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1. 发明申请

WO2016076937A1 LUBRICANT LEVEL SENSING FOR AN ACTUATOR 审中-公开
标题翻译：润滑剂水平感应器
公开(公告)号：WO2016076937A1
公开(公告)日：2016-05-19
申请号：PCT/US2015/047137
申请日：2015-08-27
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： MATALANIS, Claude G. , JONSSON, Ulf J. , WAKE, Brian E. , CANNATA, John D.
IPC分类号： F04B39/02
CPC分类号： F16N29/00 , B64C27/615 , B64C27/72 , B64C2027/7294 , F16N2250/04 , F16N2250/18 , G01F23/164
摘要： According to one aspect, a lubricant level sensing system for an actuator is provided. The lubricant level sensing system includes a pressure port in an outer housing of the actuator, a pressure sensor, and a pathway from the pressure port to the pressure sensor. The pathway establishes fluid communication between the pressure sensor and a free volume of an internal cavity of the outer housing relative to a lubricant level in the internal cavity such that the pressure sensor detects a pressure of the free volume used to derive the lubricant level.
摘要翻译：根据一个方面，提供了一种用于致动器的润滑剂液位感测系统。润滑剂液位感测系统包括致动器的外壳中的压力端口，压力传感器以及从压力端口到压力传感器的路径。所述通道建立所述压力传感器与所述外部壳体的内部空腔的自由体积之间相对于所述内部空腔中的润滑剂液位的流体连通，使得所述压力传感器检测用于导出润滑剂水平的自由体积的压力。

2. 发明申请

WO2018013208A1 ROTOR BLADE DEFLECTION SENSING SYSTEM 审中-公开
标题翻译：转子叶片偏转传感系统
公开(公告)号：WO2018013208A1
公开(公告)日：2018-01-18
申请号：PCT/US2017/032347
申请日：2017-05-12
申请人： SIKORSKY AIRCRAFT CORPORATION , UNITED TECHNOLOGIES CORPORATION
发明人： GEIGER, Derek , KIM, Seung Bum , MATALANIS, Claude G. , WAKE, Brian E. , BOWLES, Patrick
IPC分类号： F03D17/00
摘要： A rotor blade deflection sensing system including a rotor blade having a first surface, a second surface, a third surface and a fourth surface. At least two fiber optic sensor arrays are mounted to the rotor blade. At least one of the at least two fiber optic sensor arrays is mounted to one of the first surface, the second surface, the third surface and the fourth surface and another of the at least two fiber optic sensor arrays being mounted to another of the first surface, a second surface, a third surface and a fourth surface. A controller is operatively connected to the at least two fiber optic sensor arrays. The controller determines one or more of a flapwise and an edgewise displacement based on inputs from the at least two fiber optic sensor arrays.
摘要翻译：转子叶片偏转感测系统包括具有第一表面，第二表面，第三表面和第四表面的转子叶片。至少有两个光纤传感器阵列安装在转子叶片上。所述至少两个光纤传感器阵列中的至少一个安装到所述第一表面，所述第二表面，所述第三表面和所述第四表面中的一个，并且所述至少两个光纤传感器阵列中的另一个安装到所述第一表面，第二表面，第三表面和第四表面。控制器可操作地连接到至少两个光纤传感器阵列。控制器基于来自至少两个光纤传感器阵列的输入来确定一个或多个翼展方向和翼展方向位移。

3. 发明申请

WO2016126301A3 ACTIVE FLOW CONTROL SYSTEM 审中-公开
公开(公告)号：WO2016126301A3
公开(公告)日：2016-08-11
申请号：PCT/US2015/061600
申请日：2015-11-19
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： WAKE, Brian E. , MATALANIS, Claude G. , BOWLES, Patrick
IPC分类号： B64C23/06 , B64C7/00
摘要： An aircraft is provided and includes a fuselage including a top and a tail, a main rotor apparatus disposed at the top of the fuselage, which rotates one or more rotors to generate lift, and an active flow control (AFC) system. The AFC system includes plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and/or at the tail of the fuselage.

4. 发明申请

WO2015084624A1 BOUNDARY LAYER INGESTING BLADE 审中-公开
标题翻译：边界层植物叶片
公开(公告)号：WO2015084624A1
公开(公告)日：2015-06-11
申请号：PCT/US2014/067140
申请日：2014-11-24
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： MOFFITT, Blake Almy , TILLMAN, Thomas G. , WAKE, Brian E. , MIN, Byung-Young , MATALANIS, Claude G.
IPC分类号： B64C11/18
CPC分类号： B64C27/82 , B64C11/18 , B64C2027/8236 , F01D5/14
摘要： A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.
摘要翻译：提供具有跨度的边界层摄取（BLI）叶片，并且包括可连接到轮毂的根部，与轮毂相距一定距离的顶端部分，并且具有俯仰和从根部到翼展方向尺寸延伸的主体尖端部分。根部具有从根部到约70％跨度位置的局部间距，其小于尖端部分处的间距，从而减小限定在根部周围和周围的边界层区域中的局部迎角。

5. 发明授权

EP3077283B1 BOUNDARY LAYER INGESTING BLADE 有权
公开(公告)号：EP3077283B1
公开(公告)日：2018-11-14
申请号：EP14867254.6
申请日：2014-11-24
申请人： Sikorsky Aircraft Corporation
发明人： MOFFITT, Blake Almy , TILLMAN, Thomas G. , WAKE, Brian E. , MIN, Byung-Young , MATALANIS, Claude G.
IPC分类号： B64C11/18 , B64C27/82
CPC分类号： B64C27/82 , B64C11/18 , B64C2027/8236 , F01D5/14
摘要： A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.

6. 发明公开

EP3485161A1 ROTOR BLADE DEFLECTION SENSING SYSTEM 审中-公开
公开(公告)号：EP3485161A1
公开(公告)日：2019-05-22
申请号：EP17828109.3
申请日：2017-05-12
申请人： Sikorsky Aircraft Corporation , United Technologies Corporation
发明人： GEIGER, Derek , KIM, Seung Bum , MATALANIS, Claude G. , WAKE, Brian E. , BOWLES, Patrick
IPC分类号： F03D17/00

7. 发明公开

EP3141473A1 DRAG REDUCTION OF HIGH SPEED AIRCRAFT WITH A COAXIAL-ROTOR SYSTEM 审中-公开
标题翻译： WIDERSTANDSREDUZIERUNG EINES HOCHGESCHWINDIGKEITSFLUGZEUGS MIT EINEM KOAXIALROTORSYSTEM
公开(公告)号：EP3141473A1
公开(公告)日：2017-03-15
申请号：EP16178627.2
申请日：2016-07-08
申请人： Sikorsky Aircraft Corporation
发明人： FLOREA, Razan Virgil , BOWLES, Patrick , BOTROS, Barbara Brenda , MIN, Byung Young , MATALANIS, Claude G. , WAKE, Brian E.
IPC分类号： B64C7/00 , B64C23/00 , B64C27/10
摘要： A rotor hub fairing system (36) for use in a counter-rotating, coaxial rotor system (12) is provided including an upper hub fairing (38) defined about an axis and a lower hub fairing (40) defined about the axis. A shaft fairing (42) is disposed between the upper hub fairing (38) and the lower hub fairing (40). The geometry of the shaft fairing (42) is configured to encourage a wake adjacent the upper hub fairing (38) to form collectively with a wake adjacent the lower hub fairing (40).
摘要翻译：提供一种用于反向旋转同轴转子系统（12）的转子毂整流罩系统（36），其包括绕轴线限定的上轮毂整流装置（38）和绕该轴线限定的下轮毂整流罩（40）。在上部轮毂整流罩（38）和下部轮毂整流罩（40）之间设置有一个整流罩（42）。轴整流罩（42）的几何形状构造成鼓励靠近上部轮毂整流罩（38）的尾迹与靠近下部轮毂整流罩（40）的尾迹集中地形成。

8. 发明授权

EP3141473B1 DRAG REDUCTION OF HIGH SPEED AIRCRAFT WITH A COAXIAL-ROTOR SYSTEM 有权
公开(公告)号：EP3141473B1
公开(公告)日：2020-04-15
申请号：EP16178627.2
申请日：2016-07-08
申请人： Sikorsky Aircraft Corporation
发明人： FLOREA, Razan Virgil , BOWLES, Patrick , BOTROS, Barbara Brenda , MIN, Byung Young , MATALANIS, Claude G. , WAKE, Brian E.
IPC分类号： B64C7/00 , B64C23/00 , B64C27/10

9. 发明公开

EP3224138A2 ACTIVE FLOW CONTROL SYSTEM 审中-公开
标题翻译：主动流量控制系统
公开(公告)号：EP3224138A2
公开(公告)日：2017-10-04
申请号：EP15881391.5
申请日：2015-11-19
申请人： Sikorsky Aircraft Corporation
发明人： WAKE, Brian E. , MATALANIS, Claude G. , BOWLES, Patrick
IPC分类号： B64C23/06 , B64C7/00
CPC分类号： B64C27/10 , B64C7/00 , B64C23/005 , B64C2027/8236 , B64C2230/12 , H05H1/2406 , H05H2001/2412 , Y02T50/166
摘要： An aircraft is provided and includes a fuselage including a top and a tail, a main rotor apparatus disposed at the top of the fuselage, which rotates one or more rotors to generate lift, and an active flow control (AFC) system. The AFC system includes plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and/or at the tail of the fuselage.
摘要翻译：提供了一种飞机，其包括具有顶部和尾部的机身，设置在机身顶部的主旋翼装置以及主动流动控制（AFC）系统，所述主旋翼装置旋转一个或多个旋翼以产生升力。 AFC系统包括等离子体致动器，等离子体致动器被配置为在与主旋翼装置相邻的位置和/或机身的尾部产生等离子体。

10. 发明公开

EP3077283A1 BOUNDARY LAYER INGESTING BLADE 有权
标题翻译：边界层嵌入刀片
公开(公告)号：EP3077283A1
公开(公告)日：2016-10-12
申请号：EP14867254.6
申请日：2014-11-24
申请人： Sikorsky Aircraft Corporation
发明人： MOFFITT, Blake Almy , TILLMAN, Thomas G. , WAKE, Brian E. , MIN, Byung-Young , MATALANIS, Claude G.
IPC分类号： B64C11/18
CPC分类号： B64C27/82 , B64C11/18 , B64C2027/8236 , F01D5/14
摘要： A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.
摘要翻译：提供了具有跨度的边界层摄取（BLI）叶片，并且包括可连接到轮毂的根部部分，可离开所述轮毂一定距离并且具有间距的尖端部分和从根部段沿翼展方向延伸的主体，尖端部分。根部具有从根部至大约70％跨度位置的局部间距，该间距小于尖端部处的间距，从而减小在根部中和其周围限定的边界层区域中的局部迎角。

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