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    STRUCTURALLY BIASED PROPROTOR BLADE ASSEMBLY
    1.
    发明公开
    STRUCTURALLY BIASED PROPROTOR BLADE ASSEMBLY 有权
    结构偏置的PROPROTOR BLADE组件

    公开(公告)号：EP3246247A1

    公开(公告)日：2017-11-22

    申请号：EP16174779.5

    申请日：2016-06-16

    Applicant: Bell Helicopter Textron Inc.

    Inventor： FOSKEY, Christopher ,  BURNETT, Michael ,  BOSWORTH, Jeffrey ,  PAULSON, Jared ,  McINTYRE, Joel ,  OLDROYD, Paul K.

    IPC: B64C11/24 ,  B64C11/26 ,  B64C27/473 ,  B64C29/00

    CPC classification number: B64C11/26 ,  B64C11/24 ,  B64C27/473 ,  B64C29/0033 ,  B64C2027/4736

    Abstract: A tiltrotor aircraft (10) includes a fuselage (12), a wing member (18) extending from the fuselage, an engine disposed relative to the wing member and a proprotor (26) mechanically coupled to the engine. The proprotor includes a plurality of proprotor blade assemblies (28) each including a spar (40) and a sheath (52) extending spanwise along the spar forming the leading edge (48) of the proprotor blade assembly. The spar has a root section (42), a main section (44) and a tip section (46). The spar has a generally oval cross section at radial stations along the main section and a first edge having a structural bias relative to a generally oppositely disposed second edge at the radial stations along the main section.

    Abstract translation: 倾转旋翼飞机（10）包括机身（12），从机身延伸的机翼构件（18），相对于机翼构件设置的发动机以及机械地联接到发动机的推进器（26）。 该推进器包括多个推进器桨叶组件（28），每个推进器桨叶组件包括沿着形成推进器桨叶组件的前缘（48）的翼梁沿翼展方向延伸的翼梁（40）和护套（52）。 翼梁具有根部（42），主部（44）和末端部（46）。 翼梁在沿着主要部分的径向站点处具有大致椭圆形的横截面，并且第一边缘相对于沿着主要部分的径向站点处的大致相对设置的第二边缘具有结构偏置。

    FOLDING PROPROTOR BLADE ASSEMBLY HAVING INTEGRAL TANG ASSEMBLY
    2.
    发明公开
    FOLDING PROPROTOR BLADE ASSEMBLY HAVING INTEGRAL TANG ASSEMBLY 审中-公开
    具有一体式TANG组件的折叠式推进器叶片总成

    公开(公告)号：EP3246248A1

    公开(公告)日：2017-11-22

    申请号：EP16173572.5

    申请日：2016-06-08

    Applicant: Bell Helicopter Textron Inc.

    Inventor： PAULSON, Jared ,  OLDROYD, Paul K. ,  FOSKEY, Christopher

    IPC: B64C11/26 ,  B64C27/473 ,  B64C29/00

    CPC classification number: B64C11/28 ,  B64C11/26 ,  B64C27/473 ,  B64C27/50 ,  B64C29/0033 ,  B64C2027/4736

    Abstract: A tiltrotor aircraft (10) includes a fuselage (12), a wing member (18) extending from the fuselage, an engine disposed relative to the wing member, a rotor hub assembly (26) mechanically coupled to the engine and a plurality of proprotor blade assemblies (28) rotatably mounted to the rotor hub assembly and operable for beamwise folding relative thereto. The proprotor blade assemblies each including a spar (40) and a sheath (52) extending spanwise along a leading edge of the spar. The spar has a root section (42), a main section (44) and a tip section (46). The spar has a generally oval cross section at radial stations along the main section of the spar with the root section of the spar forming an integral tang assembly (70) operable for coupling the spar to the rotor hub assembly.

    Abstract translation: 倾转旋翼飞行器（10）包括机身（12），从机身延伸的翼件（18），发动机设置相对于机翼构件，转子轮毂组件（26）机械地联接到所述发动机和多个旋翼螺旋桨的 叶片组件（28），所述叶片组件可旋转地安装到所述转子毂组件并且可操作用于相对于所述叶片组件进行光束折叠。 每个推进器桨叶组件包括翼梁（40）和沿着翼梁的前缘沿翼展方向延伸的护套（52）。 翼梁具有根部（42），主部（44）和末端部（46）。 翼梁在沿着翼梁的主部分的径向站处具有大致椭圆形的横截面，翼梁的根部部分形成可操作用于将翼梁耦合到转子毂组件的整体柄脚组件（70）。

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