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    AIRCRAFT WITH AN AIR INTAKE FOR AN AIR BREATHING PROPULSION ENGINE
    2.
    发明申请
    AIRCRAFT WITH AN AIR INTAKE FOR AN AIR BREATHING PROPULSION ENGINE 有权
    具有用于空气呼吸推进发动机的空气入口的飞机

    公开(公告)号：US20160075439A1

    公开(公告)日：2016-03-17

    申请号：US14849093

    申请日：2015-09-09

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Sebastian MORES ,  Frank LOSER ,  Stefan PROBST ,  Michael MATT

    IPC分类号： B64D33/02 ,  F02M35/04 ,  F02M35/16 ,  F02M35/10

    CPC分类号： B64D33/02 ,  B64C27/04 ,  B64D2033/022 ,  B64D2033/0253 ,  F02C7/052 ,  F02C7/055 ,  F05D2220/329 ,  F05D2260/607 ,  Y02T50/675

    摘要： An aircraft with a fuselage that accommodates at least one air breathing propulsion engine, the fuselage having a maximum fuselage width determined in the region of the at least one air breathing propulsion engine and comprising at least one front fuselage cowling and at least one rear fuselage cowling that are each covering the at least one air breathing propulsion engine at least partly, the at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal axis of the at least one air breathing propulsion engine by a predetermined cowling offset to define a dynamic air intake through which an intake air stream is supplied to the at least one air breathing propulsion engine in operation.

    摘要翻译： 一种具有机身的飞机，其容纳至少一个空气呼吸推进发动机，所述机身具有在所述至少一个呼吸推进发动机的区域中确定的最大机身宽度，并且包括至少一个前机身罩和至少一个后机身罩 其至少部分地覆盖所述至少一个呼吸推进发动机，所述至少一个前机身和后机身整流罩在横向于所述至少一个空气呼吸推进发动机的纵向轴线的方向上彼此间隔开 预定的整流罩偏移以限定动态空气入口，通过所述动态空气入口在运行中将进气流供应到所述至少一个空气呼吸推进发动机。

    SHROUDED ROTARY ASSEMBLY FROM SEGMENTED COMPOSITE FOR AIRCRAFT
    4.
    发明申请
    SHROUDED ROTARY ASSEMBLY FROM SEGMENTED COMPOSITE FOR AIRCRAFT 审中-公开
    来自SEGMENTED COMPOSITE FOR AIRCRAFT的SHROUDED旋转总成

    公开(公告)号：US20150307190A1

    公开(公告)日：2015-10-29

    申请号：US14554191

    申请日：2014-11-26

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Stefan PROBST ,  Marc NOTHEN ,  Christian WEHLE

    IPC分类号： B64C27/82 ,  B32B38/00 ,  F04D29/52

    CPC分类号： B64C27/82 ,  B29C70/30 ,  B29L2031/3088 ,  B32B38/0012 ,  B32B2038/0052 ,  B64C2027/8254 ,  F04D29/522

    摘要： A shrouded rotor assembly for an aircraft. The shrouded rotor assembly comprises a stator hollow structure comprises formed from a plurality of composite angular segments. Each composite angular segment includes: a core arched section of a central hub casing, a peripheral rim section of an external hollow duct and a pair of angularly opposed sliced portions, respectively for one of a pair of guide vanes. The resulting stator hollow structure is a unitary one-piece, integrating together continuously the composite angular segments. The invention typically applies e.g. to aircrafts such as rotary wing aircrafts.

    摘要翻译： 用于飞机的被覆盖的转子组件。 被覆盖的转子组件包括由多个复合角度段形成的定子中空结构。 每个复合角形部分包括：中央轮毂壳体的芯拱形部分，外部中空管道的外围边缘部分和分别用于一对导叶中的一个的一对角度相对的切片部分。 所得到的定子中空结构是整体的单件，将复合角段连续地集成在一起。 本发明通常适用于例如 飞机如旋翼飞机。

    TAIL ASSEMBLY FOR A ROTORCRAFT, ROTORCRAFT AND METHOD OF MANUFACTURE OF A STRENGTHENED TAIL ASSEMBLY
    6.
    发明申请
    TAIL ASSEMBLY FOR A ROTORCRAFT, ROTORCRAFT AND METHOD OF MANUFACTURE OF A STRENGTHENED TAIL ASSEMBLY 有权
    用于转子，转轮和加强尾部装配的制造方法的尾部装配

    公开(公告)号：US20160251080A1

    公开(公告)日：2016-09-01

    申请号：US15054485

    申请日：2016-02-26

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Christian WEHLE ,  Justus STEGER ,  Marc NOTHEN ,  Stefan PROBST ,  Antonia HORSTMANN

    IPC分类号： B64C27/82 ,  B64F5/00 ,  B64C27/20

    CPC分类号： B64C27/82 ,  B64C27/20 ,  B64C2027/8272 ,  B64F5/10

    摘要： A tail assembly for a rotorcraft. The tail assembly is manufactured to include at least one transition structure provided in the tail assembly. The transition structure is longitudinally arranged between a longitudinal median boom portion and a tail fin. A power transmission shaft of the rotorcraft extends at least partly externally above a longitudinal median boom portion of the tail assembly. The transition structure includes at an entering region a cut-out elevation step, where is made a passing through opening for the power transmission shaft.

    摘要翻译： 用于旋翼航空器的尾部组件。 尾部组件被制造为包括设置在尾部组件中的至少一个过渡结构。 过渡结构纵向布置在纵向中间吊杆部分和尾翼之间。 旋翼航空器的动力传递轴至少部分地从尾部组件的纵向中间臂部分的外部延伸。 过渡结构包括在进入区域处的切口升高台阶，其中形成用于动力传递轴的通过开口。

    MODULAR SUBFLOOR ARRANGEMENT FOR AN AIRCRAFT
    7.
    发明申请
    MODULAR SUBFLOOR ARRANGEMENT FOR AN AIRCRAFT 审中-公开

    公开(公告)号：US20190389592A1

    公开(公告)日：2019-12-26

    申请号：US16443960

    申请日：2019-06-18

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Gottfried HUEBNER ,  Stefan PROBST ,  Frank LOESER ,  Robert SEILER

    IPC分类号： B64D37/04 ,  B64C1/06 ,  B64C1/18 ,  B64D37/06 ,  B64D37/16

    摘要： A modular subfloor system comprises first longitudinal structural frames, lateral regions, and a modular tank system that is connected to the first longitudinal structural frames. The modular tank system comprises a bottom shell, an upper panel, second longitudinal structural frames arranged between the bottom shell and the upper panel and transversal structural frames that are arranged between the bottom shell and the upper panel. The transversal structural frames and the second longitudinal structural frames form compartments. The modular tank system further comprises tank bladders arranged in at least some of the compartments and sealing elements that seal the upper panel, the bottom shell, and the at least some of the compartments of the modular tank system.

    ADVANCED PITCH STABILIZER
    8.
    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。

    ROTARY WING AIRCRAFT WITH A TAIL SHROUD
    9.
    发明申请
    ROTARY WING AIRCRAFT WITH A TAIL SHROUD 有权
    旋转翼飞机与尾巴

    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。