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1. 发明申请

WO2015160679A1 ENGINE INLET CONFIGURATION 审中-公开
标题翻译：发动机入口配置
公开(公告)号：WO2015160679A1
公开(公告)日：2015-10-22
申请号：PCT/US2015/025507
申请日：2015-04-13
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BOFILL, Steven , CHASEN, Scott A. , SIMONETTI, Joseph Lawrence , LAMB, Donald William, Jr.
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0246 , B64D2033/0253
摘要： An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet.
摘要翻译：发动机入口组件包括具有第一入口管道腿部和第二入口管道腿部的入口管道，第一入口管道腿部和第二入口管道腿部朝向位于发动机入口处的公共入口管道出口延伸。第一入口管道腿和第二入口管道腿在空气入口处固定地固定到飞行器的机身上。管道出口具有与发动机入口的浮动接口。

2. 发明申请

WO2015171716A1 FUEL SYSTEM BREAKAWAY VALVE REACTION BRIDGE AND REACTION COLLAR 审中-公开
标题翻译：燃油系统破碎阀反应桥和反应堆
公开(公告)号：WO2015171716A1
公开(公告)日：2015-11-12
申请号：PCT/US2015/029398
申请日：2015-05-06
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： CHASEN, Scott A. , ROGSTAD, Robert R. , BIEHL, Chris John
IPC分类号： F16K17/40
CPC分类号： B64D37/12 , B64D37/005 , B64D37/14 , F16K17/40
摘要： A flexible fuel bladder assembly for an aircraft includes a flexible fuel bladder positioned at an airframe and having an opening to allow a flow of fuel into and/or out of the fuel bladder. A breakaway valve is operably connected to the fuel bladder at the opening to control a flow of fuel therethrough. A non-contacting or loose fitting reaction feature is affixed to the airframe and is interactive with the breakaway valve such that movement of the breakaway valve relative to the reaction feature results in breakage of a valve body of the breakaway valve and closure of the breakaway valve to prevent flow of fuel therethrough while also allowing for a second reaction mode to cause breakage of a valve body should the connecting hose be pulled relative to the breakaway valve.
摘要翻译：用于飞行器的柔性燃料囊组件包括位于机身处的柔性燃料囊，并且具有开口以允许燃料流入和/或流出燃料囊。分离阀在开口处可操作地连接到燃料囊，以控制燃料通过其中。非接触或松散的接合反应特征被固定在机身上并且与分离阀相互作用，使得分离阀相对于反应特征的运动导致分流阀的阀体的断裂和分离阀的闭合以防止燃料流过其中，同时还允许第二反应模式在连接软管相对于分流阀被拉动时引起阀体的断裂。

3. 发明申请

WO2016054018A3 BLADE INDEXING OF A ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋翼式飞机的叶片指数
公开(公告)号：WO2016054018A3
公开(公告)日：2016-04-07
申请号：PCT/US2015/052907
申请日：2015-09-29
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： HUNTER, David H. , CHASEN, Scott A. , CERGE, Brandon Michael , KOESSICK, Maximilian August , KOSTOSS, Michael J. , NUSSENBLATT, Eric Lucien , THOMAS, Justin , BUTLER, Christopher P.
IPC分类号： B64C27/10
摘要： An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with a plurality of blades rotating in a first plane and a lower rotor assembly with a plurality of blades rotating in a second plane, each of the blades having a root end, a midpoint, and a tip end. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. The blades of the upper rotor assembly and the blades of the lower rotor assembly are indexed to improve tip end clearance between pairs of tip ends in the crossing plane as the tip ends move in respective first and second sinusoidal paths.
摘要翻译：提供了一种包括机身，延伸尾部以及反转同轴主转子组件的飞机，所述同轴主转子组件包括上转子组件和下转子组件，所述上转子组件具有在第一平面内旋转的多个叶片，多个叶片在第二平面内旋转，每个叶片具有根端，中点和末端。位于延伸尾部的平移推力系统，平移推力系统为机身提供平移推力。上部转子组件的叶片和下部转子组件的叶片被转位以当尖端在相应的第一和第二正弦路径中移动时改善交叉平面中的成对尖端之间的尖端间隙。

4. 发明申请

WO2016003534A2 ARTICULATED MOUNTS 审中-公开
标题翻译：铰接式支架
公开(公告)号：WO2016003534A2
公开(公告)日：2016-01-07
申请号：PCT/US2015/028839
申请日：2015-05-01
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： MCBRIDE, Jon , CHASEN, Scott A.
IPC分类号： F16M7/00
CPC分类号： B64D27/26 , B64D27/14 , B64D41/00 , B64D2041/002
摘要： A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.
摘要翻译：提供了一种使用可调安装组件固定发动机的方法，包括将可调安装组件的可延伸元件从第一位置调整到第二位置。可调安装组件的另一个可延伸元件从第三位置调整到第四位置。发动机使用可调节的安装组件安装，可伸展元件处于第二位置，另一伸缩元件处于第四位置。

5. 发明申请

WO2010065213A2 ECCENTRIC FITTING ASSEMBLY 审中-公开
标题翻译：偏心配件
公开(公告)号：WO2010065213A2
公开(公告)日：2010-06-10
申请号：PCT/US2009/062027
申请日：2009-10-26
申请人： SIKORSKY AIRCRAFT CORPORATION , MAXWELL, Robert W. , CHASEN, Scott A. , HAINSWORTH, Barton J.
发明人： MAXWELL, Robert W. , CHASEN, Scott A. , HAINSWORTH, Barton J.
IPC分类号： B64D1/04 , F16B5/00 , B64D7/04 , F16B37/00
CPC分类号： F16B5/025 , F16B5/0225 , F16B19/02 , F16B21/16 , F16B21/186
摘要： An eccentric fitting assembly includes an outer eccentric fitting which defines an outer axis, the outer eccentric fitting defines an opening offset from the outer axis and an inner eccentric fitting which defines an inner axis, the inner eccentric fitting defines a stud opening offset from the inner axis, the inner eccentric fitting receivable within the opening.
摘要翻译：偏心配件组件包括限定外轴线的外偏心配件，外偏心配件限定从外轴偏移的开口和限定内轴线的内偏心配件，内偏心配件限定了从内侧偏移的螺柱孔口轴心，内偏心配件可接收在开口内。

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