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13 条记录 (耗时 0.022 秒)

    Propulsive Anti-Torque System for Rotorcraft
    1.
    发明申请
    Propulsive Anti-Torque System for Rotorcraft 有权
    旋翼机推进式反扭矩系统

    公开(公告)号：US20080093500A1

    公开(公告)日：2008-04-24

    申请号：US11662559

    申请日：2004-09-28

    申请人： Dudley Smith ,  Walter Joiner ,  Paul Madej ,  Charles Hollimon ,  Daniel Robertson

    发明人： Dudley Smith ,  Walter Joiner ,  Paul Madej ,  Charles Hollimon ,  Daniel Robertson

    IPC分类号： B64C27/82

    CPC分类号： B64C27/82 ,  B64C2027/8245

    摘要： A rotorcraft having an enhanced configuration in which a simple wing and a propulsive anti-torque system are combined is disclosed. The propulsive anti-torque system includes an anti-torque thruster system in which a variable pitch fan is installed internal to the tail boom of the rotorcraft and an anti-torque thruster nozzle is mounted at the extremity of the tail boom. The fan is driven directly from the main rotor drive. The configuration and location of the fan allows the primary exhaust from the engine to be mixed with the compressed air flow from the fan. The mixed air flow from the fan and the engine passes through the tail boom and out the thruster nozzle.

    摘要翻译： 公开了一种具有增强结构的旋翼航空器，其中简单翼和推进式反扭矩系统组合在一起。 推进式反扭矩系统包括抗扭矩推进器系统，其中可变桨距风扇安装在旋翼航空器尾翼的内部，反扭矩推进器喷嘴安装在尾吊臂的末端。 风扇直接从主转子驱动器驱动。 风扇的配置和位置允许来自发动机的主排气与来自风扇的压缩空气流混合。 来自风扇和发动机的混合空气流通过尾部悬臂并从推进器喷嘴出来。

    Proprotor blade with leading edge slot
    2.
    发明申请
    Proprotor blade with leading edge slot 有权
    Proprotor刀片带前缘槽

    公开(公告)号：US20060239824A1

    公开(公告)日：2006-10-26

    申请号：US10543222

    申请日：2003-01-23

    申请人： Daniel Robertson ,  Dudley Smith ,  Charles Hollimon ,  Jimmy Narramore ,  B. Mullins

    发明人： Daniel Robertson ,  Dudley Smith ,  Charles Hollimon ,  Jimmy Narramore ,  B. Mullins

    IPC分类号： A23L3/18

    CPC分类号： B64C11/16 ,  B64C27/467 ,  B64C29/0033

    摘要： A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so the a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades.

    摘要翻译： 公开了一种具有固定的，翼展方向的前缘槽（215）的推进器叶片（27a，27b，127a，127b），其位于至少在推进器的内侧部分中。 狭槽215由位于驱动器叶片的主要部分的前缘（202）上的选择性形状的凹入区域（219）中的选择性地成形的板条（217）形成。 狭槽215被选择成形，使得在推进器叶片的下翼面表面上的气流的一部分在推进器叶片的主要部分和板条（217）之间转向并在推进器的上部翼型表面处离开 刀。 本发明可以用于军用型倾转旋翼飞机（11）和民用型倾转旋翼飞机（111），只有微小的变化来适应不同形状的推进器叶片。

    Method and Apparatus for In-Flight Blade Folding
    8.
    发明申请
    Method and Apparatus for In-Flight Blade Folding 有权
    飞行刀片折叠的方法和装置

    公开(公告)号：US20120292456A1

    公开(公告)日：2012-11-22

    申请号：US13576612

    申请日：2010-06-15

    申请人： Charles Hollimon ,  Dudley E. Smith ,  David Ludolph

    发明人： Charles Hollimon ,  Dudley E. Smith ,  David Ludolph

    IPC分类号： B64C27/30 ,  B64C11/28 ,  B64C27/26 ,  F01D7/00

    CPC分类号： B64C29/0033 ,  B64C27/28 ,  B64C27/30

    摘要： A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft.

    摘要翻译： 一种用于旋翼航空器的可折叠转子系统，所述可折叠转子系统包括与驱动轴可操作地相关联的转子组件，所述驱动轴可与发动机相关联，所述转子组件包括连接到夹紧销的转子叶片。 旋转斜盘可操作地与夹紧销相关联，以便选择性地改变转子叶片的间距。 叶片折叠致动器可操作地与抓持销相关联，使得叶片折叠致动器构造成围绕叶片折叠轴线折叠和展开转子叶片。 在飞机模式期间，旋翼航空器可以停止和折叠转子叶片，使得旋翼飞机依靠来自发动机的推力用于推进。 转子叶片以螺旋折叠路径折叠，使得转子叶片在折叠过程中保持基本上沿边缘或羽状。 螺旋折叠路径使转子叶片在旋翼飞机飞行期间被折叠时所经历的空气动力学阻力最小化。

    Engine Exhaust System with Directional Nozzle
    9.
    发明申请
    Engine Exhaust System with Directional Nozzle 有权
    具有方向喷嘴的发动机排气系统

    公开(公告)号：US20110131948A1

    公开(公告)日：2011-06-09

    申请号：US12303970

    申请日：2007-06-11

    申请人： Charles Hollimon ,  John Barber ,  John Sherrer ,  Robert Laramee

    发明人： Charles Hollimon ,  John Barber ,  John Sherrer ,  Robert Laramee

    IPC分类号： F02K1/00

    CPC分类号： F02K1/004 ,  B64D33/04 ,  F02C7/20 ,  F02K1/36 ,  F02K1/52 ,  F02K1/805 ,  F05D2220/329 ,  F05D2230/642 ,  F05D2250/40 ,  F05D2260/54

    摘要： An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The secondary duct has a portion selectively rotatable relative to the remainder of the secondary duct for directing the exhaust gas vector. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.

    摘要翻译： 用于飞行器的排气系统具有用于将来自发动机排气出口的废气连通并且被构造成与发动机一起运动的主排气管道。 二次排气管道与主排气管道流体连通并且可移动地安装到机身。 次级管道具有相对于辅助管道的其余部分选择性地可旋转的部分，用于引导废气向量。 该系统具有用于维持主管道和次管道之间的大致一致的相对对准的装置。

    Method and apparatus for in-flight blade folding
    10.
    发明授权
    Method and apparatus for in-flight blade folding 有权
    飞行刀片折叠的方法和装置

    公开(公告)号：US08998125B2

    公开(公告)日：2015-04-07

    申请号：US13576612

    申请日：2010-06-15

    申请人： Charles Hollimon ,  Dudley E. Smith ,  David Ludolph

    发明人： Charles Hollimon ,  Dudley E. Smith ,  David Ludolph

    IPC分类号： B64C27/28 ,  B64C29/00 ,  B64C27/30

    CPC分类号： B64C29/0033 ,  B64C27/28 ,  B64C27/30

    摘要： A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft.

    摘要翻译： 一种用于旋翼航空器的可折叠转子系统，所述可折叠转子系统包括与驱动轴可操作地相关联的转子组件，所述驱动轴可与发动机相关联，所述转子组件包括连接到夹紧销的转子叶片。 旋转斜盘可操作地与夹紧销相关联，以便选择性地改变转子叶片的间距。 叶片折叠致动器可操作地与抓持销相关联，使得叶片折叠致动器构造成围绕叶片折叠轴线折叠和展开转子叶片。 在飞机模式期间，旋翼航空器可以停止和折叠转子叶片，使得旋翼飞机依靠来自发动机的推力用于推进。 转子叶片以螺旋折叠路径折叠，使得转子叶片在折叠过程中保持基本上沿边缘或羽状。 螺旋折叠路径使转子叶片在旋翼飞机飞行期间被折叠时所经历的空气动力学阻力最小化。