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公开(公告)号：US4281966A
公开(公告)日：1981-08-04
申请号：US55096
申请日：1979-07-05
IPC分类号： B64C11/22 , B29D99/00 , B64C11/20 , B64C27/35 , B64C27/45 , B64C27/46 , B64C27/473 , B64C27/82 , B64C11/06 , B64C11/32
CPC分类号： B29D99/0025 , B64C11/20 , B64C27/45 , B64C27/82 , B64C2027/8254
摘要： A variable-pitch, multi-blade propeller specially usable as a rear rotor of a rotary-wing aircraft and a process for manufacturing the same are described. The propeller comprises a number of pairs of blades emanating from a central hub, each pair comprising a single elongate strip secured at its center to the hub. The strip is composed of two flat bundles of fibres and defining an aperture for a sliding shaft at their center. The shaft is used to control the pitch angles of the blades and aerodynamic blade shells are secured to the fibre bundles by adhesive synthetic cellular or foam material.
摘要翻译： 描述了一种特殊可用作旋翼飞机的后转子的可变螺距，多叶片螺旋桨及其制造方法。 螺旋桨包括从中心毂发出的多对叶片，每对叶片包括在其中心处固定到轮毂的单个细长条。 该条由两束扁平的纤维组成，并在其中心限定一个用于滑动轴的孔。 轴用于控制叶片的桨距角，并且空气动力学叶片壳通过粘合剂合成的细胞或泡沫材料固定到纤维束上。
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公开(公告)号：US4255084A
公开(公告)日：1981-03-10
申请号：US9614
申请日：1979-02-05
CPC分类号： B64C27/001 , B64C2027/003 , Y10S416/50
摘要： The invention relates to a device for damping the vibrations of the rotor of a rotary-wing aircraft. This device comprises a flapping weight concentrated near the rotor axis and at least three resiliently deformable elements, such as helical springs. The deformable elements are radially biassed in directions regularly distributed around the rotor axis. The inner ends of the deformable elements directly bear on the flapping weight. Their outer ends directly bear on rigid structure elements, rigidly secured to the rotor hub, so that the biassed deformable elements apply statically balanced centripetal thrusts to the flapping weight.
摘要翻译： 本发明涉及一种用于阻尼转翼飞机转子振动的装置。 该装置包括在转子轴线附近集中的扑动重物和至少三个可弹性变形的元件，例如螺旋弹簧。 可变形元件在围绕转子轴线规则分布的方向上径向偏压。 可变形元件的内端直接承受扑动重量。 它们的外端直接承载在刚性结构元件上，刚性地固定到转子毂上，使得偏置的可变形元件将静态平衡的向心推力施加到扑动重量。
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3.发明授权Resonator device for damping the vibrations of a rotor of a rotary-wing aircraft 失效用于阻尼旋翼飞机转子振动的谐振器装置
公开(公告)号：US4281967A
公开(公告)日：1981-08-04
申请号：US9578
申请日：1979-02-05
CPC分类号： B64C27/001 , B64C2027/003 , Y10S416/50 , Y10T464/50
摘要： The invention relates to a device for damping the vibrations of a rotary-wing aircraft rotor. An annular weight is disposed concentrically of the rotor axis. This weight is supported by at least three resiliently deformable elements such as helical springs, radially biased in directions distributed regularly around the rotor axis. The inner ends of the springs directly bear on a part extending the rotor shaft axially. Their outer ends directly bear on the annular weight so that the spring apply statically balanced centrifugal thrusts to the annular weight. The springs are so still that they support the annular weight without substantially bending.
摘要翻译： 本发明涉及一种用于阻尼旋翼飞机转子振动的装置。 环形重物与转子轴线同心设置。 这种重量由至少三个可弹性变形的元件（例如螺旋弹簧）支撑，径向偏压地围绕转子轴线规则地分布。 弹簧的内端直接承载在轴向上延伸转子轴的部分上。 它们的外端直接承受环形重量，使得弹簧将静态平衡的离心推力施加到环形重物上。 弹簧仍然如此，使得它们支撑环形重量而基本不弯曲。
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