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    Primary flight controls
    3.
    发明授权
    Primary flight controls 有权
    主要飞行控制

    公开(公告)号：US08888036B2

    公开(公告)日：2014-11-18

    申请号：US13534193

    申请日：2012-06-27

    申请人： Bruno Chaduc ,  Boris Grohmann ,  Christophe Tempier

    发明人： Bruno Chaduc ,  Boris Grohmann ,  Christophe Tempier

    IPC分类号： B64C11/00 ,  B64C27/68 ,  B64C27/64 ,  B64C27/625 ,  B64C13/50

    CPC分类号： B64C27/625 ,  B64C13/503 ,  B64C27/64 ,  B64C27/68 ,  Y02T50/44

    摘要： Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).

    摘要翻译： 用于直升机的主和/或尾转子（4）的主飞行控制（10），其具有在线控和/或飞越控制之间的电 - 机械接口和用于控制力的液压伺服致动器（8） 朝向所述主和/或尾部转子控制器（4）的放大。 对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械联动装置（7）连接到一个电动马达（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）和其输出端（30）的一个机械连杆（7）和一个电动机（5）是直接驱动型的类型，所述电动马达（5）的位置 ）和所述电动马达（5）传递到所述液压伺服驱动器（8）的扭矩与所述电动马达（5）的功率消耗有关。

    Helicopter with main and auxiliary rotors
    4.
    发明申请
    Helicopter with main and auxiliary rotors 有权
    直升机与主和辅助转子

    公开(公告)号：US20100130093A1

    公开(公告)日：2010-05-27

    申请号：US12323209

    申请日：2008-11-25

    申请人： Alexander Jozef Magdalena Van de Rostyne ,  Chi Pok Billy WAI

    发明人： Alexander Jozef Magdalena Van de Rostyne ,  Chi Pok Billy WAI

    IPC分类号： A63H27/133

    CPC分类号： A63H27/12 ,  B64C27/605 ,  B64C27/625

    摘要： A remote control toy helicopter has a main rotor and an auxiliary rotor both driven by a rotor shaft. The auxiliary rotor has elongated elements at an acute angle relative to blades of the main rotor. A control system is provided that includes an actuator for engaging with a control assembly depending from the auxiliary rotor. The inter-engagement of the actuator and the control assembly effects change in the angle of incidence of the elongated elements of the auxiliary rotor. The interaction occurs when the assembly engages with the actuator by a depending arm associated with the assembly.

    摘要翻译： 遥控玩具直升机具有由转子轴驱动的主转子和辅助转子。 辅助转子相对于主转子的叶片具有锐角的细长元件。 提供了一种控制系统，其包括用于与从辅助转子悬挂的控制组件接合的致动器。 致动器和控制组件的相互接合效应改变了辅助转子的细长元件的入射角。 当组件通过与组件相关联的悬垂臂与致动器接合时，发生相互作用。

    Helicopter having rotors equipped with flaps
    5.
    发明授权
    Helicopter having rotors equipped with flaps 失效
    直升机具有装有襟翼的转子

    公开(公告)号：US5255871A

    公开(公告)日：1993-10-26

    申请号：US44027

    申请日：1993-04-08

    申请人： Minoru Ikeda

    发明人： Minoru Ikeda

    IPC分类号： B64C27/615 ,  B64C27/625 ,  B64C27/57

    CPC分类号： B64C27/625 ,  B64C27/615 ,  Y02T50/34

    摘要： A helicopter comprises a pair of rotors each having a flap hinged to one of its edges, a seesaw rod swingably supported above the rotors, a pair of auxiliary wings fixed to opposite ends of the seesaw rod, and a pair of connecting rods each connecting one of the flaps with seesaw rod above it. When the lift produced by one of the rotors becomes larger than that produced by the other, the auxiliary wing located above the rotor producing the larger lift rises and turns up the flap of the rotor to reduce its flap effect and decrease the rotor lift, while the auxiliary wing located above the rotor producing the smaller lift lowers and turns down the flap of the rotor to increase its flap effect and raise its lift. As a result, the lifts of the two rotors are regulated.

    摘要翻译： 直升机包括一对转子，每个转子具有铰接到其一个边缘的翼片，摆动地支撑在转子上方的跷跷板，固定到跷跷板杆的相对端的一对辅助翼片和一对连接杆 的襟翼与其上的跷跷板。 当由一个转子产生的升力变得大于由另一转子产生的升力时，产生较大升力的转子上方的辅助翼升高并转动转子的翼片以减小其挡板效应并减小转子升力，同时 位于转子上方的辅助翼产生较小的升力降低并且转动转子的翼片以增加其翼片效应并提升其升力。 结果，两个转子的升降机受到规范。

    PRIMARY FLIGHT CONTROLS
    7.
    发明申请
    PRIMARY FLIGHT CONTROLS 有权
    主要飞行控制

    公开(公告)号：US20130168501A1

    公开(公告)日：2013-07-04

    申请号：US13534193

    申请日：2012-06-27

    申请人： Bruno Chaduc ,  Boris Grohmann ,  Christophe Tempier

    发明人： Bruno Chaduc ,  Boris Grohmann ,  Christophe Tempier

    IPC分类号： B64C27/625

    CPC分类号： B64C27/625 ,  B64C13/503 ,  B64C27/64 ,  B64C27/68 ,  Y02T50/44

    摘要： Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).

    摘要翻译： 用于直升机的主和/或尾转子（4）的主飞行控制（10），其具有在线控和/或飞越控制之间的电 - 机械接口和用于控制力的液压伺服致动器（8） 朝向所述主和/或尾部转子控制器（4）的放大。 对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械联动装置（7）连接到一个电动马达（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）和其输出端（30）的一个机械连杆（7）和一个电动机（5）是直接驱动型的类型，所述电动马达（5）的位置 ）和所述电动马达（5）传递到所述液压伺服驱动器（8）的扭矩与所述电动马达（5）的功率消耗有关。

    ROTOR ASSEMBLY
    8.
    发明申请
    ROTOR ASSEMBLY 有权
    转子总成

    公开(公告)号：US20120230824A1

    公开(公告)日：2012-09-13

    申请号：US13509403

    申请日：2010-11-15

    申请人： Petter Muren

    发明人： Petter Muren

    IPC分类号： F04D29/36 ,  B64C27/04

    CPC分类号： B64C27/605 ,  A63H27/12 ,  B64C27/625

    摘要： A rotor assembly for helicopter vehicles for stabilizing the aircraft and thus providing an easy way of controlling pitch and roll of the aircraft by respectively associated magnetic actuators. The rotor assembly comprises a rotor with two flexible rotor blades, a rotor head rotationally coupled to the rotor shaft, a rotating swash plate, with at least three fly bars extending therefrom. The swash plate is rotationally coupled to the rotor shaft and adjusted to tilt in all directions relative to a plane perpendicular to the rotor shaft. The rotor head is hinged to the rotor shaft in one direction so that the rotor head and the rotor blades jointly are not able to tilt around their transversal axis. The coupling between the rotating swash plate and the rotor head provide synchronized tilt movements between the rotor head and the rotating swash plate around the longitudinal axis of the rotor head.

    摘要翻译： 用于直升机车辆的转子组件，用于稳定飞行器，并且因此提供了一种通过分别相关联的磁致动器来控制飞行器的俯仰和滚动的简单方法。 转子组件包括具有两个柔性转子叶片的转子，与转子轴旋转耦合的转子头，旋转的斜盘，其中至少有三个从其延伸的飞杆。 斜盘旋转地联接到转子轴并且被调节成相对于垂直于转子轴的平面在所有方向上倾斜。 转子头在一个方向上铰接到转子轴上，使得转子头和转子叶片不能围绕它们的横向轴线倾斜。 旋转斜盘和转子头之间的联接在转子头部和旋转斜盘之间提供同步的倾斜运动，围绕转子头部的纵向轴线。

    Single rotor model helicopter with improved stability behavior
    9.
    发明授权
    Single rotor model helicopter with improved stability behavior 有权
    单转子模型直升机具有改进的稳定性行为

    公开(公告)号：US08177600B2

    公开(公告)日：2012-05-15

    申请号：US12732004

    申请日：2010-03-25

    申请人： Guochuan Huang ,  Yuchen Wu ,  Yizhen Yu ,  Huanzhong Ding

    发明人： Guochuan Huang ,  Yuchen Wu ,  Yizhen Yu ,  Huanzhong Ding

    IPC分类号： A63H27/127

    CPC分类号： A63H27/12 ,  B64C27/43 ,  B64C27/625

    摘要： A single rotor model helicopter is provided, comprising a spindle, a rotor clamp disposed on the spindle, a pair of rotor blades disposed on the rotor clamp, and a pair of hybrid control rocker arms. The helicopter further includes an operating system and a balancing system. The pair of hybrid control rocker arms are disposed on both sides of the rotor clamp respectively and rotatably connected to a pitch control rocker arm through each axial hole located on a center of each hybrid control rocker arm, so as to control attack angles of the rotor blades. Each hybrid control rocker arm has two control points. A first pair of control points diagonally opposite each other in the pair of hybrid control rocker arms are controlled by a cyclic torque transmitted from the operating system, and a second pair of control points diagonally opposite each other are controlled by the balancing system. Furthermore, the second pair of control points controlled by the balancing system and the first pair of control points controlled by a swash plate can move relative to each other as mutual fulcrums. The single rotor model helicopter of the present application can separately adjust operating sensitivity and stability, thereby finding an optimum combination of dynamic stability and maneuverability of the model helicopter.

    摘要翻译： 提供单转子模型直升机，包括主轴，设置在主轴上的转子夹具，设置在转子夹具上的一对转子叶片和一对混合控制摇臂。 直升机还包括操作系统和平衡系统。 一对混合控制摇臂分别设置在转子夹具的两侧，分别通过位于每个混合控制摇臂的中心的每个轴孔可旋转地连接到俯仰控制摇臂，以便控制转子的撞击角 刀片。 每个混合控制摇臂具有两个控制点。 在一对混合控制摇臂中彼此对角地对置的第一对控制点由从操作系统发送的循环扭矩控制，并且由对平衡系统控制对角彼此的第二对控制点。 此外，由平衡系统控制的第二对控制点和由斜盘控制的第一对控制点可相对于彼此作为相互支点移动。 本应用单转子模型直升机可以分别调整运行灵敏度和稳定性，从而找到模型直升机的动态稳定性和机动性的最佳组合。

    SINGLE ROTOR MODEL HELICOPTER WITH IMPROVED STABILITY BEHAVIOR
    10.
    发明申请
    SINGLE ROTOR MODEL HELICOPTER WITH IMPROVED STABILITY BEHAVIOR 有权
    单转子型号直升机具有改进的稳定性行为

    公开(公告)号：US20100178836A1

    公开(公告)日：2010-07-15

    申请号：US12732004

    申请日：2010-03-25

    申请人： Guochuan HUANG ,  Yuchen Wu ,  Yizhen Yu ,  Huanzhong Ding

    发明人： Guochuan HUANG ,  Yuchen Wu ,  Yizhen Yu ,  Huanzhong Ding

    IPC分类号： A63H27/127

    CPC分类号： A63H27/12 ,  B64C27/43 ,  B64C27/625

    摘要： A single rotor model helicopter is provided, comprising a spindle, a rotor clamp disposed on the spindle, a pair of rotor blades disposed on the rotor clamp, and a pair of hybrid control rocker arms. The helicopter further includes an operating system and a balancing system. The pair of hybrid control rocker arms are disposed on both sides of the rotor clamp respectively and rotatably connected to a pitch control rocker arm through each axial hole located on a center of each hybrid control rocker arm, so as to control attack angles of the rotor blades. Each hybrid control rocker arm has two control points. A first pair of control points diagonally opposite each other in the pair of hybrid control rocker arms are controlled by a cyclic torque transmitted from the operating system, and a second pair of control points diagonally opposite each other are controlled by the balancing system. Furthermore, the second pair of control points controlled by the balancing system and the first pair of control points controlled by a swash plate can move relative to each other as mutual fulcrums. The single rotor model helicopter of the present application can separately adjust operating sensitivity and stability, thereby finding an optimum combination of dynamic stability and maneuverability of the model helicopter.

    摘要翻译： 提供单转子模型直升机，包括主轴，设置在主轴上的转子夹具，设置在转子夹具上的一对转子叶片和一对混合控制摇臂。 直升机还包括操作系统和平衡系统。 一对混合控制摇臂分别设置在转子夹具的两侧，分别通过位于每个混合控制摇臂的中心的每个轴孔可旋转地连接到俯仰控制摇臂，以便控制转子的撞击角 刀片。 每个混合控制摇臂具有两个控制点。 在一对混合控制摇臂中彼此对角地对置的第一对控制点由从操作系统发送的循环扭矩控制，并且由对平衡系统控制对角彼此的第二对控制点。 此外，由平衡系统控制的第二对控制点和由斜盘控制的第一对控制点可相对于彼此作为相互支点移动。 本应用单转子模型直升机可以分别调整运行灵敏度和稳定性，从而找到模型直升机的动态稳定性和机动性的最佳组合。