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435 条记录 (耗时 0.026 秒)

    Rotorcraft with a fuselage and at least one main rotor
    12.
    发明授权
    Rotorcraft with a fuselage and at least one main rotor 有权
    转子陀飞轮与机身和至少一个主转子

    公开(公告)号：US09527577B2

    公开(公告)日：2016-12-27

    申请号：US14605097

    申请日：2015-01-26

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Martin Embacher

    IPC分类号： B64C5/16 ,  B64C3/38 ,  B64C27/04 ,  B64C27/82

    CPC分类号： B64C5/16 ,  B64C3/385 ,  B64C27/04 ,  B64C27/82 ,  B64C2027/8236 ,  Y02T50/14

    摘要： A rotorcraft with a fuselage and at least one main rotor, the at least one main rotor being drivable for controlling an associated pitch attitude of the rotorcraft in operation, and the fuselage being equipped with at least one passive wing-type aerodynamic device that is adapted for generating independently of the associated pitch attitude a lift force acting on the fuselage, the lift force being oriented perpendicular to an air flow that is directed in operation of the rotorcraft against the passive wing-type aerodynamic device.

    摘要翻译： 一种具有机身和至少一个主转子的旋翼航空器，所述至少一个主转子可驱动，用于控制所述旋翼航空器在运行中的相关俯仰姿态，并且所述机身装备有至少一个被动式翼型空气动力学装置， 为了独立于相关联的俯仰姿态产生作用在机身上的提升力，提升力垂直于在旋转航空器的操作中被引导以抵抗被动翼型空气动力学装置的空气流定向。

    Variable geometry aircraft wing supported by struts and/or trusses
    14.
    发明授权
    Variable geometry aircraft wing supported by struts and/or trusses 有权
    可变几何飞机机翼由支柱和/或桁架支撑

    公开(公告)号：US09327822B1

    公开(公告)日：2016-05-03

    申请号：US14179401

    申请日：2014-02-12

    申请人： The United States of America as Represented by the Administrator of the National Aeronautics & Space Administration (NASA)

    发明人： John E. Melton ,  Michael R. Dudley

    IPC分类号： B64C3/38

    CPC分类号： B64C3/385 ,  B64C3/40 ,  Y02T50/14

    摘要： The present invention provides an aircraft having variable airframe geometry for accommodating efficient flight. The aircraft includes an elongated fuselage, an oblique wing pivotally connected with said fuselage, a wing pivoting mechanism connected with said oblique wing and said fuselage, and a brace operably connected between said oblique wing and said fuselage. The present invention also provides an aircraft having an elongated fuselage, an oblique wing pivotally connected with said fuselage, a wing pivoting mechanism connected with said oblique wing and said fuselage, a propulsion system pivotally connected with said oblique wing, and a brace operably connected between said propulsion system and said fuselage.

    摘要翻译： 本发明提供一种具有可变的机身几何形状以适应有效飞行的飞行器。 飞机包括细长的机身，与所述机身枢转连接的倾斜翼，与所述倾斜翼和所述机身连接的翼转动机构，以及可操作地连接在所述倾斜翼与所述机身之间的支架。 本发明还提供一种飞行器，其具有细长机身，与所述机身枢转连接的倾斜翼，与所述倾斜翼和所述机身连接的翼转动机构，与所述倾斜翼枢转连接的推进系统，以及可操作地连接在 说推进系统和机身。

    Aircraft with C-Shaped Carrier Surfaces and Movable Top Surfaces
    15.
    发明申请
    Aircraft with C-Shaped Carrier Surfaces and Movable Top Surfaces 审中-公开
    具有C形载体表面和可移动顶面的飞机

    公开(公告)号：US20160068258A1

    公开(公告)日：2016-03-10

    申请号：US14845909

    申请日：2015-09-04

    申请人： Airbus Defence and Space GmbH

    发明人： Klaus Seywald ,  Andreas Wildschek

    IPC分类号： B64C23/06

    CPC分类号： B64C23/076 ,  B64C3/385 ,  Y02T50/164

    摘要： An aircraft with C-shaped carrier surfaces wherein an axis of rotation of top surfaces is arranged in the respective aerodynamic center of the top surfaces, furthermore that each top surface can be adjusted by an adjustment device that can be controlled by a control device, wherein an angle of attack of the top surfaces can be adjusted that is optimal for a minimal induced resistance based on flight state parameters. This arrangement minimizes the adjusting moment during the adjusting of the top surfaces and is independent of the angle of attack of the top surface.

    摘要翻译： 具有C形载体表面的飞机，其中顶表面的旋转轴线布置在顶表面的相应空气动力学中心中，此外，每个顶表面可以由可由控制装置控制的调节装置调节，其中 可以根据飞行状态参数来调节顶表面的攻角，对于最小感应电阻是最佳的。 这种布置使得在顶表面的调节期间的调节力矩最小化，并且独立于顶表面的迎角。

    Aircraft With Integrated Lift And Propulsion System
    16.
    发明申请
    Aircraft With Integrated Lift And Propulsion System 有权
    具有集成升降和推进系统的飞机

    公开(公告)号：US20140191088A1

    公开(公告)日：2014-07-10

    申请号：US14010382

    申请日：2013-08-26

    申请人： Abe Karem

    发明人： Abe Karem

    IPC分类号： B64C27/26

    CPC分类号： B64C29/0033 ,  B64C3/10 ,  B64C3/385 ,  B64C27/28 ,  B64C27/467 ,  Y02T50/12

    摘要： A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior.

    摘要翻译： 垂直起飞和着陆（VTOL）飞机设计得非常高效，使其在100到1000英里范围内的跑道依赖飞机具有商业竞争力。 改进包括高效倾斜转子和机翼设计，可实现垂直起飞和高效巡航，高纵横比翼，以及在悬停和巡航飞行中都有效的变速推进系统。 优选的飞机使用薄的内侧和外侧翼，薄的转子叶片，并且使用有效的轻量级设计来实现异常低的空重部分。 本发明的方法包括利用先进的设计和分析技术，可以准确预测飞机的物理行为。

    Aircraft with its fuselage suspended under the wing
    17.
    发明授权
    Aircraft with its fuselage suspended under the wing 有权
    飞机与机身悬挂在机翼下方

    公开(公告)号：US08336811B2

    公开(公告)日：2012-12-25

    申请号：US12541256

    申请日：2009-08-14

    申请人： Olivier Cazals ,  Thierry Druot

    发明人： Olivier Cazals ,  Thierry Druot

    IPC分类号： B64C37/02

    CPC分类号： B64C1/26 ,  B64C3/38 ,  B64C3/385 ,  B64C3/42 ,  B64C17/00 ,  B64C39/02 ,  B64C39/04 ,  Y02T50/14

    摘要： An aircraft includes a reference system including a longitudinal X axis, a vertical Z axis perpendicular to the X axis, and a lateral Y axis perpendicular to the plane defined by the X and Z axes, a fuselage, a wing affixed to an upper central part of the fuselage, a set of rear airfoils situated behind the wing, and propulsion engines mounted on the wing, where the wing, the set of rear airfoils and the propulsion engines are parts of an aero-propulsive unit forming a structure independent of the fuselage, and where the aero-propulsive unit is connected to the fuselage by a six degrees of freedom connection system using arms with lengths modified to control a position of the aero-propulsive unit relative to the fuselage along the X, Y and Z axes and in rotation about the X, Y and Z axes, during flight.

    摘要翻译： 一种飞机包括一个参考系统，包括纵向X轴，垂直于X轴的垂直Z轴和垂直于由X轴和Z轴限定的平面的横向Y轴，机身，固定到上中心部分的翼 机身后面的一组后翼面，以及安装在机翼上的推进发动机，其中机翼，后翼型组件和推进发动机是形成独立于机身的结构的航空推进单元的部件 ，并且航空推进单元通过六自由度连接系统连接到机身，使用具有修改的长度的臂来控制航空推进单元相对于机身沿着X，Y和Z轴的位置，并且在 在飞行过程中围绕X，Y和Z轴旋转。

    Compound Aircraft with Autorotation
    18.
    发明申请
    Compound Aircraft with Autorotation 失效
    复合飞机与自动化

    公开(公告)号：US20110036954A1

    公开(公告)日：2011-02-17

    申请号：US12757287

    申请日：2010-04-09

    申请人： Frederick W. Piasecki

    发明人： Frederick W. Piasecki

    IPC分类号： B64C27/22 ,  B64C27/26

    CPC分类号： B64C27/025 ,  B64C3/385 ,  B64C27/12 ,  B64C27/26

    摘要： A compound aircraft features variable incidence wings, a thruster, a rotor and a clutch connecting the engines to the rotor. Upon reaching a suitable forward speed, the control system of the compound aircraft unloads the rotor and disengages the clutch, disconnecting the rotor from the engines. The control system configures the cyclic and collective pitch effectors to cause the rotor to autorotate. The control system selects an autorotation rotational speed that is adequately rapid to prevent excessive deformation of the rotor blades due to aerodynamic forces acting on the blade and that is adequately slow to prevent excessive compressibility effects.

    摘要翻译： 复合飞机具有可变入射翼，推进器，转子和将发动机连接到转子的离合器。 在达到合适的前进速度时，复合飞机的控制系统卸载转子并使离合器分离，使转子与发动机断开连接。 控制系统配置循环和集合桨距效应器，使转子自转。 控制系统选择适当快速的自转转速，以防止由于作用在叶片上的空气动力引起的转子叶片的过度变形，并且足够慢以防止过度的压缩效应。

    Aircraft with integrated lift and propulsion system
    20.
    发明授权
    Aircraft with integrated lift and propulsion system 有权
    具有集成升降机和推进系统的飞机

    公开(公告)号：US07861967B2

    公开(公告)日：2011-01-04

    申请号：US12429982

    申请日：2009-04-24

    申请人： Abe Karem

    发明人： Abe Karem

    IPC分类号： B64C15/12

    CPC分类号： B64C29/0033 ,  B64C3/10 ,  B64C3/385 ,  B64C27/28 ,  B64C27/467 ,  Y02T50/12

    摘要： A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior.

    摘要翻译： 垂直起飞和着陆（VTOL）飞机设计得非常高效，使其在100到1000英里范围内的跑道依赖飞机具有商业竞争力。 改进包括高效倾斜转子和机翼设计，可实现垂直起飞和高效巡航，高纵横比翼，以及在悬停和巡航飞行中都有效的变速推进系统。 优选的飞机使用薄的内侧和外侧翼，薄的转子叶片，并且使用有效的轻量级设计来实现异常低的空重部分。 本发明的方法包括利用先进的设计和分析技术，可以准确预测飞机的物理行为。