公开(公告)号：US20150191245A1

公开(公告)日：2015-07-09

申请号：US14284956

申请日：2014-05-22

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Sebastian MORES ,  Alessandro D'ALASCIO ,  Marius BEBESEL

IPC分类号： B64C27/82 ,  B64C27/06

CPC分类号： B64C27/82 ,  B64C27/06 ,  B64C2027/8245

摘要： A helicopter with a fuselage (4), at least one engine, a roll axis, at least one main rotor, and at least one housing (2) mounted to said fuselage (4). An air inlet (8) and an air outlet (7) are provided along at least a part of a circumference of the at least one housing (2), said air inlet (8) and said air outlet (7) being formed by angularly offset and separate gaps between an inside segment (33) and an outside segment (34) essentially extending respectively longitudinally in direction of said roll axis. At least one rotatable compressor (1) with a plurality of airfoil blades (6) is provided radial inside said at least one housing (2) between said air inlet (8) and said air outlet (7), said at least one rotatable compressor (1) being drivable by said at least one engine about a fan axis (5) and each chord of said airfoil blades (6) is essentially radial oriented with regard to said fan axis (5).

摘要翻译： 具有机身（4），至少一个发动机，滚动轴线，至少一个主转子和安装到所述机身（4）的至少一个壳体（2）的直升机。 空气入口（8）和空气出口（7）沿着至少一个壳体（2）的圆周的至少一部分设置，所述空气入口（8）和所述空气出口（7）通过角度 内侧段（33）和外侧段（34）之间的偏移和分离的间隙基本上在所述辊轴的方向上纵向延伸。 具有多个翼型叶片（6）的至少一个可旋转的压缩机（1）在所述空气入口（8）和所述空气出口（7）之间的所述至少一个壳体（2）的径向内侧设置，所述至少一个可旋转的压缩机 （1）可由所述至少一个发动机围绕风扇轴线（5）驱动，并且所述翼型叶片（6）的每个弦线相对于所述风扇轴线（5）基本上是径向定向的。

公开(公告)号：US20180208295A1

公开(公告)日：2018-07-26

申请号：US15878831

申请日：2018-01-24

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Sebastian MORES ,  Alessandro D'ALASCIO ,  Thomas KNEISCH ,  Klaus KICKER ,  Stefanie LINK ,  Uwe KIESEWETTER ,  Marius BEBESEL

IPC分类号： B64C11/00 ,  B64C27/08 ,  B64C11/48

CPC分类号： B64C11/001 ,  B64C11/48 ,  B64C27/08 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/162 ,  B64D25/00

摘要： A thrust producing unit for producing thrust in a predetermined direction, comprising at least two rotor assemblies and a shrouding, each one of the at least two rotor assemblies, defining an associated rotor plane, wherein a first rotor assembly of the at least two rotor assemblies is provided for operating in a failure-free operating mode of the thrust producing unit and a second rotor assembly of the at least two rotor assemblies is provided for operating at least in case of a failure of the first rotor assembly, and wherein the shrouding accommodates at most one of the at least two rotor assemblies.

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。

公开(公告)号：US20150158584A1

公开(公告)日：2015-06-11

申请号：US14563054

申请日：2014-12-08

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Sebastian MORES ,  Alessandro D'ALASCIO ,  Rainer GRODAU ,  Qinyin ZHANG ,  Christian WEHLE ,  Stefan PROBST

IPC分类号： B64C27/82 ,  B64C27/06

CPC分类号： B64C27/82 ,  B64C2027/8254 ,  B64C2027/8272

摘要： A rotary wing aircraft with a tail rotor in a rotor duct of a shroud. A bumper projects from a lower transition region of said shroud, said lower transition region having a left hand and a right hand lower transition edge between respectively the left hand and the right hand annular surface around the rotor duct and the bumper. Upper leading edges of a vertical fin and of said shroud are provided with left hand and right hand trailing edges. A projection of the upper transition edge to an upright longitudinal plane is defined by a spline curve through points Pi (i=1 . . . 5) and a projection of the lower transition edge to the plane is defined by a spline curve through points Pi (i=6 . . . 10) defined by their respective coordinates (xi, zi) relative to a centre of the shrouded tail rotor.

摘要翻译： 一种旋翼式飞机，其尾翼具有护罩的转子导管。 保险杠从所述护罩的下过渡区域突出，所述下过渡区域分别在转子管道和保险杠周围的左手和右手环形表面之间具有左手和右手下过渡边缘。 垂直翅片和所述护罩的上前缘设置有左手和右手后缘。 上过渡边缘到垂直纵向平面的投影由通过点Pi（i = 1.5）的样条曲线定义，并且下过渡边缘到平面的投影由通过点Pi的样条曲线定义 （i = 6·10）相对于被覆盖的尾部转子的中心各自的坐标（xi，zi）定义。