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    • 2. 发明申请
    • METHOD OF MANUFACTURING A STRUCTURE
    • 制造结构的方法
    • US20100327114A1
    • 2010-12-30
    • US12821718
    • 2010-06-23
    • Alex ILIOPOULOSJohn FLOOD
    • Alex ILIOPOULOSJohn FLOOD
    • B64C3/18B32B3/02B32B37/00B64C1/00
    • B32B3/263B29C70/342B29K2707/04B29K2709/08B29L2031/3085B64C1/12B64C1/26B64C3/185B64C3/26Y02T50/43Y10T428/24612
    • A method of manufacturing a structure, the method comprising: forming a panel assembly by bonding a stack of thickness control plies of composite material to a laminar composite panel, the stack of thickness control plies having a first edge proximate an edge of the laminar composite panel, a second edge opposite the first edge, and a ramp where the thickness of the stack of thickness control plies decreases towards the first or second edge; measuring the thickness of the laminate composite panel or the panel assembly; controlling the number of thickness control plies in accordance with the measured thickness; attaching a first component to the panel assembly, the first component having a surface which engages the laminar composite panel and a ramp which engages the ramp in the stack of thickness control plies; and attaching the laminar composite panel at or near its edge to a further component.
    • 一种制造结构的方法,所述方法包括:通过将复合材料的厚度控制层的堆叠结合到层状复合板来形成面板组件,所述厚度控制层堆叠具有靠近所述层状复合板的边缘的第一边缘 ,与第一边缘相对的第二边缘,以及斜面,其中厚度控制层叠层的厚度朝向第一边缘或第二边缘减小; 测量层压复合板或板组件的厚度; 根据测量厚度控制厚度控制层的数量; 将第一部件附接到所述面板组件,所述第一部件具有接合所述层状复合面板的表面和与所述厚度控制层叠层中的所述斜面接合的斜面; 以及将层状复合板在其边缘处或附近附接到另一部件。
    • 3. 发明申请
    • COMPOSITE JOINT PROTECTION
    • 复合接头保护
    • US20100308170A1
    • 2010-12-09
    • US12735761
    • 2009-03-12
    • Paul HadleyJohn FloodAlan Quayle
    • Paul HadleyJohn FloodAlan Quayle
    • B64C3/26B32B37/02B32B37/24
    • B64C1/12B29C65/564B29C65/76B29C66/43441B29C66/721B29L2031/3076Y10T156/10
    • The present invention relates to a joint between a laminar composite cover (12) and a second cover (15) (which may or may not be also formed from a composite material). The invention also relates to a method of manufacturing such a joint and a method of manufacturing a composite cover suitable for use in such a joint. The laminar composite cover (12) comprises a stack of layers, substantially all of the layers being shaped to form a joggle, each joggle comprising a first portion, a second portion where the layer extends substantially parallel with the first portion, and a ramp (33) between the first and second portions where the layer extends at an angle to the first and second portions, the number of layers being substantially the same on both sides of the ramp. The second cover (15) partially overlaps with the composite cover, and a clamp or fastener (31) holds the covers together where they overlap. The covers have external sides which are substantially aligned with each other so as to form a smooth aerodynamic surface.
    • 本发明涉及层状复合盖(12)和第二盖(15)之间的接头(其可以或可以不由复合材料形成)。 本发明还涉及这种接头的制造方法和制造适用于这种接头的复合罩的方法。 层状复合材料覆盖物(12)包括一叠层,基本上所有的层都被成形为形成一个弯曲部,每个弯曲部包括第一部分,第二部分,其中该层基本上平行于第一部分延伸,以及斜面 在第一和第二部分之间,其中层与第一和第二部分成一定角度延伸,层数在斜坡两侧基本相同。 第二盖(15)部分地与复合盖重叠,并且夹具或紧固件(31)将盖保持在重叠的位置。 盖具有彼此基本对准的外侧,以便形成平滑的空气动力学表面。
    • 7. 发明授权
    • Composite panel stiffener
    • 复合板加强筋
    • US08864074B2
    • 2014-10-21
    • US12602158
    • 2008-06-24
    • John Flood
    • John Flood
    • B64C3/18B64C1/06B64C3/26B29C70/30G05B19/4099
    • B64C3/182B29C70/30B64C3/26G05B19/4099G05B2219/35044G05B2219/45204Y02T50/43Y10T428/24174Y10T428/24628
    • A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer. The risk of causing, during fabrication of the stringer, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the stringer varies may be reduced by means of such arrangements.
    • 用于航空航天结构的多层复合L形纵梁包括从脚的边缘延伸的脚和腹板。 脚上的第一表面被成形为邻接待硬化的结构。 脚还具有与第一表面相对的第二表面。 纸幅在复合材料中与第一和第三表面分别具有在同一层的第三表面和第四表面。 纵梁的几何形状可以沿其长度(L)变化,使得当第一表面朝向第二表面移位时,第四表面朝向第三表面移位。 从脚的远端边缘到桁条的腹板的远端边缘的显影宽度(DW)可以沿着桁条的长度的所有横截面基本上是恒定的。 通过这种布置可以减少在制造纵梁期间引起在纵梁几何形状变化的区域中复合材料层的不希望的压痕,应力或拉伸的风险。
    • 9. 发明申请
    • COMPOSITE PANEL STIFFENER
    • 复合面板加热器
    • US20100170985A1
    • 2010-07-08
    • US12602158
    • 2008-06-24
    • John Flood
    • John Flood
    • B64C1/06B64C3/18B32B3/00B32B7/00B29C65/02G06F17/50
    • B64C3/182B29C70/30B64C3/26G05B19/4099G05B2219/35044G05B2219/45204Y02T50/43Y10T428/24174Y10T428/24628
    • A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer. The risk of causing, during fabrication of the stringer, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the stringer varies may be reduced by means of such arrangements.
    • 用于航空航天结构的多层复合L形纵梁包括从脚的边缘延伸的脚和腹板。 脚上的第一表面被成形为邻接待硬化的结构。 脚还具有与第一表面相对的第二表面。 纸幅在复合材料中与第一和第三表面分别具有在同一层的第三表面和第四表面。 纵梁的几何形状可以沿其长度(L)变化,使得当第一表面朝向第二表面移位时,第四表面朝向第三表面移位。 从脚的远端边缘到桁条的腹板的远端边缘的显影宽度(DW)可以沿着桁条的长度的所有横截面基本上是恒定的。 通过这种布置可以减少在制造纵梁期间引起在纵梁几何形状变化的区域中复合材料层的不希望的压痕,应力或拉伸的风险。
    • 10. 发明申请
    • Elastomeric fibers comprising controlled distribution block copolymers
    • 包含受控分布嵌段共聚物的弹性纤维
    • US20070055015A1
    • 2007-03-08
    • US11219478
    • 2005-09-02
    • John FloodMartin Ehrlich
    • John FloodMartin Ehrlich
    • C08L53/00
    • C08F297/04C08F297/044C08L23/10C08L51/006C08L53/00C08L53/025D01F1/10D01F8/06D01F8/12D01F8/14C08L2666/24C08L2666/02C08L2666/04
    • Bicomponent fibers comprising a thermoplastic polymer and an elastomeric compound are made which can be continuously extruded from the melt at high production rates. The elastomeric compound comprises a selectively hydrogenated block copolymer having a controlled distribution elastomeric block which has a mono alkenyl arene blockiness index of less than 40 mol % and high flow. Elastomeric fibers are also provided which comprise a controlled distribution block copolymer and a slip agent. The fibers are useful for the manufacture of articles such as woven fabrics, spunbond non-woven fabrics or filters, staple fibers, yarns and bonded, carded webs. The bicomponent fibers can be made using a process comprising coextrusion of the thermoplastic polymer and elastomeric compound to produce fibers at spinning speeds of at least 1000 mpm and having a denier from 0.1 to 50 g/9000 m.
    • 制备包含热塑性聚合物和弹性体化合物的双组分纤维,其可以以高生产率从熔体中连续挤出。 弹性体化合物包括具有受控分布的弹性体嵌段的选择性氢化嵌段共聚物,其具有小于40mol%的单链烯基芳烃嵌段指数和高流动性。 还提供弹性纤维,其包含受控分布嵌段共聚物和增滑剂。 纤维可用于制造诸如机织织物,纺粘非织造织物或过滤器,短纤维,纱线和粘合的梳理纤维网之类的制品。 双组分纤维可以使用包括共挤出热塑性聚合物和弹性体化合物以在纺丝速度为至少1000mpm并具有0.1-50g / 9000m的旦数的纤维的方法制备。