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91. 发明授权

US4892462A Blade of composite materials and its manufacturing process 失效
标题翻译：复合材料刀片及其制造工艺
公开(公告)号：US4892462A
公开(公告)日：1990-01-09
申请号：US203373
申请日：1989-06-07
申请人： Bruno J. M. Barbier , Jean A. Michaud-Soret
发明人： Bruno J. M. Barbier , Jean A. Michaud-Soret
IPC分类号： B64C27/46 , B29D99/00 , B64C11/26 , B64C27/473 , B64C27/82
CPC分类号： B29D99/0025 , B64C11/26 , B64C27/473 , B64C2027/4736 , Y10T29/49332 , Y10T29/49337
摘要： The blade of composite materials and its manufacturing process according to the invention are such that the spar includes at least one bundle (10a, 10b) extending longitudinally in the shell (4), between the fillings of the leading edge (12a) and the trailing edge (12c) and which adheres directly to the laminated pressure face and suction face coverings, (4a, 4b) of the rigid shell (4). Beyond the blade footing (3), the spar is shaped to form a root loop flexible in torsion (8) and passing round an attaching socket (9) on the hub. Application to variable pitch multi-blade propellers for the streamlined tail rotors of helicopters.
摘要翻译：根据本发明的复合材料刀片及其制造方法使得翼梁包括在壳体（4）中纵向延伸的至少一个束（10a，10b），在前缘（12a）的填充物和尾部边缘（12c），并且其直接粘附到刚性壳体（4）的层压压力面和吸力面罩（4a，4b）。在叶片基部（3）之外，翼梁被成形为形成柔性的扭转（8）的根部环，并且穿过轮毂上的附接插座（9）。适用于直升机流线型尾转子的变桨距多叶片螺旋桨。

92. 发明授权

US4639284A Process for manufacturing a variable pitch multi-blade propeller by molding resin-impregnated fails around a preform 失效
标题翻译：通过模制树脂浸渍制造可变节距多叶片螺旋桨的方法在预成型件周围失效
公开(公告)号：US4639284A
公开(公告)日：1987-01-27
申请号：US688896
申请日：1985-01-04
申请人： Rene L. Mouille , Marc Declerco , Jean-Pierre Jalaguier , Bernard Jaugey
发明人： Rene L. Mouille , Marc Declerco , Jean-Pierre Jalaguier , Bernard Jaugey
IPC分类号： B64C11/22 , B29C43/02 , B29C43/18 , B29C43/20 , B29C43/32 , B29C43/34 , B29C57/00 , B29C67/00 , B29C70/06 , B29D99/00 , B29K105/10 , B32B3/12 , B64C11/26 , B64C27/46 , B64C27/473 , B64C27/82 , F01D5/28 , B32B31/20
CPC分类号： B29D99/0025 , B64C11/26 , B64C27/473 , B64C27/82 , F01D5/282 , B64C2027/4736 , B64C2027/8254 , F05D2200/31 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10T156/103 , Y10T156/1043
摘要： A variable pitch multi-blade propeller suitable for use on a helicopter is constructed of a foam preform joined with a fibrous spar enclosed in resin-impregnated foils and fitted with a metal leading edge. Various components are assembled in a mold and the resins, then cured. The structure may further include a reinforcing yoke of carbon fiber fabrics preimpregnated with a polymerizable synthetic resin. The process may further include a heat treating step to effect polymerization.
摘要翻译：适用于直升机的可变螺距多叶片螺旋桨由泡沫预制件构成，泡沫预制件与封闭在浸渍树脂的箔中并配有金属前缘的纤维状翼梁连接。各种部件组装在模具和树脂中，然后固化。该结构还可以包括用可聚合的合成树脂预浸渍的碳纤维织物的增强轭。该方法还可以包括进行聚合的热处理步骤。

93. 发明授权

US4626173A Variable-pitch multi-blade propeller incorporating individually dismountable blades made of composite materials, process for manufacturing such blades and blades thus produced 失效
标题翻译：可变螺距多叶片螺旋桨，包括由复合材料制成的单独可拆卸的叶片，由此制造这种叶片和叶片的方法
公开(公告)号：US4626173A
公开(公告)日：1986-12-02
申请号：US587649
申请日：1984-03-08
申请人： Rene L. Mouille , Marc Declerco , Jean-Pierre Jalaguier , Bernard Jaugey
发明人： Rene L. Mouille , Marc Declerco , Jean-Pierre Jalaguier , Bernard Jaugey
IPC分类号： B64C11/22 , B29C43/02 , B29C43/18 , B29C43/20 , B29C43/32 , B29C43/34 , B29C57/00 , B29C67/00 , B29C70/06 , B29D99/00 , B29K105/10 , B32B3/12 , B64C11/26 , B64C27/46 , B64C27/473 , B64C27/82 , F01D5/28 , B64C27/45 , B64C11/00
CPC分类号： B29D99/0025 , B64C11/26 , B64C27/473 , B64C27/82 , F01D5/282 , B64C2027/4736 , B64C2027/8254 , F05D2200/31 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10T156/103 , Y10T156/1043
摘要： Each blade is fixed to the hub by the root part of the spar, arranged in the form of a loop surrounding a connection element bolted on the hub, with the interposition of rigid rings by a pin simultaneously fixing the hub on a drive sleeve transmitting thereto the driving torque of the central shaft. The hub comprises two coaxial cylindrical walls in each of which is pierced, for each blade, a circular opening in which the member for controlling the angle of attach which is fast with the blade root is mounted to rotate via self-lubricating rings. The invention is particularly applicable to helicopters.
摘要翻译：每个叶片通过翼梁的根部固定到轮毂上，该环形部分围绕螺栓连接在轮毂上的连接元件的环形结构，通过销插入刚性环，同时将轮毂固定在传递到其上的驱动套筒上中心轴的驱动扭矩。轮毂包括两个同轴的圆柱形壁，每个叶片每个叶片被刺穿一个圆形开口，其中用于控制与叶片根部快速相关的附着角度的构件安装在其上，通过自润滑环旋转。本发明特别适用于直升机。

94. 发明授权

US4626172A Variable-pitch multi-blade propeller incorporating individually dismountable blades made of composite materials, process for manufacturing such blades and blades thus produced 失效
标题翻译：可变螺距多叶片螺旋桨，包括由复合材料制成的单独可拆卸的叶片，由此制造这种叶片和叶片的方法
公开(公告)号：US4626172A
公开(公告)日：1986-12-02
申请号：US726640
申请日：1985-04-24
申请人： Rene L. Mouille , Marc Declerco , Jean-Pierre Jalaguier , Bernard Jaugey
发明人： Rene L. Mouille , Marc Declerco , Jean-Pierre Jalaguier , Bernard Jaugey
IPC分类号： B64C11/22 , B29C43/02 , B29C43/18 , B29C43/20 , B29C43/32 , B29C43/34 , B29C57/00 , B29C67/00 , B29C70/06 , B29D99/00 , B29K105/10 , B32B3/12 , B64C11/26 , B64C27/46 , B64C27/473 , B64C27/82 , F01D5/28 , B64C11/06
CPC分类号： B29D99/0025 , B64C11/26 , B64C27/473 , B64C27/82 , F01D5/282 , B64C2027/4736 , B64C2027/8254 , F05D2200/31 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y10T156/103 , Y10T156/1043
摘要： Each blade is fixed to the hub by the root part of the spar, arranged in the form of a loop surrounding a connection element bolted on the hub, with the interposition of rigid rings by a pin simultaneously fixing the hub on a drive sleeve transmitting thereto the driving torque of the central shaft. The hub comprises two coaxial cylindrical walls in each of which is pierced, for each blade, a circular opening in which the member for controlling the angle of attack which is fast with the blade root is mounted to rotate via self-lubricating rings. The invention is particularly applicable to helicopters.
摘要翻译：每个叶片通过翼梁的根部固定到轮毂上，该环形部分围绕螺栓连接在轮毂上的连接元件的环形结构，通过销插入刚性环，同时将轮毂固定在传递到其上的驱动套筒上中心轴的驱动扭矩。轮毂包括两个同轴的圆柱形壁，每个叶片被刺穿，每个叶片都有一个圆形开口，其中用于控制与叶片根部快速的迎角的构件安装成通过自润滑环旋转。本发明特别适用于直升机。

95. 发明授权

US4403918A Hubless, hingeless and bearingless helicopter rotor system 失效
标题翻译：无枢纽，无铰链和无轴承的直升机转子系统
公开(公告)号：US4403918A
公开(公告)日：1983-09-13
申请号：US340774
申请日：1982-01-19
申请人： Buford J. Schramm
发明人： Buford J. Schramm
IPC分类号： B64C27/33 , B64C27/473 , B64C27/38
CPC分类号： B64C27/473 , B64C27/33 , B64C2027/4736
摘要： A helicopter rotor system with a plurality of identical rotor blades each of which includes a skin that forms an interior region, a counterweight rod and a bundle of longitudinally-extending fibers in the region. The bundle continues outside of the region, and there it includes a bight portion with a pair of arms and a bend. The fibers in the region are continuations of the fibers in the bight portion. A torque tube is attached to the counterweight rod, and a bearing stabilizes the torque tube relative to the mast, but does not transfer any appreciable centrifugal load. This bearing permits rotation (feathering) of the torque tube around its own axis, and lateral movement in any direction from the torque tube axis, around the center of this bearing (lead lag, and flapping). The bight portion is progressively shaped from a single flat portion bent directly around the mast, through a pair of separate channel sections to a bundle adjacent to the counterbalance rod. The fibers are bonded together, and in the said region they are bonded not only to each other, but also to the counterweight rod, and to the skin. The blades are angularly spaced apart, and their flat portions are stacked one on top of the other. Attachment means, preferably fasteners and mounting plates, attaches the stack of flat portions to the mast, where they transfer the centrifugal load to the mast and are driven directly by it.
摘要翻译：一种具有多个相同转子叶片的直升机转子系统，每个转子叶片包括在该区域中形成内部区域，配重杆和纵向延伸纤维束的皮肤。束持续在该区域的外部，并且其包括具有一对臂和弯曲部的弯曲部分。该区域中的纤维是弯曲部分中的纤维的延续。扭矩管连接到配重杆上，并且轴承相对于桅杆稳定扭矩管，但不会传递任何明显的离心载荷。该轴承允许扭矩管围绕其自身轴线旋转（羽化），并且在扭矩管轴线的任何方向上横向移动，围绕该轴承的中心（牵引滞后和振荡）。弯曲部分从直接围绕桅杆弯曲的单个平坦部分逐渐成形，通过一对单独的通道部分到邻近平衡杆的束。纤维结合在一起，并且在所述区域中，它们不仅彼此粘合，而且还粘合到配重杆和皮肤上。叶片角度间隔开，并且它们的平坦部分彼此层叠。附接装置，优选地是紧固件和安装板，将平坦部分堆叠连接到桅杆上，在那里它们将离心载荷传递到桅杆并由其直接驱动。

96. 发明授权

US4316701A Composite aerodynamic rotor blade assembly 失效
标题翻译：复合空气动力转子叶片组件
公开(公告)号：US4316701A
公开(公告)日：1982-02-23
申请号：US903451
申请日：1978-05-08
申请人： Thomas S. Scarpati , Robert J. Ford
发明人： Thomas S. Scarpati , Robert J. Ford
IPC分类号： B64C27/473 , B64C27/46
CPC分类号： B64C27/473 , B64C2027/4736
摘要： What follows is a description of a composite aerodynamic rotor blade assembly which has been optimized from the standpoint of both fabrication cost and structural integrity. The rotor blade is fabricated using fewer overall assemblies to optimize cost and includes an aft fairing structure which is uniquely characterized in that it includes not only the typical elements of an aft fairing structure of the composite blade, but the spar heel as well. In assembly the skin members of the aft fairing structure are secured between the spar heel and the cap member of the assembly. This insures a fail-safe design and in this way the skin members are enabled to carry load effectively. The deicing blanket is assembled with the spar and cap member so that its supporting structural material serves as a load carrying member. Also, the spar, the inboard termination of the cap member, and the spar heel together form the root end of the rotor blade into which the torsion splices are formed.
摘要翻译：以下是从制造成本和结构完整性两方面优化的复合空气动力学转子叶片组件的描述。转子叶片使用更少的整体组件来制造，以优化成本，并且包括后整流罩结构，其特征在于，其不仅包括复合叶片的后整流罩结构的典型元件，而且还包括翼梁。在组装中，后整流罩结构的皮肤构件固定在组件的翼梁跟部和帽部件之间。这确保了故障安全设计，并以这种方式使皮肤成员能够有效地携带负载。除冰毯与翼梁和帽构件组装，使得其支撑结构材料用作承载构件。此外，翼梁，盖构件的内侧端接和翼梁跟部一起形成转子叶片的根端，扭转接头形成在其中。

97. 发明授权

US4299540A Tail rotor blade 失效
标题翻译：尾转子叶片
公开(公告)号：US4299540A
公开(公告)日：1981-11-10
申请号：US272
申请日：1979-01-02
申请人： Cecil E. Covington , Ronnie L. Martin
发明人： Cecil E. Covington , Ronnie L. Martin
IPC分类号： B64C27/473 , B64C11/20 , B64C11/26
CPC分类号： B64C27/473
摘要： A tail rotor blade for a helicopter has a core 22 whose shape defines the trailing portions of the blade. Core 22 is adhered to upper 20 and lower 21 metallic skins which extend within and are adhered to the inner surfaces at the trailing edge of a metallic nose spar 10. A pair of straps 30, 31 of unidirectional fiberglass strands extend spanwise and are adhered to the inner surface of the leading edges of the skins 20, 21 and the outer leading surfaces of the core 22 as to span chordwise the regions of the joints between nose spar 10 and skins 20, 21.
摘要翻译：用于直升机的尾部转子叶片具有形状限定叶片后部的芯部22。芯22粘附在上金属外表面20和下表面21上，金属外皮在金属鼻梁10的后缘处延伸并附着到内表面。单向玻璃纤维束的一对带30,31延伸展开并粘附到表皮20,21的前缘的内表面和芯22的外引导表面，以跨越鼻翼10和皮肤20,21之间的关节的区域。

98. 发明授权

US4281966A Multi-blade propellers 失效
标题翻译：多叶片螺旋桨
公开(公告)号：US4281966A
公开(公告)日：1981-08-04
申请号：US55096
申请日：1979-07-05
申请人： Maurice L. Duret , Bernard L. J. Lamarche , Marc A. Declercq , Robert D. Martin
发明人： Maurice L. Duret , Bernard L. J. Lamarche , Marc A. Declercq , Robert D. Martin
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。

99. 发明授权

US4213739A Helicopter rotor blade 失效
标题翻译：直升机转子叶片
公开(公告)号：US4213739A
公开(公告)日：1980-07-22
申请号：US879915
申请日：1978-02-22
申请人： August H. L. Euler , Gilbert F. A. Beziac
发明人： August H. L. Euler , Gilbert F. A. Beziac
IPC分类号： B29D99/00 , B64C27/473 , B64C27/46
CPC分类号： B29D99/0025 , B64C27/473 , B64C2027/4736 , Y10T29/49337
摘要： A rotor blade, specially for a helicopter rotor, which blade is made of reinforced plastics.This blade comprises: a solid one-piece leading edge spar embodied by strands of glass fibre filaments extending lengthwise over the whole length of the blade; a core made of a lightweight cellular substance and placed contiguous with the spar rear face; a thick sheet-like member extending around the spar and the core and comprising at least one layer of a fabric consisting of parallel glass fibres disposed askew of the blade longitudinal axis so as to form a torque-tube; a rear filling element, and a covering extending around the torque-tube and the rear filling element. The airfoil portion of this blade is centered substantially in the front quarter of the chord of the blade cross-section and it has a very high torsional stiffness.
摘要翻译：转子叶片，特别用于直升机转子，该叶片由增强塑料制成。

100. 发明授权

US4137007A Rotor blade structure 失效
标题翻译：转子叶片结构
公开(公告)号：US4137007A
公开(公告)日：1979-01-30
申请号：US752323
申请日：1976-12-20
申请人： Walter Schonball
发明人： Walter Schonball
IPC分类号： B64C27/473 , F03D1/06
CPC分类号： B64C27/473 , Y02E10/721
摘要： A system of spars, each having a rectangular cross-section, is provided by placing the spars in lateral juxtaposition to one another like a plank to form a rotor blade. A skin of plastic foam is provided on the blade. The cross-sections of the spars, and the corresponding cross-sections of the blade, are varied in accordance with aerodynamic requirements. The spars are kept in position by means of clamps and/or connections and/or rings, forming an integral unit similar to a plank; and the integrated spars are directly attached to a hub or an electric generator.
摘要翻译：每个具有矩形横截面的翼梁系统通过将翼梁彼此侧向并置放置而形成，以形成一个转子叶片。在叶片上提供塑料泡沫的皮肤。叶片的横截面和叶片的相应横截面根据空气动力学要求而变化。翼梁通过夹具和/或连接和/或环保持在适当位置，形成与木板相似的整体单元; 并且集成的翼梁直接连接到轮毂或发电机。

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