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    Lightweight propeller blade with improved retention capacity
    5.
    发明授权
    Lightweight propeller blade with improved retention capacity 有权

    公开(公告)号：US09849969B2

    公开(公告)日：2017-12-26

    申请号：US14663941

    申请日：2015-03-20

    申请人： Hamilton Sundstrand Corporation

    发明人： David P. Nagle ,  Stephen L. Smith

    IPC分类号： B64C11/04 ,  B64C11/26 ,  B64C11/06 ,  B64C27/473

    CPC分类号： B64C11/26 ,  B64C11/06 ,  B64C2027/4736

    摘要： A propeller blade assembly includes a spar extending along a propeller blade axis and an outer sleeve surrounding the spar portion at a root end of the rotor blade assembly. The spar is adhesively bonded to the outer sleeve at an interface portion. A spar maximum diameter along the interface portion is larger than an outer sleeve minimum diameter along the interface portion. A method of assembling a propeller blade includes installing an outer sleeve over a spar at a root end of the spar, the spar a not fully cured composite component, and urging the spar into compressive conformance with the outer sleeve at an interface portion of the propeller blade assembly. A spar maximum diameter along the interface portion is larger than an outer sleeve minimum diameter along the interface portion. The spar is cured thereby adhesively bonding the spar to the outer sleeve at the interface portion.

    DEPLOYABLE PROPELLER
    8.
    发明申请
    DEPLOYABLE PROPELLER 有权
    可配螺旋桨

    公开(公告)号：US20160347441A1

    公开(公告)日：2016-12-01

    申请号：US14727045

    申请日：2015-06-01

    申请人： Northrop Grumman Systems Corporation

    发明人： Barnaby S. WAINFAN ,  Stephen D. JOHNSON

    IPC分类号： B64C11/28 ,  B64C11/04

    CPC分类号： B64C11/28 ,  B64C11/04 ,  B64C27/46 ,  B64C27/50 ,  B64C2027/4736

    摘要： A propeller which can be folded and stowed in compact form and then deployed for powered flight is disclosed. The deployable propeller has two or more blades, and each blade is composed of multiple segments which are disengaged when stowed and then interlock when deployed to form an efficient blade. The segmented deployable propeller retains all effective area to the spinner radius.

    摘要翻译： 公开了一种螺旋桨，其可以以紧凑形式被折叠和收起，然后部署用于动力飞行。 可部署的螺旋桨具有两个或更多个叶片，并且每个叶片由多个段组成，当收起时它们分离，然后在展开时互锁以形成有效的叶片。 分段可部署的螺旋桨将所有有效区域保留到旋转半径。

    Composite rotor blade for a reaction drive rotorcraft
    9.
    发明授权
    Composite rotor blade for a reaction drive rotorcraft 有权
    复合转子叶片用于反作用驱动旋翼飞机

    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

    IPC分类号： B64C11/24 ,  B64C11/26 ,  B64C27/82 ,  B32B1/00 ,  G06F17/40 ,  G06F19/00

    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。

    COMPOSITE YOKE FITTING FOR BEARING ATTACHMENT TO ROTORCRAFT BLADE
    10.
    发明申请
    COMPOSITE YOKE FITTING FOR BEARING ATTACHMENT TO ROTORCRAFT BLADE 审中-公开
    用于轴承连接到旋转叶片的复合轴承配件

    公开(公告)号：US20160280367A1

    公开(公告)日：2016-09-29

    申请号：US14669977

    申请日：2015-03-26

    申请人： Bell Helicopter Textron Inc.

    发明人： Andrew Haldeman ,  Frank Bradley Stamps ,  Drew Sutton

    IPC分类号： B64C27/46

    CPC分类号： B64C27/46 ,  B64C27/48 ,  B64C2027/4736

    摘要： A rotor blade assembly includes a rotor blade comprising an inboard end and an outboard end. A composite yoke fitting made from a composite material is attached to the rotor blade. The composite yoke fitting includes an outboard portion inserted into the inboard end of the rotor blade, an inboard portion, and a flexure region about which the rotor blade is configured to flex. The inboard portion and the flexure region are outside the rotor blade.

    摘要翻译： 转子叶片组件包括转子叶片，其包括内侧端部和外侧端部。 由复合材料制成的复合轭配件安装在转子叶片上。 复合轭配件包括插入转子叶片的内侧端部的外侧部分，内侧部分和弯曲区域，转子叶片围绕弯曲区域弯曲。 内侧部分和挠曲区域在转子叶片的外侧。