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1. 发明申请

WO2008008051A2 SYSTEM AND METHOD FOR IMPROVED ROTARY-WING AIRCRAFT PERFORMANCE WITH INTERIOR/EXTERNAL LOADS 审中-公开
标题翻译：用于内部/外部负载的改进的旋转飞行器性能的系统和方法
公开(公告)号：WO2008008051A2
公开(公告)日：2008-01-17
申请号：PCT/US2006/024494
申请日：2006-06-22
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： BRAINARD, Steven, J. , HOUY, David, R. , STOBIECKI, Anthony, Z. , SCOTT, Mark, W. , WEINER, Steven, D.
IPC分类号： C08K3/04
CPC分类号： B64D1/22 , G01D7/02 , G01M1/127 , G05D1/0858
摘要： An interactive aircraft load management system automates calculation and provides simulation capability to changes in an aircraft CG. limit for display on a three-dimensional aircraft symbology. The aircraft load management system also communicates with a fly by wire (FBW) flight control system wherein the aircraft's control system is programmed to automatically compensate for CG. excursions and to alter control laws. The aircraft load management system also selectively reels-in and reels out sling lines as the aircraft pitches and rolls to maintain a load vector from a slung load along the aircraft centerline. Load vector travel is accomplished by coupling a winch control system into the flight control system.
摘要翻译：交互式飞机负载管理系统自动计算并提供飞机CG变化的仿真能力。限制在三维飞机符号系统上显示。飞机负载管理系统还与飞行（FBW）飞行控制系统进行通信，其中飞行器的控制系统被编程为自动补偿CG。游览和改变控制法。飞机负载管理系统还可以选择性地卷起并卷起吊索，因为飞机的间距和滚动以沿着飞机中心线从静止载荷维持载荷矢量。通过将绞盘控制系统连接到飞行控制系统来实现负载矢量行驶。

2. 发明申请

WO2017123294A1 REDUCED BLADE VORTEX INTERACTION 审中-公开
标题翻译：减少叶片涡旋相互作用
公开(公告)号：WO2017123294A1
公开(公告)日：2017-07-20
申请号：PCT/US2016/056514
申请日：2016-10-12
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： SARGENT, Daniel, C. , SCOTT, Mark, W.
IPC分类号： B64C27/46 , B64C27/32
CPC分类号： B64C27/46 , B64C11/16 , B64C21/04 , Y02T50/166
摘要： A blade includes an elongated body having a leading edge, a trailing edge, a root end, and a tip end, a fluid inlet arranged closer to the root end than the fluid outlet, a fluid outlet arranged near the tip end of the elongated body, and a centrifugal air flow channel defined within the body between the inlet and the outlet to direct air from the inlet to the outlet to issue the flow when the rotor blade is rotating in a rotational path. The blade also includes a valve to selectively open and close the centrifugal air flow channel to selectively issue the flow and change a blade vortex issuing from the rotor blade at discrete portions of the rotational path of the rotor blade. A controller can be operatively connected to the valve to control the valve to open and close the centrifugal air flow channel.
摘要翻译：叶片包括具有前缘，后缘，根端和末端的细长本体，布置成比流体出口更靠近根端的流体入口，布置的流体出口靠近细长本体的末端，以及离心空气流动通道，限定在本体内在入口和出口之间以将空气从入口引导至出口以在转子叶片在旋转路径中旋转时发出流动。叶片还包括阀门，以选择性地打开和关闭离心气流通道，以选择性地发出流动并且改变在转子叶片的旋转路径的离散部分处从转子叶片发出的叶片涡流。控制器可以可操作地连接到阀门，以控制阀门打开和关闭离心气流通道。

3. 发明申请

WO2017083089A1 ROTOR BLADE STRUCTURES 审中-公开
标题翻译：转子叶片结构
公开(公告)号：WO2017083089A1
公开(公告)日：2017-05-18
申请号：PCT/US2016/058564
申请日：2016-10-25
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： THOMAS, Justin , KOPANSKI, Krzysztof , SCOTT, Mark, W.
IPC分类号： B64C27/72 , B64C27/46 , B64C27/473 , B64C27/54 , B64C27/59 , B64C27/64
CPC分类号： B64C27/72 , B64C27/473 , B64C27/54 , B64C27/64 , B64C2027/7272 , Y02T50/34
摘要： A closeout structure for a rotor blade includes a first fluid channel for supplying a first pressure to a first port of a trailing edge (TE) device, a second fluid channel for supplying a second pressure to a second port of the TE de vice, and a trough disposed between the first fluid channel and the second fluid channel. The closeout structure forms a double- W shape.
摘要翻译：用于转子叶片的封闭结构包括用于向后缘（TE）装置的第一端口提供第一压力的第一流体通道，用于向第二端口提供第二压力的第二流体通道 TE设备的出入口以及设置在第一流体通道和第二流体通道之间的槽。收尾结构形成双W形。

4. 发明申请

WO2008018912A2 RADIO FREQUENCY EMITTING HOOK SYSTEM FOR A ROTARY-WING AIRCRAFT EXTERNAL LOAD HANDLING 审中-公开
标题翻译：用于旋转式飞机外部负载处理的无线电频率发射钩系统
公开(公告)号：WO2008018912A2
公开(公告)日：2008-02-14
申请号：PCT/US2007/002723
申请日：2007-01-31
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： EADIE, William, J. , SCOTT, Mark, W.
IPC分类号： B64D9/00
CPC分类号： B64D1/22 , B66C13/063 , B66C13/46
摘要： An aircraft load management system that determines the position of an aircraft cargo hook for display to an aircrew. The cargo hook positional information may alternatively or additionally be communicated directly to a flight control system and a winch control system to automate and coordinate flight control inputs with winch operation to actively position the cargo hook. Data transfer from the cargo through a data link system also provides the load management system with exact position of the cargo load connection points even prior to attachment of the cargo hook to the load. The load management system also includes anti-sway algorithms for active load stability inputs to the flight control system and to alter flight control laws and automatically compensate for CG. excursions.
摘要翻译：航空器负载管理系统，用于确定飞机货物挂钩的位置，以显示给机组人员。货钩位置信息可以替代地或附加地直接传达到飞行控制系统和绞盘控制系统，以通过绞车操作自动化和协调飞行控制输入，以主动定位货物吊钩。通过数据链接系统从货物的数据传输，即使在将货钩连接到负载之前，也可以使负载管理系统具有货物负载连接点的精确位置。负载管理系统还包括用于飞行控制系统的主动负载稳定性输入的反摆动算法，并改变飞行控制规律并自动补偿CG。游览。

5. 发明申请

WO2003027789A1 FLIGHT CONTROL SYSTEM FOR A HYBRID AIRCRAFT IN A TRANSITION REGION 审中-公开
标题翻译：过渡区混合飞机飞行控制系统
公开(公告)号：WO2003027789A1
公开(公告)日：2003-04-03
申请号：PCT/US2002/030555
申请日：2002-09-25
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： KINKEAD, W., Douglas , SCOTT, Mark, W.
IPC分类号： G05D1/08
CPC分类号： G05D1/0858
摘要： A flight control system (24) includes a blending algorithm (74) which evaluates the current flight regime and determines the effectiveness of the flight controls to effect the rotational moment of a hybrid vehicle about the pitch axis. Gain schedules for both pitch cyclic and elevator control provide a quantitative measure of control effectiveness. Based on the respective gain schedules, the algorithm determines how much of the control commands should be sent to each control surface. The result is that for a given control command, the same amount of pitch moment will be generated regardless of flight regime. A lift control algorithm selectively communicates with the pitch command of the flight system control algorithm. The lift control algorithm selects the proper control commands to coordinate an effective transition between hover and forward flight. The most efficient vehicle pitch during transition is thereby automatically generated so that sufficient lift and control throughout the transition between rotor borne and wing borne flight.
摘要翻译：飞行控制系统（24）包括混合算法（74），其对当前飞行状态进行评估，并确定飞行控制器实现混合动力车辆围绕俯仰轴的旋转力矩的有效性。音调循环和电梯控制的增益调度提供了控制有效性的定量测量。基于相应的增益计划，该算法确定应将多少控制命令发送到每个控制表面。结果是，对于给定的控制命令，将产生相同数量的俯仰力矩，而不管飞行状态如何。升降机控制算法选择性地与飞行系统控制算法的俯仰命令通信。升降机控制算法选择适当的控制命令来协调悬停和前进飞行之间的有效过渡。因此，在转换期间最有效的车辆间距由此自动产生，使得在转子承载和机翼飞行之间的过渡期间具有足够的提升和控制。

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