公开(公告)号：US20160251080A1

公开(公告)日：2016-09-01

申请号：US15054485

申请日：2016-02-26

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

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

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

CPC classification number: B64C27/82 ,  B64C27/20 ,  B64C2027/8272 ,  B64F5/10

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20190016452A1

公开(公告)日：2019-01-17

申请号：US16020525

申请日：2018-06-27

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Stefan PROBST ,  Marc NOTHEN ,  Christian WEHLE

IPC: B64C27/82 ,  F04D29/52 ,  B32B38/00 ,  B29C70/30 ,  B29L31/30

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

Abstract: 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.

公开(公告)号：US20160236767A1

公开(公告)日：2016-08-18

申请号：US15043758

申请日：2016-02-15

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Sebastian MORES ,  Frank LOESER ,  Johannes FRESE ,  Ralf BRAEUTIGAM ,  Christian WEHLE

IPC: B64C1/40 ,  B64C27/82 ,  B64D33/04 ,  B64C1/16

CPC classification number: B64C1/40 ,  B64C1/10 ,  B64C1/16 ,  B64C27/82 ,  B64D33/04 ,  B64D33/08 ,  B64D41/00

Abstract: An aircraft with a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region being arranged inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement, the at least one fire protection zone accommodating at least one engine within the at least one associated firewall arrangement such that the associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage, wherein the at least one associated firewall arrangement comprises at least one air duct for ducting a hot air flow that is generated in operation of the aircraft independent from heat generation of the at least one engine.

Abstract translation: 具有至少限定内部区域和驱动系统容纳区域的机身的飞行器，所述驱动系统容纳区域布置在所述机身内部，并且包括由至少一个相关联的防火墙布置限定的至少一个防火区域，所述防火墙装置 至少一个防火区域，其容纳至少一个相关联的防火墙装置内的至少一个发动机，使得所述相关联的防火墙装置限定所述至少一个发动机与所述机身的内部区域之间的耐火间隔，其中，所述至少一个相关联的防火墙装置 防火墙装置包括至少一个空气管道，用于在独立于至少一个发动机的发热的情况下运送在飞机运行中产生的热空气流。

公开(公告)号：US20170089443A1

公开(公告)日：2017-03-30

申请号：US15278427

申请日：2016-09-28

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Justus STEGER ,  Christian WEHLE ,  Henry GUNN

IPC: F16H57/025 ,  B64C27/14 ,  F16H57/028 ,  B64D35/08

CPC classification number: F16H57/025 ,  B64C27/12 ,  B64C27/14 ,  B64C2027/002 ,  B64D35/08 ,  F16H57/028

Abstract: A mounting arrangement for mounting at least a gear box of a rotorcraft to a fuselage of a rotorcraft, the mounting arrangement comprising a gear box of a rotorcraft and at least two support plates that are rigidly attached to at least approximately opposing sides of the gear box, each one of the at least two support plates comprising at least two attachment means that are adapted to allow attachment of the at least two support plates to a fuselage of a rotorcraft by means of associated struts in order to enable transfer of induced loads occurring in operation, which are directed into a predetermined load direction, via the associated struts.

公开(公告)号：US20150307182A1

公开(公告)日：2015-10-29

申请号：US14554142

申请日：2014-11-26

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

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

IPC: B64C5/10 ,  B64C9/06

CPC classification number: B64C5/10 ,  B64C9/06 ,  B64C27/82 ,  B64C2027/8254 ,  B64C2027/8272 ,  B64C2027/8281

Abstract: 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.

Abstract translation: 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

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

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

IPC: B64C27/82 ,  B64C27/06

CPC classification number: B64C27/82 ,  B64C2027/8254 ,  B64C2027/8272

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20150307190A1

公开(公告)日：2015-10-29

申请号：US14554191

申请日：2014-11-26

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Stefan PROBST ,  Marc NOTHEN ,  Christian WEHLE

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

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

Abstract: 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.

Abstract translation: 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。