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公开(公告)号：US20110211968A1
公开(公告)日：2011-09-01
申请号：US12959959
申请日：2010-12-03
IPC分类号： B64C27/473 , B21D53/78
CPC分类号： B64C27/463 , B64C27/473 , B64C2027/4736 , Y10T29/49332 , Y10T29/49336 , Y10T29/49337
摘要： A rotor blade for a rotary-wing aircraft includes a core member having a first end that extends to a second end, and a spar member positioned about the core member. The spar member includes a first end section that extends to a second end section. A tip core assembly is mounted at the second end section of the spar member. The tip core assembly is formed from a honeycombed material. The rotor blade also includes a rotor blade skin mounted about the spar member and the tip core assembly.
摘要翻译： 用于旋转翼飞行器的转子叶片包括具有延伸到第二端的第一端的芯构件和围绕芯构件定位的翼梁构件。 翼梁构件包括延伸到第二端部的第一端部。 尖端芯组件安装在翼梁构件的第二端部。 尖端芯组件由蜂窝状材料形成。 转子叶片还包括围绕翼梁构件和尖端芯组件安装的转子叶片皮肤。
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公开(公告)号：US20090148301A1
公开(公告)日：2009-06-11
申请号：US12062807
申请日：2008-04-04
IPC分类号： B64C27/473
CPC分类号： B64C27/463 , B64C27/473 , B64C2027/4736 , Y10T29/49337
摘要： A main rotor blade assembly includes a tip cap removably mountable to an outboard end section of a forward tip spar section and an aft tip spar section.
摘要翻译： 主转子叶片组件包括可拆卸地安装到前尖端翼梁部分和尾翼翼梁部分的外侧端部的末端盖。
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公开(公告)号：US08858183B2
公开(公告)日：2014-10-14
申请号：US12959959
申请日：2010-12-03
IPC分类号： B64C27/473 , B64C27/46
CPC分类号： B64C27/463 , B64C27/473 , B64C2027/4736 , Y10T29/49332 , Y10T29/49336 , Y10T29/49337
摘要： A rotor blade for a rotary-wing aircraft includes a core member having a first end that extends to a second end, and a spar member positioned about the core member. The spar member includes a first end section that extends to a second end section. A tip core assembly is mounted at the second end section of the spar member. The tip core assembly is formed from a honeycombed material. The rotor blade also includes a rotor blade skin mounted about the spar member and the tip core assembly.
摘要翻译： 用于旋转翼飞行器的转子叶片包括具有延伸到第二端的第一端的芯构件和围绕芯构件定位的翼梁构件。 翼梁构件包括延伸到第二端部的第一端部。 尖端芯组件安装在翼梁构件的第二端部。 尖端芯组件由蜂窝状材料形成。 转子叶片还包括围绕翼梁构件和尖端芯组件安装的转子叶片皮肤。
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公开(公告)号：US5836062A
公开(公告)日：1998-11-17
申请号：US843527
申请日：1997-04-16
CPC分类号： B29D99/0028 , B29L2031/082 , Y10T29/37 , Y10T29/49332 , Y10T29/53026 , Y10T29/53539
摘要： An apparatus for assembling a helicopter main rotor blade subassembly which includes a lower airfoil skin, a core, an upper airfoil skin, and a spar assembly having a tip end and a root end, the apparatus including a lower assembly including a base having a contoured upper airfoil nest, wherein the contoured upper airfoil nest has a root end and a tip end, at least two guide ramps disposed proximal to the contoured upper airfoil nest, wherein at least one of the guide ramps is disposed proximal to the root end and at least one of the guide ramps is disposed proximal to the tip end, and a plurality of leading-edge pusher cams disposed proximal to the contoured upper airfoil nest. An upper assembly configured for mating with the lower assembly is provided, and includes a support structure and a flexible impervious membrane supported by the support structure, wherein the flexible impervious membrane and the contoured upper airfoil nest define a molding cavity therebetween upon mating of the upper assembly to the lower assembly.
摘要翻译： 一种用于组装直升机主转子叶片子组件的装置，其包括下翼面皮，芯，上翼面皮和具有尖端和根端的翼梁组件，该装置包括下组件，下组件包括具有轮廓的基座 上部翼型套，其中所述成型的上翼型座具有根端和尖端，至少两个设置在所述轮廓上翼型座附近的引导斜面，其中所述引导斜面中的至少一个布置在所述根端附近， 至少一个导向斜面靠近尖端设置，并且多个前缘推动器凸轮设置在近似于轮廓的上翼型嵌套上。 提供了一种构造成与下部组件配合的上部组件，并且包括支撑结构和由支撑结构支撑的柔性不透水膜，其中柔性不透水膜和成型上部翼型套在上部配合时在其间限定模制腔 组装到下部组件。
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公开(公告)号：US07758312B2
公开(公告)日：2010-07-20
申请号：US12062822
申请日：2008-04-04
IPC分类号： B64C27/473
CPC分类号： B64C27/463 , B64C27/473 , B64C2027/4736 , Y10T29/49337
摘要： A main rotor blade assembly includes a tip spar which defines a tip spar non-straight form, an upper blade skin which defines an upper blade skin non-straight form adjacent to the tip spar non-straight form and a lower blade skin which defines a lower blade skin non-straight form adjacent to the tip spar non-straight form.
摘要翻译： 主转子叶片组件包括限定尖端翼片非直线形式的尖端翼片，限定与尖端翼梁非直线形式相邻的上部叶片皮肤非直线形式的上部叶片皮肤以及限定一个 较低的叶片皮肤非直线形，与尖端翼梁非直线形相邻。
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公开(公告)号：US20090269205A1
公开(公告)日：2009-10-29
申请号：US12110312
申请日：2008-04-26
CPC分类号： B64C27/463 , B64C27/473 , B64C2027/4736
摘要： A main rotor blade assembly includes a main spar with an integral cuff. The main spar is directly to a rotor hub assembly through the integral cuff.
摘要翻译： 主转子叶片组件包括具有整体套筒的主翼梁。 主翼梁通过整体式袖带直接连接到转子轮毂组件。
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公开(公告)号：US20090148303A1
公开(公告)日：2009-06-11
申请号：US12062822
申请日：2008-04-04
IPC分类号： B64C27/473
CPC分类号： B64C27/463 , B64C27/473 , B64C2027/4736 , Y10T29/49337
摘要： A main rotor blade assembly includes a tip spar which defines a tip spar non-straight form, an upper blade skin which defines an upper blade skin non-straight form adjacent to the tip spar non-straight form and a lower blade skin which defines a lower blade skin non-straight form adjacent to the tip spar non-straight form.
摘要翻译： 主转子叶片组件包括限定尖端翼片非直线形式的尖端翼片，限定与尖端翼梁非直线形式相邻的上部叶片皮肤非直线形式的上部叶片皮肤以及限定一个 较低的叶片皮肤非直线形，与尖端翼梁非直线形相邻。
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8.发明授权Apparatus for installing a leading-edge sheath onto a helicopter main rotor blade subassembly 失效用于将前缘护套安装在直升机主转子叶片子组件上的装置
公开(公告)号：US5862576A
公开(公告)日：1999-01-26
申请号：US838214
申请日：1997-04-16
CPC分类号： B64F5/0009 , B29D99/0028 , B29L2031/082 , Y10T29/37 , Y10T29/49332 , Y10T29/53026 , Y10T29/53539
摘要： An apparatus for installing a leading-edge sheath onto a helicopter main rotor blade subassembly, including a lower assembly having a leading-edge sheath contour nest configured for supporting the leading-edge sheath, opposed carriage members connected to a base, wherein each of the opposed carriage members supports a plurality of suction cups and is capable of synchronized translational movement relative to the leading-edge sheath contour nest between an engaged position wherein the plurality of suction cups are in abutting engagement with the leading-edge sheath, and a disengaged position where the plurality of suction cups are disengaged from the leading-edge sheath. A vacuum system is connected in fluid communication with the plurality of suction cups and is capable of providing vacuum pressure to the plurality of suction cups, whereby the vacuum pressure generates suction forces between the plurality of suction cups and the leading-edge sheath when the opposed carriage members are in the engaged position. An upper assembly is disposed in combination with the lower assembly, and comprises a plurality of stanchions connected to the base of the lower assembly, and a contour clamp connected to each of the stanchions capable of translational movement relative to the leading-edge sheath contour nest. The contour clamps are configured for supporting the helicopter main rotor blade subassembly and function to facilitate insertion of the helicopter main rotor blade subassembly into the leading-edge sheath.
摘要翻译： 一种用于将前缘护套安装到直升机主转子叶片子组件上的装置，包括具有构造成用于支撑前缘护套的前缘护套轮廓座的下部组件，连接到底座的相对的支架构件， 相对的托架构件支撑多个吸盘，并且能够在接合位置之间相对于前缘护套轮廓座同步平移运动，其中多个吸盘与前缘护套邻接接合，并且脱离位置 其中多个吸盘与前缘护套分离。 真空系统与多个吸盘流体连通地连接并且能够向多个吸盘提供真空压力，由此当相对的位置处于相对的位置时，真空压力在多个吸盘和前缘护套之间产生吸力 支架成员处于订立状态。 上部组件与下部组件组合设置，并且包括连接到下部组件的底部的多个支柱，以及连接到每个支柱的轮廓夹具，其能够相对于前缘护套轮廓嵌套平移运动 。 轮廓夹具被配置为支撑直升机主转子叶片子组件，并且具有促进直升机主转子叶片子组件插入前缘护套中的功能。
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公开(公告)号：US5832605A
公开(公告)日：1998-11-10
申请号：US838295
申请日：1997-04-16
CPC分类号： B64F5/0009 , B29C70/38 , B29D99/0028 , B29L2031/082 , Y10T29/37 , Y10T29/49332 , Y10T29/49334
摘要： A method for fabricating a helicopter blade subassembly includes the steps of providing a blade compaction apparatus having a lower assembly configured for mating with an upper assembly. The lower assembly includes a base having a contoured upper airfoil nest with at least two guide ramps and a plurality of leading-edge pusher cams disposed proximal thereto. The upper assembly includes a support structure supporting a flexible impervious membrane, wherein the flexible impervious membrane and the contoured upper airfoil nest define a molding cavity therebetween upon mating of the upper assembly to the lower assembly. The method further includes disposing the upper airfoil skin and the core in combination with the contoured upper airfoil nest, and then connecting a tip end support insert and a root end support insert in combination with the spar assembly, wherein each of the support inserts include guide members. The spar assembly is located in chordwise alignment in the contoured upper airfoil nest by driving the guide members into conics in the guide ramps and driving the spar assembly into a core conic with the leading-edge pusher cams. The lower airfoil skin is then disposed in combination with the core and the spar to form the helicopter blade subassembly, and then the upper assembly is mated to the lower assembly. The air within the molding cavity is then evacuated such that evacuating the air causes the flexible impervious membrane to apply compaction forces to the helicopter blade subassembly.
摘要翻译： 一种用于制造直升机叶片子组件的方法包括以下步骤：提供具有下部组件的叶片压实装置，所述下部组件被配置为与上部组件配合。 下部组件包括具有具有至少两个引导斜面的成形上部翼型嵌套的基座和在其附近设置的多个前缘推动器凸轮。 上部组件包括支撑柔性不透水膜的支撑结构，其中柔性不透水膜和成型上部翼型嵌套在上部组件与下部组件配合时在其间限定模制腔。 该方法还包括将上翼面外壳和芯体与成型的上翼型嵌套组合设置，然后将顶端支撑插入件和根端支撑插入件与翼梁组合件组合连接，其中每个支撑插入件包括引导件 会员 翼梁组件通过在引导斜坡中驱动引导构件成锥形并且将翼梁组件驱动到具有前缘推动器凸轮的芯锥形中，位于成型的上翼型嵌套中的弦向对准。 然后将下部翼型皮肤与芯和翼梁组合设置以形成直升机叶片子组件，然后将上部组件配合到下部组件。 然后将成型腔内的空气抽真空，使得排空空气使柔性防渗膜向直升机叶片组件施加压实力。
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公开(公告)号：US5570631A
公开(公告)日：1996-11-05
申请号：US566758
申请日：1995-12-04
申请人： Kevin P. Leahy , Corey D. Jones
发明人： Kevin P. Leahy , Corey D. Jones
IPC分类号： B64C27/46 , B29C70/44 , B29C70/78 , B29C70/86 , B29D99/00 , B64C27/473 , B64F5/00 , B30B5/02
CPC分类号： B29D99/0028 , B29C70/446 , B29C70/78 , B29C70/86 , B64C27/473 , B29L2031/082 , B64C2027/4736 , Y10T29/37 , Y10T29/49332 , Y10T29/53026 , Y10T29/53539 , Y10T29/5397
摘要： Apparatus and methods for fabricating a helicopter main rotor blade include a compaction fixture for assembling and compacting blade subassembly components and a sheath spreading/insertion apparatus for spreading and inserting a leading-edge sheath onto the blade subassembly during the compaction process. The compaction fixture includes a lower assembly having a contoured upper airfoil nest mounted in combination with a support structure and an upper assembly having a pressure bag affixed in sealed combination to a contoured backplate affixed in combination to a structural support truss. The contoured upper airfoil nest includes a plurality of tooling pins for locating an upper composite skin in aligned combination on the contoured upper airfoil nest and a plurality of pusher pins for chordwise alignment of a spar assembly in the contoured upper airfoil nest. Spar stanchions affixed to the support structure provide spanwise alignment of the spar assembly in the contoured upper airfoil nest. With the upper and lower assemblies in locked combination, the pressure bag is pressurized to compact the assembled blade subassembly components. The sheath spreading/insertion apparatus includes a movable stanchion, upper and lower elongate carriage members mounted in synchronized movable combination with the stanchion, and a row of suction cups mounted in combination with each carriage member. Pneumatic cylinders are mounted in combination with the stanchion and the respective carriage members.
摘要翻译： 用于制造直升机主转子叶片的装置和方法包括用于组装和压实叶片子组件部件的压实夹具和用于在压实过程期间将前缘护套铺展并插入到叶片子组件上的护套扩展/插入装置。 压实夹具包括下部组件，其具有与支撑结构组合安装的轮廓上部翼型嵌套，以及具有与密封组合固定到与结构支撑桁架组合的轮廓背板的压力袋的上部组件。 成型的上翼型嵌套包括多个工具销，用于将上复合材料表层以对准的组合定位在成型的上翼型嵌套上，以及多个推杆，用于在轮廓上的翼型嵌套中翼弦对准。 固定到支撑结构的翼梁支柱提供了翼型组件在成型的上翼型嵌套中的翼展对准。 通过将上部和下部组件锁定组合，压力袋被加压以压缩组装的叶片子组件部件。 护套扩展/插入装置包括可移动支柱，与支柱同步移动的组合安装的上部和下部细长托架构件以及与每个托架构件组合安装的一排吸盘。 气动缸与支柱和相应的支架构件组合安装。
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