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公开(公告)号：US20120156050A1
公开(公告)日：2012-06-21
申请号：US13283461
申请日：2011-10-27
申请人： Robert Owen White
发明人： Robert Owen White
IPC分类号： B64C27/473 , B23P6/00
CPC分类号： B64C27/473 , B64C27/023 , B64C27/18 , B64C27/26 , Y10T29/49318
摘要： A rotor blade having a detachable fairing is disclosed. The rotor blade includes leading and trailing edge fairings secured to the blade spar and one or more control lines extending between of the fairings and the blade spar. A detachable fairing extends from one or both of the leading and trailing edge fairings toward one of the distal and proximal ends of the blade spar. The detachable fairing and blade spar form an airfoil contour. The detachable fairing may secure to a tip jet attachment fitting at a distal end of the blade spar. A mounting structure including upper and lower plates may secure near a proximal end of the blade spar and the detachable fairing may secure to both the upper and lower plates to form all or part of an airfoil contour. The mounting structure may include a spherical seat engaging a spherical surface of a hub shroud.
摘要翻译： 公开了一种具有可拆卸整流罩的转子叶片。 转子叶片包括固定到叶片翼梁的前缘和后缘整流罩以及在整流罩和叶片翼梁之间延伸的一个或多个控制线。 可拆卸的整流罩从前缘和后缘整流罩中的一个或两个朝向叶片翼梁的远端和近端延伸。 可拆卸的整流罩和叶片翼梁形成翼型轮廓。 可拆卸的整流罩可以固定到叶片翼梁的远端处的尖端喷射器附件配件。 包括上板和下板的安装结构可以固定在叶片翼梁的近端附近，并且可拆卸的整流罩可以固定到上板和下板两者以形成翼型轮廓的全部或一部分。 安装结构可以包括接合轮毂罩的球形表面的球形座。
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公开(公告)号：US20120175461A1
公开(公告)日：2012-07-12
申请号：US13427696
申请日：2012-03-22
CPC分类号： B64C27/48 , B64C7/00 , B64C27/025 , B64C27/32
摘要： A fairing system may be assembled about a rotor of a rotorcraft to present an aerodynamically quasi-static region that rotates in an airstream, as well as certain extensions that sweep through the airstream as the rotor hub passes through the air. A spherical interface between the extensions on the rotor hub fairing and the base or root portion of each blade fairing provides three degrees of freedom permitting lead-lag, flapping, and blade pitch pivoting in the blade, while still maintaining an aerodynamic profile that will minimize drag.
摘要翻译： 可以围绕旋翼航空器的转子组装整流罩系统，以呈现在气流中旋转的空气动力学准静态区域，以及当转子毂通过空气时扫过气流的某些延伸部分。 转子轮毂整流罩上的延伸部分与每个叶片整流罩的基部或根部之间的球形接口提供了三个自由度，允许在叶片中进行超前滞后，振动和叶片俯仰摆动，同时仍保持空气动力学特性将使 拖动。
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公开(公告)号：US09079659B2
公开(公告)日：2015-07-14
申请号：US13427696
申请日：2012-03-22
CPC分类号： B64C27/48 , B64C7/00 , B64C27/025 , B64C27/32
摘要： A fairing system may be assembled about a rotor of a rotorcraft to present an aerodynamically quasi-static region that rotates in an airstream, as well as certain extensions that sweep through the airstream as the rotor hub passes through the air. A spherical interface between the extensions on the rotor hub fairing and the base or root portion of each blade fairing provides three degrees of freedom permitting lead-lag, flapping, and blade pitch pivoting in the blade, while still maintaining an aerodynamic profile that will minimize drag.
摘要翻译： 可以围绕旋翼航空器的转子组装整流罩系统，以呈现在气流中旋转的空气动力学准静态区域，以及当转子毂经过空气时扫过气流的某些延伸部分。 转子轮毂整流罩上的延伸部分与每个叶片整流罩的基部或根部之间的球形接口提供了三个自由度，允许在叶片中进行超前滞后，振动和叶片俯仰摆动，同时仍保持空气动力学特性将使 拖动。
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公开(公告)号：US08894791B1
公开(公告)日：2014-11-25
申请号：US13373439
申请日：2011-11-14
申请人： Robert Owen White
发明人： Robert Owen White
IPC分类号： B29C70/00
CPC分类号： B64C27/473 , B29C70/446 , B29L2031/082 , B64C27/18 , B64C2027/4736
摘要： Apparatus and methods are disclosed for manufacture of a composite structure, such as a composite rotor blade spar or composite rotor blade. A first mold may define a first mold surface and a second mold may include a rigid layer and a heated layer secured to the rigid layer and defining a second mold surface. A plurality of heating elements embedded in the second mold may be activated according to different temperature progressions to cure portions of the uncured composite rotor blade positioned coextensive therewith. In some embodiments, the second mold defines a root portion and first and second branch portions. A shear web placed between the branch portions may be bonded to a blade skin positioned within the mold. The rotor blade may include a rotor blade spar having leading and trailing edge fairings secured thereto or the blade spar may define a complete airfoil contour.
摘要翻译： 公开了用于制造诸如复合转子叶片翼片或复合转子叶片的复合结构的装置和方法。 第一模具可以限定第一模具表面，并且第二模具可以包括固定到刚性层并限定第二模具表面的刚性层和加热层。 嵌入在第二模具中的多个加热元件可以根据不同的温度进行而被激活以固化与其共同延伸的未固化的复合转子叶片的部分。 在一些实施例中，第二模具限定根部部分和第一和第二分支部分。 放置在分支部分之间的剪切网可以结合到位于模具内的刀片皮肤。 转子叶片可以包括具有固定到其上的前缘和后缘整流罩的转子叶片翼梁，或者叶片翼梁可以限定完整的翼型轮廓。
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公开(公告)号：US09056674B2
公开(公告)日：2015-06-16
申请号：US13283461
申请日：2011-10-27
申请人： Robert Owen White
发明人： Robert Owen White
IPC分类号： B64C11/06 , B64C11/24 , B64C15/14 , B64C27/473 , B64C27/82 , B64C27/18 , B64C27/22 , B64C27/26 , B64C11/20
CPC分类号： B64C27/473 , B64C27/023 , B64C27/18 , B64C27/26 , Y10T29/49318
摘要： A rotor blade having a detachable fairing is disclosed. The rotor blade includes leading and trailing edge fairings secured to the blade spar and one or more control lines extending between of the fairings and the blade spar. A detachable fairing extends from one or both of the leading and trailing edge fairings toward one of the distal and proximal ends of the blade spar. The detachable fairing and blade spar form an airfoil contour. The detachable fairing may secure to a tip jet attachment fitting at a distal end of the blade spar. A mounting structure including upper and lower plates may secure near a proximal end of the blade spar and the detachable fairing may secure to both the upper and lower plates to form all or part of an airfoil contour. The mounting structure may include a spherical seat engaging a spherical surface of a hub shroud.
摘要翻译： 公开了一种具有可拆卸整流罩的转子叶片。 转子叶片包括固定到叶片翼梁的前缘和后缘整流罩以及在整流罩和叶片翼梁之间延伸的一个或多个控制线。 可拆卸的整流罩从前缘和后缘整流罩中的一个或两个朝向叶片翼梁的远端和近端延伸。 可拆卸的整流罩和叶片翼梁形成翼型轮廓。 可拆卸的整流罩可以固定到叶片翼梁的远端处的尖端喷射器附件配件。 包括上板和下板的安装结构可以固定在叶片翼梁的近端附近，并且可拆卸的整流罩可以固定到上板和下板两者以形成翼型轮廓的全部或一部分。 安装结构可以包括接合轮毂罩的球形表面的球形座。
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公开(公告)号：US20120111997A1
公开(公告)日：2012-05-10
申请号：US13349201
申请日：2012-01-12
申请人： Robert Owen White
发明人： Robert Owen White
摘要： An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. The rudder may mount to a first vertical stabilizer extending between the horizontal stabilizers. The horizontal stabilizers may be secured to second and third vertical stabilizers to form a duct having the rudder positioned within the duct. Additional rudders may mount to the second and third vertical stabilizers.
摘要翻译： 公开了一种具有安装在机身上的发动机和螺旋桨的飞机。 一个尾翼安装在飞行器上，并且包括第一和第二水平稳定器，该水平稳定器在水平稳定器处分开的距离大于螺旋桨的流管的直径。 方向舵在水平稳定器之间延伸并且位于螺旋桨的流管内。 方向舵可以安装到在水平稳定器之间延伸的第一垂直稳定器。 水平稳定器可以固定到第二和第三垂直稳定器以形成具有舵定位在管道内的管道。 额外的方向舵可以安装到第二和第三垂直稳定器。
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公开(公告)号：US09499253B1
公开(公告)日：2016-11-22
申请号：US13373440
申请日：2011-11-14
申请人： Robert Owen White
发明人： Robert Owen White
CPC分类号： B64C11/24 , B32B1/00 , B64C11/26 , B64C13/12 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/32 , B64C27/48 , B64C27/56 , B64C27/72 , B64C27/82 , B64C2027/4736 , B64D31/04 , G06F17/40 , G06F19/00 , Y02T50/44 , Y10T74/20612
摘要： Apparatus and methods are disclosed for designing and manufacturing a composite structure, such as a composite rotor blade spar or composite rotor blade. A first mold may define a first mold surface and a second mold may include a rigid layer and a heated layer secured to the rigid layer and defining a second mold surface. A plurality of heating elements embedded in the second mold may be activated according to different temperature progressions to cure portions of the uncured composite rotor blade positioned coextensive therewith. In some embodiments, the second mold defines a root portion and first and second branch portions. A shear web may be placed between the branch portions during curing. The blade spar may define a complete airfoil contour or have fairings secured thereto having lines extending therethrough to a tip jet. A tip jet mounting structure and blade root attachment apparatus are also disclosed.
摘要翻译： 公开了用于设计和制造诸如复合转子叶片翼片或复合转子叶片的复合结构的装置和方法。 第一模具可以限定第一模具表面，并且第二模具可以包括固定到刚性层并限定第二模具表面的刚性层和加热层。 嵌入在第二模具中的多个加热元件可以根据不同的温度进行而被激活以固化与其共同延伸的未固化的复合转子叶片的部分。 在一些实施例中，第二模具限定根部部分和第一和第二分支部分。 在固化期间，可以在分支部分之间设置剪切网。 叶片翼梁可以限定一个完整的翼型轮廓，或者具有固定到其上的整流罩，其中有线穿过其延伸到尖端射流。 还公开了尖端喷射器安装结构和叶片根部附着装置。
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公开(公告)号：US09144944B1
公开(公告)日：2015-09-29
申请号：US13317749
申请日：2011-10-27
申请人： Robert Owen White
发明人： Robert Owen White
IPC分类号： B29C70/34 , B64C27/473 , B29C70/46 , B29C33/02 , B29C35/02
CPC分类号： B29C70/345 , B29C33/02 , B29C35/0288 , B29C35/16 , B29C37/0064 , B29C70/462 , B29C2035/0211 , B29L2031/082 , B64C27/473 , B64C2027/4736 , B64F5/10
摘要： Apparatus and methods are disclosed for manufacture of a composite rotor blade spar having non-uniform wall thickness. Tooling for manufacturing include a first mold defining a first mold surface and a second mold comprising a rigid layer and a heated layer secured to the rigid layer and defining a second mold surface. A plurality of heating elements embedded in the second mold are activated according to a plurality of different temperature progressions effective to cure portions of the uncured composite blade spar positioned between the first and second mold surfaces coextensive with each heating element of the plurality of heating elements. In some embodiments, the second mold defines a root portion and first and second branch portions. A shear web is placed between the first and second branch portions and is bonded to a blade spar skin surrounding the second mold during curing of the blade spar skin.
摘要翻译： 公开了用于制造具有不均匀壁厚的复合转子叶片翼梁的装置和方法。 用于制造的模具包括限定第一模具表面的第一模具和包括刚性层和固定到刚性层并限定第二模具表面的加热层的第二模具。 嵌入在第二模具中的多个加热元件根据多个不同的温度进行而被激活，这些升温有效地固化位于与多个加热元件的每个加热元件共同延伸的第一和第二模具表面之间的未固化复合叶片翼梁的部分。 在一些实施例中，第二模具限定根部部分和第一和第二分支部分。 剪切织物放置在第一和第二分支部分之间，并且在叶片翼片皮肤固化期间结合到围绕第二模具的叶片皮肤皮肤。
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公开(公告)号：US09139297B1
公开(公告)日：2015-09-22
申请号：US13317750
申请日：2011-10-27
申请人： Robert Owen White
发明人： Robert Owen White
IPC分类号： B64C11/24 , B64C27/473 , B21D53/78 , B21K3/00 , B21K3/04 , B64C11/06 , B64C27/18 , B64C11/20 , B64C27/82 , B64C27/22 , B64C27/24 , B64C27/26 , B64C15/14
CPC分类号： B64C27/18 , B21D53/78 , B21K3/00 , B21K3/04 , B64C11/06 , B64C11/20 , B64C11/24 , B64C15/14 , B64C27/22 , B64C27/24 , B64C27/26 , B64C27/473 , B64C27/56 , B64C27/82 , B64C2027/8245 , B64D31/04 , Y10T74/20612
摘要： A rotor blade having conduits for supporting control lines is disclosed. The control lines extend from a rotor hub to a tip jet mounted near a distal end of the rotor blade. The conduits mount within leading and trailing edge fairings mounted to a blade spar. The conduits may be supported by bulkheads secured at discrete locations along the blade spar and secured to the leading and trailing edge fairings. The conduits may also be secured to support webs secured to the leading or trailing edge fairing and extending longitudinally therealong. The conduit may have a tapered inner surface and a tapered fitting may secure to the control line to engage the tapered inner surface.
摘要翻译： 公开了一种具有用于支撑控制线的导管的转子叶片。 控制线从转子毂延伸到安装在转子叶片远端附近的尖端喷射器。 导管安装在安装在叶片翼梁上的前缘和后缘整流罩内。 导管可以被固定在沿着叶片翼梁的离散位置处并固定到前缘和后缘整流罩上的隔板支撑。 导管还可以固定到固定到前缘或后缘整流罩上并沿其纵向延伸的支撑腹板。 导管可以具有锥形内表面，并且锥形配件可以固定到控制线以接合锥形内表面。
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公开(公告)号：US09120564B1
公开(公告)日：2015-09-01
申请号：US13199720
申请日：2011-09-07
申请人： Robert Owen White
发明人： Robert Owen White
IPC分类号： B64C11/24 , B64C15/14 , B64C27/473 , B64C27/18 , B64C27/82 , B64C11/20 , B64C11/06 , B64C27/22 , B64C27/26
CPC分类号： B64C27/18 , B64C11/06 , B64C11/20 , B64C11/24 , B64C15/14 , B64C27/22 , B64C27/26 , B64C27/473 , B64C27/82 , B64C2027/8245
摘要： A rotor blade assembly is disclosed including a blade spar having a duct extending therethrough and having upper and lower surfaces. A mounting structure is secured to the blade spar and defines a fluid path in fluid communication with the duct. The mounting structure likewise has upper and lower surfaces. A tip jet is secured to the mounting structure in fluid communication with the fluid path. The blade spar and mounting structure abut one another at a joint and the upper surfaces of the blade spar and mounting structure lie on a common airfoil contour extending across the joint. The lower surfaces of the blade spar and mounting structure also lie on the common airfoil contour. One or both of the blade and mounting structure include a composite material. The mounting structure may include two portions secured to one another having a distal portion of the blade spar captured therebetween.
摘要翻译： 公开了一种转子叶片组件，其包括具有延伸穿过其中且具有上表面和下表面的管道的叶片翼梁。 安装结构被固定到叶片翼梁并且限定与管道流体连通的流体路径。 安装结构同样具有上表面和下表面。 尖端喷射器固定到与流体路径流体连通的安装结构。 叶片翼梁和安装结构在接头处彼此邻接，并且叶片翼梁和安装结构的上表面位于延伸穿过接头的共同翼型轮廓上。 叶片翼梁和安装结构的下表面也位于公共翼型轮廓上。 叶片和安装结构中的一个或两个包括复合材料。 安装结构可以包括彼此固定的两个部分，其中夹在其间的叶片翼梁的远端部分。
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