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    AUTOGYRO WITH A STREAMLINED OUTER CONTOUR
    2.
    发明申请
    AUTOGYRO WITH A STREAMLINED OUTER CONTOUR 审中-公开

    公开(公告)号：US20170327210A1

    公开(公告)日：2017-11-16

    申请号：US15535485

    申请日：2015-12-16

    申请人： CHRISTOPH FRAUNDORFER

    发明人： CHRISTOPH FRAUNDORFER

    IPC分类号： B64C27/02 ,  B64C27/82

    CPC分类号： B64C27/02 ,  B64C2027/8281

    摘要： The invention related to an autogyro (1) comprising a body (2), a mast (3) arranged in the upper region of the body, a rotor (4) which is rotatably arranged in the region of the end of the body (3) and which can be put into autorotation by an air flow, a drivable propeller (6) which is arranged in the region of a rear body end (5) and which generates a propulsion of the autogyro (1), a guide mechanism (7) arranged behind a propeller (1), and at least one brace (8) which extends past the propeller in the longitudinal direction of the autogyro at a radial distance from the propeller (6) in an outwards direction and which connects the guide mechanism (7) to the body (2). According to the invention, the guide mechanism (7) has a guide mechanism protrusion (9) which is arranged coaxially to the rear body end (5) and which extends forwards from the guide mechanism (7) in the direction of the rear body end (5) at a distance therefrom. Furthermore, at least the region of the rear body end (5) of the body (2) and the guide mechanism protrusion (9) together form a streamlined outer contour. The invention further relates to an autogyro in which the mast (3) is designed, in particular the mast is arranged and/or inclined relative to the propeller (6), such that when rotating, the blades (17) of the propeller (6) always only partly overlap with the mast (3) in a respective overlap region (21) when viewing the autogyro (1) from the rear.

    Pitch stabilizer and rotary-wing aircraft equipped with such stabilizer
    5.
    发明授权
    Pitch stabilizer and rotary-wing aircraft equipped with such stabilizer 有权
    桨距稳定器和旋翼飞机配备这种稳定器

    公开(公告)号：US09205911B2

    公开(公告)日：2015-12-08

    申请号：US14028690

    申请日：2013-09-17

    申请人： AIRBUS HELICOPTERS

    发明人： Frederic Beroul

    IPC分类号： B64C27/82 ,  B64C5/16 ,  B64C27/06 ,  B64C5/02

    CPC分类号： B64C5/16 ,  B64C5/02 ,  B64C27/06 ,  B64C27/82 ,  B64C2027/8281

    摘要： A pitch stabilizer [10] equipped with an upper stabilizer surface [15] and a lower stabilizer surface [20], with the upper stabilizer surface [15] being located in an upper plane [P1] and with the lower stabilizer surface [20] being located in a lower plane [P2], with the upper plane [P1] overhanging the lower plane [P2]. The upper stabilizer surface [15] is rotatable about an upper axis of rotation [AX1], with the said lower stabilizer surface [20] being rotatable about a lower axis of rotation [AX2], with the stabilizer means [10] having linking means [30] whereby a rotary movement of one stabilizer surface causes an equal rotary movement of the other stabilizer surface.

    摘要翻译： 配备有上稳定器表面[15]和下稳定器表面[20]的俯仰稳定器[10]，其中上稳定器表面[15]位于上平面[P1]中并且具有下稳定器表面[20] 位于下平面[P2]中，上平面[P1]伸出下平面[P2]。 上稳定器表面15可以围绕旋转轴线[AX1]旋转，其中所述下稳定器表面20可以围绕下旋转轴线[AX2]旋转，稳定装置[10]具有连接装置 由此一个稳定器表面的旋转运动导致另一个稳定器表面的相等的旋转运动。

    ADVANCED PITCH STABILIZER
    6.
    发明申请
    ADVANCED PITCH STABILIZER 有权
    高级搅拌稳定器

    公开(公告)号：US20150307182A1

    公开(公告)日：2015-10-29

    申请号：US14554142

    申请日：2014-11-26

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Sebastian MORES ,  Alessandro D'ALASCIO ,  Uwe KIESEWETTER ,  Stefan PROBST ,  Christian WEHLE ,  Marius BEBESEL

    IPC分类号： B64C5/10 ,  B64C9/06

    CPC分类号： B64C5/10 ,  B64C9/06 ,  B64C27/82 ,  B64C2027/8254 ,  B64C2027/8272 ,  B64C2027/8281

    摘要： A pitch stabilizer with box configuration suitable for providing stability to a rotorcraft comprising a vertical mid-plane and a fuselage; the pitch stabilizer comprising one or two pitch stabilizing assemblies, with no more than one pitch stabilizing assembly on each side of the vertical mid-plane, wherein each pitch stabilizing assembly comprises upper pitch stabilizing means, lower pitch stabilizing means and a wing tip element.

    摘要翻译： 一种具有箱形结构的桨距稳定器，其适于为包括垂直中平面和机身的旋翼飞机提供稳定性; 所述桨距稳定器包括一个或两个俯仰稳定组件，在垂直中平面的每一侧上不超过一个桨距稳定组件，其中每个俯仰稳定组件包括上桨距稳定装置，下桨距稳定装置和翼尖元件。

    SYSTEM AND A METHOD FOR CONTROLLING PITCHING STABILIZER MEANS OF AN AIRCRAFT
    7.
    发明申请
    SYSTEM AND A METHOD FOR CONTROLLING PITCHING STABILIZER MEANS OF AN AIRCRAFT 有权
    用于控制飞机稳定平衡装置的系统和方法

    公开(公告)号：US20140326825A1

    公开(公告)日：2014-11-06

    申请号：US14267158

    申请日：2014-05-01

    申请人： Airbus Helicopters

    发明人： Boris GROHMANN ,  Thomas BURO

    IPC分类号： B64C13/50 ,  B64C27/00 ,  B64C13/16

    CPC分类号： B64C13/50 ,  B64C13/42 ,  B64C13/503 ,  B64C2027/8281 ,  F16H3/724

    摘要： A control system (20) for controlling pitching stabilizer means of an aircraft, said system (20) being provided with at least one outlet shaft (21) and with a first actuator (31) and a second actuator (36). The first and second actuators (31 and 36) are different, and the first actuator (31) is a slow actuator having a first driving portion that moves at a first speed, the second actuator (36) being a fast actuator having a second driving portion that moves at a second speed faster than the first speed, said control system (20) comprising a control device (50) connected to the first actuator (31) and to the second actuator (36) in order to cause said outlet shaft (21) to be driven either by the first driving portion (32) and/or by the second driving portion (37).

    摘要翻译： 一种用于控制飞机的俯仰稳定装置的控制系统（20），所述系统（20）设置有至少一个出口轴（21）以及第一致动器（31）和第二致动器（36）。 第一和第二致动器（31和36）不同，并且第一致动器（31）是具有以第一速度移动的第一驱动部分的慢速致动器，第二致动器（36）是具有第二驱动 所述控制系统（20）包括连接到所述第一致动器（31）和所述第二致动器（36）的控制装置（50），以便使所述出口轴（ 21）由第一驱动部（32）和/或第二驱动部（37）驱动。

    PITCH STABILIZER AND ROTARY-WING AIRCRAFT EQUIPPED WITH SUCH STABILIZER
    9.
    发明申请
    PITCH STABILIZER AND ROTARY-WING AIRCRAFT EQUIPPED WITH SUCH STABILIZER 有权
    配有稳定器的旋转稳定器和旋转式飞机

    公开(公告)号：US20140077026A1

    公开(公告)日：2014-03-20

    申请号：US14028690

    申请日：2013-09-17

    申请人： Eurocopter

    发明人： Frederic Beroul

    IPC分类号： B64C5/16 ,  B64C27/06

    CPC分类号： B64C5/16 ,  B64C5/02 ,  B64C27/06 ,  B64C27/82 ,  B64C2027/8281

    摘要： A pitch stabilizer [10] equipped with an upper stabilizer surface [15] and a lower stabilizer surface [20], with the upper stabilizer surface [15] being located in an upper plane [P1] and with the lower stabilizer surface [20] being located in a lower plane [P2], with the upper plane [P1] overhanging the lower plane [P2]. The upper stabilizer surface [15] is rotatable about an upper axis of rotation [AX1], with the said lower stabilizer surface [20] being rotatable about a lower axis of rotation [AX2], with the stabilizer means [10] having linking means [30] whereby a rotary movement of one stabilizer surface causes an equal rotary movement of the other stabilizer surface.

    摘要翻译： 配备有上稳定器表面[15]和下稳定器表面[20]的俯仰稳定器[10]，其中上稳定器表面[15]位于上平面[P1]中并且具有下稳定器表面[20] 位于下平面[P2]中，上平面[P1]伸出下平面[P2]。 上稳定器表面15可以围绕旋转轴线[AX1]旋转，其中所述下稳定器表面20可以围绕下旋转轴线[AX2]旋转，稳定装置[10]具有连接装置 由此一个稳定器表面的旋转运动导致另一个稳定器表面的相等的旋转运动。

    Method of controlling and regulating the deflection angle of a tailplane in a hybrid helicopter
    10.
    发明授权
    Method of controlling and regulating the deflection angle of a tailplane in a hybrid helicopter 有权
    控制和调节混合直升机尾翼偏转角的方法

    公开(公告)号：US08583295B2

    公开(公告)日：2013-11-12

    申请号：US13088493

    申请日：2011-04-18

    申请人： Paul Eglin ,  Nicolas Queiras ,  André Barraco ,  Francois Malburet

    发明人： Paul Eglin ,  Nicolas Queiras ,  André Barraco ,  Francois Malburet

    IPC分类号： B64C27/57

    CPC分类号： B64C27/26 ,  B64C2027/8281

    摘要： A method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor (10), at least one variable pitch propulsion propeller (6), and at least one power plant for driving the main rotor(s) (10) and at least one propeller (6), said method consisting in using a first loop for regulating pitch or attitude, and a second loop for regulating speed by means of a control over the mean pitch of the propulsion propeller(s) (6), wherein the method further consists in controlling the deflection angle of a horizontal tailplane (30, 25, 35) by using a third loop for controlling and regulating said deflection angle of the horizontal tailplane (30, 25, 35) in order to minimize the total power consumed by the main rotor (10) and the propulsive propeller(s) (6), for a given speed and attitude.

    摘要翻译： 一种控制和调节具有高稳定性的前进速度的旋翼飞机的方法，所述旋翼航空器至少包括主提升转子（10），至少一个可变桨距推进推进器（6）和至少一个动力装置 驱动主转子（10）和至少一个螺旋桨（6），所述方法包括使用用于调节桨距或姿态的第一回路，以及用于通过对平均桨距的平均桨距的控制来调节速度的第二回路 推进螺旋桨（6），其中所述方法还包括通过使用第三回路来控制水平尾翼（30,25,35）的偏转角度，所述第三回路用于控制和调节所述水平尾翼（30,25,35）的所述偏转角， 以便以给定的速度和姿态来最小化主转子（10）和推进螺旋桨（6）所消耗的总功率。