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1. 发明专利

JP2004130777A Roll forming method 审中-公开
标题翻译：滚筒成型方法
公开(公告)号：JP2004130777A
公开(公告)日：2004-04-30
申请号：JP2003204273
申请日：2003-07-31
申请人： Airbus Uk Ltd , エアバス・ユ―ケ―・リミテッド
发明人： BURLEY GRAHAM J , WILLIAMS STEPHEN , KAYE ALLAN J
IPC分类号： B29C70/06 , B29C53/04 , B29C70/50 , D06C15/00
CPC分类号： B29C70/504 , B29C53/043 , B29D99/0003
摘要： PROBLEM TO BE SOLVED: To provide a rational roll forming method.
SOLUTION: A roll forming machine, which has a set of rollers 14, 20, 28 and 36, and curable matrices 28 and 36, shapes a fabric 13 such as a fabric impregnated with the curable matrices. The feed roller 36 feeds a raw material 37 with a certain length, such as a strand (tow) for the fabric, onto the fabric during or after a shaping process. This roll forming process is especially useful for manufacturing a blade wing reinforcing material (stiffener) for an aircraft wing.
COPYRIGHT: (C)2004,JPO
摘要翻译：要解决的问题：提供一种合理的辊轧成形方法。解决方案：具有一组辊14,20,28和36以及可固化基质28和36的辊成型机成形织物13，例如浸渍有可固化基质的织物。进给辊36在成形过程中或之后将一定长度的原料37（例如织物的股线（丝束））送入织物上。该辊成型方法对于制造用于飞机机翼的叶片翼加强材料（加强筋）尤其有用。版权所有（C）2004，JPO

2. 发明申请

WO2009044194A3 METHOD OF MOULDING A CHARGE 审中-公开
标题翻译：模拟电荷的方法
公开(公告)号：WO2009044194A3
公开(公告)日：2009-11-26
申请号：PCT/GB2008050882
申请日：2008-09-29
申请人： AIRBUS UK LTD , PRIDIE JAGO
发明人： PRIDIE JAGO
IPC分类号： B29C43/36 , B29C70/44 , B29C70/54
CPC分类号： B29C70/44 , B29C43/3642 , B29C70/542 , B29C2043/3644 , Y02T50/433 , Y10T428/24132
摘要： A method of moulding a charge (12) during the manufacture of a composite part. The method comprises: placing the charge and a diaphragm (4) on a male tool, the charge having a first part (12a) which is positioned above a top of the male tool (2) and a second part (12b, 12c) which projects to one side of the maletool; and progressively deforming the second part of the charge against a side ofthe male tool by applying a pressure difference across the diaphragm and stretching the diaphragm over the male tool as the pressure difference is applied. The diaphragm has a tensile modulus in the plane of the diaphragm which is greater than 5 MPa. Optionally a support membrane may be positioned on a opposite sides of the charge. In the case where a support membrane is used, then the diaphragm has a stiffness in the planeof the diaphragm which is higher than the stiffness of the support membrane in the plane of the support membrane.
摘要翻译：在制造复合部件期间模制电荷（12）的方法。该方法包括：将电荷和隔膜（4）放置在阳性工具上，电荷具有位于阳性工具（2）的顶部上方的第一部分（12a）和第二部分（12b，12c），第二部分项目到男主角的一边; 并且通过在隔膜上施加压力差并在施加压力差的同时将隔膜拉伸在阳性工具上，使电荷的第二部分逐渐变形为阳性工具的侧面。隔膜在隔膜的平面内具有大于5MPa的拉伸模量。任选地，支撑膜可以位于电荷的相对侧上。在使用支撑膜的情况下，隔膜在隔膜的平面中具有比支撑膜平面中的支撑膜的刚度高的刚度。

3. 发明申请

WO2009004362A3 COMPOSITE PANEL STIFFENER 审中-公开
标题翻译：复合面板增强剂
公开(公告)号：WO2009004362A3
公开(公告)日：2009-06-04
申请号：PCT/GB2008050480
申请日：2008-06-24
申请人： AIRBUS UK LTD , FLOOD JOHN
发明人： FLOOD JOHN
IPC分类号： B64C3/18 , G05B19/4097 , G05B19/4099
CPC分类号： B64C3/182 , B29C70/30 , B64C3/26 , G05B19/4099 , G05B2219/35044 , G05B2219/45204 , Y02T50/43 , Y02T50/433 , Y10T428/24174 , Y10T428/24628
摘要： A multi layer composite L-shaped stringer (2) for use in an aerospace structure comprises a foot(6) and a web (8) extending from an edge of the foot. A first surface (10) on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface (12) opposite the first surface. The web (8) has a third surface (14) and a fourth surface (16) at the same layer in the composite material as the first and third surfaces (10, 14), respectively. The geometry of the stringer (2) may vary along its length (L) so that as the first surface (10) is displaced towards the second surface (12), the fourth surface (16) is displaced towards the third surface (14). The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer (2) may be substantially constant for all cross-sections along a length of the stringer. The risk of causing, during fabrication of the stringer (2), 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.
摘要翻译：用于航空航天结构的多层复合L形纵梁（2）包括脚部（6）和从脚部边缘延伸的腹板（8）。脚上的第一表面（10）成形为邻接待加强的结构。该脚还具有与第一表面相对的第二表面（12）。网（8）在复合材料的同一层分别具有与第一和第三表面（10,14）相同的第三表面（14）和第四表面（16）。纵梁（2）的几何形状可沿其长度（L）变化，使得当第一表面（10）朝第二表面（12）移位时，第四表面（16）朝第三表面（14）移位，。对于沿纵梁长度的所有横截面而言，从足的远侧边缘到纵梁（2）的腹板的远侧边缘的展开宽度（DW）可以基本恒定。在桁条（2）的制造期间，通过这样的布置可以减少在桁条（2）的几何结构变化的区域中的复合材料层的不希望的褶皱，应力或拉伸的风险。

4. 发明申请

WO2009004364A3 IMPROVEMENTS IN ELONGATE COMPOSITE STRUCTURAL MEMBER 审中-公开
标题翻译：在ELENATE复合结构构件中的改进
公开(公告)号：WO2009004364A3
公开(公告)日：2009-05-22
申请号：PCT/GB2008050485
申请日：2008-06-24
申请人： AIRBUS UK LTD , WOOD ERIC STEPHEN
发明人： WOOD ERIC STEPHEN
IPC分类号： B64C3/18 , B64C3/26 , B64F5/00
CPC分类号： B64C3/182 , B29C70/30 , B29D99/0003 , B64C3/26 , Y02T50/43 , Y02T50/433 , Y10T428/24 , Y10T428/24174 , Y10T428/24628
摘要： A composite material elongate structural member (102), such as a spar or stringer, for use in an aerospace structure, comprises a web (108) having an angled portion, for example in the form of a chamfer (107), which joins a foot (106) of the member to the rest of the web. A first surface (110) on the foot is shaped to abut a structure (104) to be stiffened. The foot has a second surface (112) opposite the first surface. The web has a third surface (114) and a fourth surface (116) at the same layer in the composite material as the first and third surfaces, respectively. In the interposed portion there is a fifth surface (130) which joins the first and third surfaces. The geometry of the member may vary along its length (L) so that with increasing distance, the first surface is displaced towards the second surface,wherby the thickness between the first and second surface remains substantially constant, as the width of the fifth surface decreases.
摘要翻译：用于航空航天结构的复合材料细长结构构件（例如翼梁或纵梁）包括具有成角度的部分的腹板（108），例如呈倒角（107）的形式，其连接成员的脚（106）到网络的其余部分。脚上的第一表面（110）成形为邻接待硬化的结构（104）。脚具有与第一表面相对的第二表面（112）。纸幅分别具有与第一和第三表面在复合材料中相同层处的第三表面（114）和第四表面（116）。在插入部分中，存在第一和第三表面的第五表面（130）。构件的几何形状可以沿其长度（L）变化，使得随着距离的增加，第一表面朝向第二表面移位，由于第五表面的宽度减小，第一表面和第二表面之间的厚度保持基本上恒定。

5. 发明申请

WO2008012570A3 A STRINGER FOR AN AIRCRAFT WING AND A METHOD OF FORMING THEREOF 审中-公开
标题翻译：飞行员之星及其形成方法
公开(公告)号：WO2008012570A3
公开(公告)日：2009-02-26
申请号：PCT/GB2007050417
申请日：2007-07-19
申请人： AIRBUS UK LTD , CHILDS THOMAS
发明人： CHILDS THOMAS
IPC分类号： B64C3/18
CPC分类号： B64C3/182 , Y10T29/49622
摘要： The present invention relates to a stringer for an aircraft wing and a method of forming such a stringer in which the stringer is formed from a single piece of material and then machined to optimise the dimensions and weight of the stringer.
摘要翻译：本发明涉及一种用于飞机机翼的纵梁和一种形成这种纵梁的方法，其中纵梁由单件材料形成，然后机加工以优化纵梁的尺寸和重量。

6. 发明申请

WO2008029179A3 METHOD OF MANUFACTURING COMPOSITE MATERIAL BY GROWING OF A LAYER OF REINFORCEMENT AND RELATED APPARATUS 审中-公开
标题翻译：通过增强加强层和相关装置制造复合材料的方法
公开(公告)号：WO2008029179A3
公开(公告)日：2008-04-24
申请号：PCT/GB2007050510
申请日：2007-08-29
申请人： AIRBUS UK LTD , FARMER BENJAMIN LIONEL , JOHNS DANIEL MARK
发明人： FARMER BENJAMIN LIONEL , JOHNS DANIEL MARK
IPC分类号： B29C70/62
CPC分类号： C08J7/123 , B29C70/30 , B29C70/62 , B33Y10/00 , B82Y30/00 , C08J5/042
摘要： A method of manufacturing a composite material, the method comprising: growing a layer of reinforcement; and impregnating the layer with a matrix. The reinforcement layer may be formed by a chemical vapour deposition process. The method can be used as an additive layer manufacturing technique to form a component with a desired shape and physical characteristics, or can be used to form a thin sheet material.
摘要翻译：一种制造复合材料的方法，所述方法包括：生长增强层; 并用基体浸渍该层。加强层可以通过化学气相沉积工艺形成。该方法可以用作添加剂层制造技术以形成具有所需形状和物理特性的组分，或可用于形成薄片材料。

7. 发明申请

WO2009109771A2 LANDING GEAR WITH COMPOSITE LEAF SPRING 审中-公开
标题翻译：具有复合叶片弹簧的接地齿轮
公开(公告)号：WO2009109771A2
公开(公告)日：2009-09-11
申请号：PCT/GB2009050181
申请日：2009-02-24
申请人： AIRBUS UK LTD , THOMPSON ROBERT IAN
发明人： THOMPSON ROBERT IAN
CPC分类号： B64C25/62 , B64C25/12 , B64C25/14 , B64C25/18
摘要： An aircraft landing gear comprising: an arm mounted to a pivot and carrying one or more wheel assemblies; and a composite leaf spring which is coupled to the arm and arranged to provide a resilient biasing force which opposes rotation of the arm about the pivot. The arm can be made relatively stiff in comparison with the leaf spring, so that load is transferred directly into the pivot without a large amount ofbending of the leg. The leaf spring shock absorber typically has a reduced part count compared with a conventional oleo-pneumatic shock absorber. By forming the leaf spring from a composite material, its weight is significantly reduced in comparison with a conventional metal spring, making it suitable for use on a relatively large aircraft.
摘要翻译：一种飞机起落架，包括：安装到枢轴并承载一个或多个车轮组件的臂; 以及复合板簧，其联接到所述臂并布置成提供与所述臂围绕所述枢轴旋转的弹性偏压力。与板簧相比，臂可以制成相对刚性，使得负载直接转移到枢轴中，而不会有大量的弯曲。与常规的油气减震器相比，板簧减震器通常具有减少的部件数量。通过从复合材料形成板簧，与传统的金属弹簧相比，其重量显着降低，使其适用于较大的飞机。

8. 发明申请

WO2009106871A2 AERODYNAMIC STRUCTURE WITH NON-UNIFORMLY SPACED SHOCK BUMPS 审中-公开
标题翻译：具有非均匀空间冲击波的空气动力学结构
公开(公告)号：WO2009106871A2
公开(公告)日：2009-09-03
申请号：PCT/GB2009050152
申请日：2009-02-17
申请人： AIRBUS UK LTD , WOOD NORMAN
发明人： WOOD NORMAN
IPC分类号： B64C23/04
CPC分类号： B64C23/04 , B64C2003/148 , B64C2003/149 , Y02T50/12
摘要： An aerodynamic structure comprising a series of shock bumps extending from its surface. The shock bumps are distributed across the structure with a non-uniform spacing between the centres and/or edges of adjacent bumps. The non-uniform spacing between the bumps can be arranged to give maximum wave drag alleviation for the minimum number of bumps as a function of the shock strength across the span, leading to minimum wing weight penalties for a given amount of wave drag alleviation.
摘要翻译：包括从其表面延伸的一系列冲击凸起的空气动力学结构。冲击突起分布在结构上，在相邻凸块的中心和/或边缘之间具有不均匀的间隔。凸块之间的不均匀间距可以被布置成为跨越跨度的冲击强度的函数给出最小数量的凸起的最大波浪减轻，导致给定量的波浪减轻的最小翼重惩罚。

9. 发明申请

WO2009022167A2 METHOD AND APPARATUS FOR MANUFACTURING A COMPONENT FROM A COMPOSITE MATERIAL 审中-公开
标题翻译：用于从复合材料制造组分的方法和装置
公开(公告)号：WO2009022167A2
公开(公告)日：2009-02-19
申请号：PCT/GB2008050682
申请日：2008-08-08
申请人： AIRBUS UK LTD , FARMER BENJAMIN LIONEL , JOHNS DANIEL MARK
发明人： FARMER BENJAMIN LIONEL , JOHNS DANIEL MARK
IPC分类号： B29C70/12 , B29C70/28 , B29C70/88
CPC分类号： C08K3/04 , B29B9/14 , B29B13/00 , B29B13/08 , B29B2009/125 , B29C70/12 , B29C70/28 , B29C70/62 , B29C70/88 , B29K2307/04 , B29K2707/04 , B29L2009/00 , B33Y10/00 , B33Y30/00 , B33Y70/00 , B33Y80/00 , B82Y30/00 , C08K3/041 , C08K3/046 , Y10T428/24802
摘要： A method ofadditively manufacturing a component from a composite material, the composite material comprising a matrix and a plurality of reinforcement elements, the method comprising: forming a series oflayers of the composite material, each layer being formed on top of a previous layer; and applying an electromagnetic field to the composite material before the next layer is formed on top of it, the electromagnetic field causing at least some of the reinforcement elements to rotate.
摘要翻译：一种从复合材料添加成分的方法，所述复合材料包括基体和多个增强元件，所述方法包括：形成所述复合材料的一系列层，每层形成在先前层的顶部上; 以及在所述复合材料上形成下一层之前对所述复合材料施加电磁场，所述电磁场使至少一些所述增强元件旋转。

10. 发明申请

WO2009004363A2 ELONGATE COMPOSITE STRUCTURAL MEMBERS AND IMPROVEMENTS THEREIN 审中-公开
标题翻译：延伸复合结构构件及其改进
公开(公告)号：WO2009004363A2
公开(公告)日：2009-01-08
申请号：PCT/GB2008050481
申请日：2008-06-24
申请人： AIRBUS UK LTD , GRAY IAN L
发明人： GRAY IAN L
IPC分类号： B64C3/18
CPC分类号： B64C1/064 , B29C70/30 , B29K2105/246 , B64C1/065 , B64C3/182 , B64C3/185 , B64C3/187 , B64C2001/0072 , G06F17/5095 , Y02T50/43 , Y02T50/433
摘要： A composite material elongate structural member, such as a spar (102), for use in an aerospace structure, comprises a web (108) disposed between upper and lower flanges (104, 106). The web (108) may include a clockwise twist about an axis (164) parallel to the length L at a first portion towards the wing-root-end of the spar (102) and a counter-twist in the anticlockwise direction at a second portion towards the wing-tip-end of the spar (102). The geometry of the spar (102) may vary non-linearly along its length (L) so that the developed width of the spar as measured from a distal edge of the upper flange (104) via the web (108) to a distal edge of the lower flange (106) varies linearly with increasing distance along the length (L). The risk of causing, during fabrication of the spar (102), undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the member (102) varies non-linearly may be reduced by means of such an arrangement.
摘要翻译：用于航空航天结构的复合材料细长结构构件（例如翼梁（102））包括设置在上凸缘（104）和下凸缘（106）之间的腹板（108）。腹板（108）可以包括在朝向翼梁（102）的翼根端部的第一部分处与平行于长度L的轴线（164）顺时针扭转，并且在第二部分处以逆时针方向部分朝向翼梁102的翼尖端。翼梁102的几何形状可以沿着其长度L非线性地变化，使得从上凸缘104的远侧边缘经由腹板108测量的翼梁的展开宽度到远侧边缘下凸缘（106）的长度随着长度（L）的增加而线性变化。在制造翼梁102期间，在其中构件102的几何结构非线性变化的区域中复合材料层的不希望的褶皱，应力或拉伸的风险可以通过这样的布置来减小。

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