top of a central vertical axis. The apex provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a supporting surface. The frame provides self-righting functionality and protection of elements carried therein.

    摘要翻译： 将自身从倒立状态转换为直立状态的航空车辆具有自对准框架组件，其顶点优选地在中心垂直轴线的顶部。 当车辆在表面上倒置时，顶点提供初始的不稳定性以开始自动矫正过程。 电梯和稳定板横跨所述框架的上部延伸以提供升力，阻力和/或稳定性。 推进系统可以位于框架组件的中心空隙内并且被定向成提供提升力。 电子组件也由自动对准框架承载，用于接收远程控制命令，并且通信地互连到电源，用于远程控制航空车辆起飞，飞行和着陆在支撑表面上。 该框架提供自身的功能和对其中承载的元件的保护。

    Methods and apparatus for digital composites
    8.
    发明授权
    Methods and apparatus for digital composites 有权
    数字复合材料的方法与装置

    公开(公告)号：US08986809B2

    公开(公告)日：2015-03-24

    申请号：US13277103

    申请日：2011-10-19

    申请人： Neil Gershenfeld ,  Kenneth Cheung

    发明人： Neil Gershenfeld ,  Kenneth Cheung

    IPC分类号： B32B3/06 ,  B23P11/00 ,  B64C1/08 ,  B32B5/12 ,  B32B5/26

    CPC分类号： B23P11/00 ,  B32B5/12 ,  B32B5/26 ,  B64C1/06 ,  B64C1/08 ,  B64C3/48 ,  Y10T29/49826 ,  Y10T29/49828 ,  Y10T428/24 ,  Y10T428/24008

    摘要： In exemplary implementations of this invention, a digital material comprising many discrete units is used to fabricate a sparse structure. The units are reversibly joined by elastic connections. Each unit comprises fiber-reinforced composite material. Each unit is small compared to the sparse structure as a whole. Likewise, in a sparse structure made from this digital material, the number of types of units is small compared to the total number of units. The digital material is anisotropic. This anisotropy may be due to different fiber orientations within each unit. Furthermore, different units in a single sparse structure may be oriented in different directions and in different, non-parallel planes. In some cases, the digital material is reinforced with carbon fibers, and connections between units are stronger than the units themselves. The small discrete units may be assembled into a strong, lightweight sparse structure, such as an airframe.

    摘要翻译： 在本发明的示例性实施方案中，使用包含许多分立单元的数字材料来制造稀疏结构。 这些单元通过弹性连接可逆连接。 每个单元包括纤维增强复合材料。 与整体稀疏结构相比，每个单位都很小。 同样，在由这种数字材料制成的稀疏结构中，与总单元数相比，单元类型的数量很小。 数字材料是各向异性的。 这种各向异性可能是由于每个单元内不同的纤维取向。 此外，单个稀疏结构中的不同单元可以在不同的方向和不同的非平行平面中取向。 在某些情况下，数字材料用碳纤维增强，单元之间的连接比单元本身更强。 小型分立单元可以组装成强大的，轻质的稀疏结构，例如机身。

    Self-Righting Frame And Aeronautical Vehicle
    10.
    发明申请
    Self-Righting Frame And Aeronautical Vehicle 有权
    自行车架和航空汽车

    公开(公告)号：US20140014767A1

    公开(公告)日：2014-01-16

    申请号：US14022213

    申请日：2013-09-09

    申请人： Gaofei Yan ,  James Dees

    发明人： Gaofei Yan ,  James Dees

    IPC分类号： B64C1/00 ,  B64C27/10

    CPC分类号： B64C1/061 ,  A63H15/06 ,  A63H27/12 ,  A63H30/04 ,  A63H33/005 ,  B64C1/00 ,  B64C1/08 ,  B64C17/00 ,  B64C27/10

    摘要： An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has an apex preferably at a top of a central vertical axis. The apex provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a supporting surface. The frame provides self-righting functionality and protection of elements carried therein.

    摘要翻译： 将自身从倒立状态转换为直立状态的航空车辆具有自对准框架组件，其顶点优选地在中心垂直轴线的顶部。 当车辆在表面上倒置时，顶点提供初始的不稳定性以开始自动矫正过程。 电梯和稳定板横跨所述框架的上部延伸以提供升力，阻力和/或稳定性。 推进系统可以位于框架组件的中心空隙内并且被定向成提供提升力。 电子组件也由自动对准框架承载，用于接收远程控制命令，并且通信地互连到电源，用于远程控制航空车辆起飞，飞行和着陆在支撑表面上。 该框架提供自身的功能和对其中承载的元件的保护。