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公开(公告)号：EP3418191B1
公开(公告)日：2019-09-11
申请号：EP17201935.8
申请日：2017-11-15
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公开(公告)号：EP3434587A1
公开(公告)日：2019-01-30
申请号：EP18193690.7
申请日：2013-06-11
摘要： Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters (120) using an autorotative assist unit (110) coupled to the transmission (102) of the helicopter (120). Methods of utilizing an autorotative assist unit (110) as well as retrofitting an autorotative assist unit (110) to an existing helicopter (120) are also disclosed. By employing an autorotative assist unit (110), improved autorotation may be achieved without the need to increase the weight of the rotor (108).
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公开(公告)号：EP2488413B1
公开(公告)日：2014-04-23
申请号：EP09850460.8
申请日：2009-10-13
CPC分类号： B64C27/32 , B29C35/02 , B29C43/18 , B29C70/026 , B29C70/46 , B29K2063/00 , B29K2309/08 , B29L2031/3088 , B64C27/33
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公开(公告)号：EP3459847A1
公开(公告)日：2019-03-27
申请号：EP17204822.5
申请日：2017-11-30
发明人： MARSHALL, Bryan , WIINIKKA, Mark , SHERRILL, Paul , STAMPS, Frank
摘要： An aircraft rotor assembly (104) has a yoke (110) defining a plurality of bearing pockets (114). Each bearing pocket houses an axisymmetric elastomeric spherical bearing (116) at least partially therein. The axisymmetric elastomeric spherical bearings (116) comprise flap, lead-lag, and pitch hinges for rotor blades (106) coupled thereto. The rotor blades (106) maintain a first in-lane frequency of less than 1/rev through the use of damper assemblies (142) coupled between adjacent blades (106).
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公开(公告)号：EP2222553B1
公开(公告)日：2013-09-11
申请号：EP07869438.7
申请日：2007-12-18
IPC分类号： B64C11/16 , B64C27/46 , B64C27/473
CPC分类号： B64C27/473 , B64C2027/4736
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6.发明公开
公开(公告)号：EP3418191A1
公开(公告)日：2018-12-26
申请号：EP17201935.8
申请日：2017-11-15
CPC分类号： B64C27/008 , B64C11/008 , B64C27/473 , B64C27/82 , F03D1/0675 , F03D13/35
摘要： The present invention includes a balancing system (300) that includes a weight box (302), mounted substantially within the rotor-blade spar (324), flush with a rotor-blade spar outer surface (326), operably accessible from a rotor-blade tip (332), and retained within the rotor-blade spar by a weight-box retention pin (304), one or more weight-box contact surfaces (328) bonded to a rotor-blade-spar inner surface, or a weight-box lip (320) providing a bearing contact with an edge of a spar rotor-blade spar cutout (325); and a weight package (306) attached to the weight box, the weight package including a weight-box cover, two or more weight guide-rods (314) attached to the weight-box cover, wherein one of the two or more weight guide-rods is positioned forward of a pitch change axis or center of twist and wherein one of the two weight guide-rods is positioned aft of the pitch change axis or center of twist, and one or more balance weights (316) mounted on the weight guide-rods.
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公开(公告)号：EP3321177A1
公开(公告)日：2018-05-16
申请号：EP17154716.9
申请日：2017-02-03
IPC分类号： B64C11/00 , B64C11/20 , B64C27/00 , B64C27/473 , B64C29/00
CPC分类号： F16F15/32 , B64C11/008 , B64C11/20 , B64C27/008 , B64C27/04 , B64C27/473 , B64C29/0033 , F16F15/34
摘要： A weight system (200) for a rotor blade (118) includes a weight box (202) open in an outboard direction, a weight guide rod (212) connected to the weight box (202), the weight guide rod (212) extending in a spanwise direction through an interior of the weight box (202), and a span balance weight (206) disposed within the weight box (202), the span balance weight (206) being captured between the weight guide rod (212) and the weight box (202).
摘要翻译： 一种用于转子叶片（118）的配重系统（200）包括沿外侧方向敞开的配重箱（202），连接到配重箱（202）的配重导杆（212），配重杆（212）延伸 （202）的内部沿翼展方向延伸，并且在配重箱（202）内设置跨距平衡配重（206），跨距平衡配重（206）捕获在配重杆（212）和 重量箱（202）。
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公开(公告)号：EP3800119A1
公开(公告)日：2021-04-07
申请号：EP20209609.5
申请日：2013-06-11
摘要： Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters (120) using an autorotative assist unit (110) coupled to the transmission (102) of the helicopter (120). Methods of utilizing an autorotative assist unit (110) as well as retrofitting an autorotative assist unit (110) to an existing helicopter (120) are also disclosed. By employing an autorotative assist unit (110), improved autorotation may be achieved without the need to increase the weight of the rotor (108).
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公开(公告)号：EP2488413A1
公开(公告)日：2012-08-22
申请号：EP09850460.8
申请日：2009-10-13
IPC分类号： B64C27/00
CPC分类号： B64C27/32 , B29C35/02 , B29C43/18 , B29C70/026 , B29C70/46 , B29K2063/00 , B29K2309/08 , B29L2031/3088 , B64C27/33
摘要： A method of making a composite rotor yoke includes preparing a molded rotor yoke in a closed cavity tool and possibly machining at least one portion of the molded rotor yoke to form the rotor yoke. In the preferred embodiment, preparing the molded rotor yoke is accomplished by applying layers of uncured low-flow composite material and a layer of uncured high-flow adhesive; substantially enclosing the uncured molded rotor yoke in the closed cavity tool; applying pressure so as to compress the uncured molded rotor yoke; and curing the uncured molded rotor yoke. During the curing process, the high-flow adhesive bleeds out of the molded rotor yoke, thereby preventing marcels from forming through movement of the low-flow composite material.
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公开(公告)号：EP2222553A1
公开(公告)日：2010-09-01
申请号：EP07869438.7
申请日：2007-12-18
CPC分类号： B64C27/473 , B64C2027/4736
摘要： A helicopter rotor blade includes a structural composite skin defining a cavity therein; a composite spar disposed within the cavity and adhesively bonded to the skin, a portion of the spar exhibiting a C-shape in cross section; and a foam core disposed within the cavity and adhesively bonded to the skin. The structural composite skin forms an external, closed box structure configured to transmit mechanical loads encountered by the rotor blade.
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