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公开(公告)号：US4755106A
公开(公告)日：1988-07-05
申请号：US931099
申请日：1986-11-17
申请人： Rene L. Coffy
发明人： Rene L. Coffy
CPC分类号： B64C27/43 , B64C27/35 , F03D1/0658 , Y02E10/721
摘要： The invention provides a balance bar twin blade hub. A beam is formed of a tube made from a composite material of evolutive form whose section is cylindrical at its end on the blade side and progressively elliptical as far as its central connection part. It is connected to a support stirrup 2 conical stratified stops 4 forming balance bar bearings identical to the conical stratified stops forming the centrifugal force take up and angle of attack bearings providing the connection between the blade 16 and the beam.
摘要翻译： 本发明提供一种平衡杆双叶片毂。 梁由由演化形式的复合材料制成的管形成，其截面在其叶片侧的端部为圆柱形，并且在其中心连接部分上呈逐渐椭圆形。 它连接到支撑箍箍2个锥形分层止动件4，形成与圆锥形分层止动件相同的平衡杆轴承，形成离心力吸收和提供叶片16和梁之间的连接的迎角轴承。
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2.发明授权Blade made of thermoplastic composite, in particular for ducted tail rotor of a helicopter, and its method of manufacture 失效由热塑性复合材料制成的刀片，特别是用于直升机的管道尾部转子及其制造方法
公开(公告)号：US5462408A
公开(公告)日：1995-10-31
申请号：US165862
申请日：1993-12-14
申请人： Rene L. Coffy
发明人： Rene L. Coffy
IPC分类号： B64C11/20 , B29B15/08 , B29C70/08 , B29C70/34 , B29D99/00 , B64C11/06 , B64C11/26 , B64C27/46 , B64C27/473 , B64C27/82 , B64C27/48
CPC分类号： B29D99/0025 , B29B15/08 , B29C70/083 , B29C70/345 , B64C27/473 , B29C2791/001 , B29K2071/00 , B29K2105/0845 , B29K2105/108 , B29K2307/00 , B29L2031/082 , B64C2027/4736 , Y10T29/49337
摘要： The blade has its lower-surface and upper-surface skins of its shell, its front and rear filling bodies and its spar made of a composite material having the same thermoplastic matrix, preferably made of PEEK, reinforced preferably with carbon fibres. The spar is extended outside the shell by an integrated rooting part with linkage attachment, in a loop or laminate, in the same thermoplastic composite. The method consists in assembling, by melting, under pressure, all the thermoplastic composite components of the blade, in a single step after manufacturing these components in the form of prefabricated elementary pieces.
摘要翻译： 叶片具有其外壳的下表面和上表面表皮，其前后填充体和其由具有相同热塑性基质的复合材料制成的翼梁，优选由PEEK制成，优选用碳纤维增强。 翼梁通过一个整合的生根部分延伸到壳体外部，该部件具有连接装置，在环或层压板中，在相同的热塑性复合材料中。 该方法包括通过在压力下熔化叶片的所有热塑性复合材料组件，以预制的基本件的形式在制造这些部件之后的一个步骤中组装。
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3.发明授权Blade made of thermoplastic composite, in particular for ducted tail rotor of a helicopter, and its method of manufacture with injection step 失效由热塑性复合材料制成的刀片，特别是用于直升机的管道尾部转子，以及其具有注射步骤的制造方法
公开(公告)号：US5454693A
公开(公告)日：1995-10-03
申请号：US165861
申请日：1993-12-14
申请人： Jacques A. Aubry , Rene L. Coffy
发明人： Jacques A. Aubry , Rene L. Coffy
IPC分类号： B64C11/20 , B29C45/14 , B29C70/34 , B29C70/72 , B29D99/00 , B64C11/26 , B64C27/473 , B64C27/82 , B64C27/48
CPC分类号： B29D99/0025 , B29C45/14467 , B29C70/345 , B29C70/72 , B64C27/473 , B29K2071/00 , B29K2101/12 , B29K2105/12 , B29K2707/04 , B29L2031/082 , B64C2027/4736 , Y10T29/49337
摘要： The blade has its lower-surface and upper-surface skins of its shell, its front and rear filling bodies and its spar made of a composite material having the same thermoplastic matrix, preferably made of PEEK, reinforced preferably with carbon fibres. The spar is extended outside the shell by an integrated rooting part with linkage attachment, in a loop or laminate, in the same thermoplastic composite. The method consists in assembling the spar with the skins, after manufacturing these components in the form of prefabricated elementary pieces, by injecting under pressure a fluidized thermoplastic composite with short reinforcing fibres moulding the filling bodies.
摘要翻译： 叶片具有其外壳的下表面和上表面表皮，其前后填充体和其由具有相同热塑性基质的复合材料制成的翼梁，优选由PEEK制成，优选用碳纤维增强。 翼梁通过一个整合的生根部分延伸到壳体外部，该部件具有连接装置，在环或层压板中，在相同的热塑性复合材料中。 该方法在于通过在压力下注射具有模制填充体的短增强纤维的流化热塑性复合材料，以预制的基本件的形式制造这些部件之后，将翼梁与皮肤组装。
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4.发明授权Flexible girder with high energy absorption, and landing gear and tail skid for an aircraft equipped with such a girder 失效具有高能量吸收的柔性梁，配备有这种大梁的飞机的起落架和尾部滑行
公开(公告)号：US4645143A
公开(公告)日：1987-02-24
申请号：US667672
申请日：1984-11-02
申请人： Rene L. Coffy
发明人： Rene L. Coffy
CPC分类号： B64C25/64 , B64C25/52 , B64C2025/325
摘要： The flexible girder made of composite materials and with high energy absorption is in the form of an elongate box of laminated structure comprising two rigid flanges (6,7) connected by two webs (9) which have aligned apertures (13). A deformable energy-absorbing block (14') is arranged between the two flanges (6,7) at the apertures and comprises a block of an elastomeric material (15). The block (14') absorbs the buckling deformation energy of the flange (6) which is subjected to compressive stress during flexion of the girder, by resting on the other flange (7) which is subjected to tensile stress. The block (14') controls the buckling of the flange (6) and only gives back part of the energy absorbed. Application to the equipment in particular of skid landing gear for helicopters and tail skids for aircraft.
摘要翻译： 由复合材料制成并且具有高能量吸收的柔性梁为细长的层叠结构的形式，包括两个由具有对准的孔（13）的腹板（9）连接的刚性凸缘（6,7）。 可变形能量吸收块（14'）布置在孔的两个凸缘（6,7）之间，并且包括弹性体材料块（15）。 块体（14'）通过搁置在受拉伸应力的另一个凸缘（7）上，吸收在弯曲过程中受到压应力的凸缘（6）的屈曲变形能。 块（14'）控制凸缘（6）的弯曲，并且仅给出吸收的能量的一部分。 应用于设备，特别是用于飞机的直升机和尾翼的滑行起落架。
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5.发明授权
公开(公告)号：US4532889A
公开(公告)日：1985-08-06
申请号：US627713
申请日：1984-07-05
申请人： Rene L. Coffy
发明人： Rene L. Coffy
IPC分类号： B22D19/14 , B22F3/26 , C22C47/00 , C22C47/16 , C22C47/18 , C23C14/32 , C23C14/56 , C23C13/08 , C23C13/10
CPC分类号： C23C14/562 , C23C14/32
摘要： The invention relates to a process and an apparatus for the metallic impregnation of a substrate that is in the form of a web of conductive fibres, in which the said substrate is placed in an inert atmosphere that is under partial vacuum (chamber 1), a potential difference is created between the said substrate (cathode) and a metal for impregnation in the said atmosphere, the metal for impregnation is supplied in molten form into the said atmosphere and is maintained at its vaporization temperature by heating.The invention is of use in the manufacture of semi-finished products for the aeronautical industry.
摘要翻译： 本发明涉及一种用于金属浸渍基材的方法和设备，该基材是导电纤维网的形式，其中所述基材置于处于部分真空（室1）的惰性气氛中， 在所述基板（阴极）和用于在所述气氛中浸渍的金属之间产生电位差，用于浸渍的金属以熔融形式供应到所述气氛中并通过加热保持在其蒸发温度。 本发明可用于制造航空工业的半成品。
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6.发明授权
公开(公告)号：US5360503A
公开(公告)日：1994-11-01
申请号：US075479
申请日：1993-06-17
申请人： Rene L. Coffy
发明人： Rene L. Coffy
CPC分类号： C08J5/046 , D03D15/00 , D03D15/12 , D06M23/00 , F16D69/026 , D10B2101/06 , D10B2101/08 , D10B2101/12 , D10B2101/20 , D10B2331/04 , D10B2401/041 , D10B2505/02 , Y10S428/913 , Y10S57/905 , Y10T156/1048 , Y10T428/1362 , Y10T428/1369 , Y10T428/1393 , Y10T428/1397 , Y10T428/24099 , Y10T428/24124 , Y10T428/24132 , Y10T428/2929 , Y10T428/2967 , Y10T442/3049 , Y10T442/607 , Y10T442/699
摘要： The semi-finished product according to the invention consists exclusively of liquid crystal thermoplastic polymers (LCP), whereof at least one first liquid crystal thermoplastic polymer (LCP) is in the form of fibers (18) and has a given melting point, and whereof at least one second liquid crystal thermoplastic polymer (LCP) (16) has a melting point below that of the first LCP. This semi-finished product is in particular a fabric. By simply heating under pressure at a temperature equal to the melting point of the second LCP, followed by cooling, a composite material with improved mechanical and physicochemical performance characteristics are obtained.
摘要翻译： PCT No.PCT / FR91 / 01031 Sec。 371日期：1993年6月17日 102（e）日期1993年6月17日PCT 1991年12月18日PCT PCT。 第WO92 / 11311号公报 日本1992年7月9日。根据本发明的半成品仅由液晶热塑性聚合物（LCP）构成，其中至少一种第一液晶热塑性聚合物（LCP）为纤维形式（18），并且具有 至少一个第二液晶热塑性聚合物（LCP）（16）的熔点低于第一个LCP的熔点。 这种半成品特别是织物。 通过简单地在等于第二LCP的熔点的温度下加压，然后冷却，获得具有改善的机械和物理化学性能特性的复合材料。
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7.发明授权
公开(公告)号：US4419398A
公开(公告)日：1983-12-06
申请号：US331787
申请日：1981-12-17
申请人： Rene L. Coffy , Jean J. E. Azeau
发明人： Rene L. Coffy , Jean J. E. Azeau
CPC分类号： F16F1/393 , B64C27/35 , Y10T428/24628 , Y10T428/2495
摘要： The invention concerns laminated stops of curved shapes, particularly for helicopter rotors. The stop has an inner fitting and an outer fitting connected by cupped elements of a resistant and rigid material alternating with layers of flexible material. The layers of flexible material increase in thickness from their centers outwardly, and the mean thickness of the flexible layers increase from the inner fitting to the outer fitting.
摘要翻译： 本发明涉及弯曲形状的层叠止动件，特别是直升机转子。 该止动件具有内部配件和外部配件，其通过与柔性材料层交替的电阻和刚性材料的杯形元件连接。 柔性材料层的厚度从它们的中心向外增加，并且柔性层的平均厚度从内部配件增加到外部配件。
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