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15 条记录 (耗时 0.05 秒)

    Propulsive anti-torque system for rotorcraft
    6.
    发明授权
    Propulsive anti-torque system for rotorcraft 有权
    旋翼飞机推进式反扭矩系统

    公开(公告)号：US07731121B2

    公开(公告)日：2010-06-08

    申请号：US11662559

    申请日：2004-09-28

    申请人： Dudley E. Smith ,  Walter C. Joiner ,  Paul J. Madej ,  Charles L. Hollimon ,  Daniel B. Robertson

    发明人： Dudley E. Smith ,  Walter C. Joiner ,  Paul J. Madej ,  Charles L. Hollimon ,  Daniel B. 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
    7.
    发明授权
    Proprotor blade with leading edge slot 有权
    Proprotor刀片带前缘槽

    公开(公告)号：US07594625B2

    公开(公告)日：2009-09-29

    申请号：US10543222

    申请日：2003-01-23

    申请人： Daniel B. Robertson ,  Dudley E. Smith ,  Charles L. Hollimon ,  Jimmy C. Narramore ,  Robert B. Mullins

    发明人： Daniel B. Robertson ,  Dudley E. Smith ,  Charles L. Hollimon ,  Jimmy C. Narramore ,  Robert B. Mullins

    IPC分类号： B64C39/00

    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。

    Rotorcraft with variable incident wing
    8.
    发明授权
    Rotorcraft with variable incident wing 有权
    具有可变事件翼的转子

    公开(公告)号：US08251305B2

    公开(公告)日：2012-08-28

    申请号：US12866904

    申请日：2009-02-11

    申请人： Dudley E. Smith ,  Walter C. Joiner ,  Daniel B. Robertson ,  David J. Ludolph ,  Jennifer D. Langston

    发明人： Dudley E. Smith ,  Walter C. Joiner ,  Daniel B. Robertson ,  David J. Ludolph ,  Jennifer D. Langston

    IPC分类号： B64C27/28

    CPC分类号： B64C37/00 ,  B64C3/385 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C29/0033

    摘要： A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position.

    摘要翻译： 双转子并排复合旋翼航空器具有机身和可变入射翼组件，其相对于机身枢转。 该飞机还具有起落架组件和尾翼组件。 可变入射翼组件枢转地附接到机身，并且包括机翼构件，固定地安装到翼构件或旋翼航空器的另一区域的发动机以及相对于翼构件以固定角度附接的桅杆。 然后发动机也可能位于机身附近或旋翼航空器的另一个区域。 可变入射翼组件能够围绕枢转轴线枢转，从而允许至少在悬停桅杆位置和向前桅杆位置的桅杆取向。 当桅杆处于向前飞行桅杆位置时，转子提供额外的向前推力，并且翼部提供额外的升力。

    Rotorcraft with Variable Incident Wing
    9.
    发明申请
    Rotorcraft with Variable Incident Wing 有权
    具有可变事件翼的转子

    公开(公告)号：US20100327123A1

    公开(公告)日：2010-12-30

    申请号：US12866904

    申请日：2009-02-11

    申请人： Dudley E. Smith ,  Walter C. Joiner ,  Daniel B. Robertson ,  David J. Ludolph ,  Jennifer D. Langston

    发明人： Dudley E. Smith ,  Walter C. Joiner ,  Daniel B. Robertson ,  David J. Ludolph ,  Jennifer D. Langston

    IPC分类号： B64C27/22

    CPC分类号： B64C37/00 ,  B64C3/385 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C29/0033

    摘要： A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position.

    摘要翻译： 双转子并排复合旋翼航空器具有机身和可变入射翼组件，其相对于机身枢转。 该飞机还具有起落架组件和尾翼组件。 可变入射翼组件枢转地附接到机身，并且包括机翼构件，固定地安装到翼构件或旋翼航空器的另一区域的发动机以及相对于翼构件以固定角度附接的桅杆。 然后发动机也可能位于机身附近或旋翼航空器的另一个区域。 可变入射翼组件能够围绕枢转轴线枢转，从而允许至少在悬停桅杆位置和向前桅杆位置的桅杆取向。 当桅杆处于向前飞行桅杆位置时，转子提供额外的向前推力，并且翼部提供额外的升力。

    Anti-torque nozzle system with internal sleeve valve for a rotorcraft
    10.
    发明授权
    Anti-torque nozzle system with internal sleeve valve for a rotorcraft 有权
    具有用于旋翼航空器的内部套筒阀的反扭矩喷嘴系统

    公开(公告)号：US08636243B2

    公开(公告)日：2014-01-28

    申请号：US13580532

    申请日：2010-11-12

    申请人： Daniel B. Robertson

    发明人： Daniel B. Robertson

    IPC分类号： B64C15/00 ,  B64C27/82

    CPC分类号： B64C27/82 ,  B64C2027/8245 ,  B64C2027/829

    摘要： The system of the present application includes a duct for receiving airflow from within a duct portion of a tailboom. The airflow is a mixture of fan driven air and engine exhaust. The system includes a fixed nozzle assembly with an anti-torque nozzle, a pro-torque nozzle and a thrust nozzle. A rotating sleeve valve is located within the fixed nozzle assembly. The rotating sleeve valve located within the fixed nozzle assembly and is configured to selectively redirect airflow into one or more of the anti-torque nozzle, the pro-torque nozzle and the thrust nozzle.

    摘要翻译： 本申请的系统包括用于从尾巴的管道部分内接收气流的管道。 气流是风扇驱动的空气和发动机排气的混合物。 该系统包括具有抗扭矩喷嘴，预扭矩喷嘴和推力喷嘴的固定喷嘴组件。 旋转套筒阀位于固定喷嘴组件内。 位于固定喷嘴组件内的旋转套筒阀被构造成选择性地将气流重定向到一个或多个抗扭矩喷嘴，前扭矩喷嘴和推力喷嘴中。