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1. 发明授权

EP3366586B1 A THRUST PRODUCING UNIT WITH AT LEAST TWO ROTOR ASSEMBLIES AND A SHROUDING 有权
公开(公告)号：EP3366586B1
公开(公告)日：2020-08-19
申请号：EP17400008.3
申请日：2017-02-27
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Kiesewetter, Uwe , Bebesel, Marius , Mores, Sebastian , Pfaller, Rupert
IPC分类号： B64C39/02 , B64C11/00 , B64C11/48 , B64C27/20

2. 发明公开

EP3354559A1 A THRUST PRODUCING UNIT WITH AT LEAST TWO ROTOR ASSEMBLIES AND A SHROUDING 有权
公开(公告)号：EP3354559A1
公开(公告)日：2018-08-01
申请号：EP17400003.4
申请日：2017-01-26
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Mores, Sebastian , Kiesewetter, Uwe , Bebesel, Marius
IPC分类号： B64C11/00 , B64C29/00 , B64C27/20
CPC分类号： B64C11/46 , B64C11/001 , B64C27/08 , B64C27/20 , B64C29/0033
摘要： The invention is related to a thrust producing unit 3d for producing thrust in a predetermined direction 23, comprising a shrouding 6d and at least two rotor assemblies 7d, 8d, wherein the shrouding 6d defines an internal volume 20c, and wherein a first rotor assembly 7d of the at least two rotor assemblies 7d, 8d defines a first rotor axis and a second rotor assembly 8d of the at least two rotor assemblies 8d defines a second rotor axis, the first and second rotor axes 12d being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles 21a, 22a with respect to the predetermined direction 23, the associated inclination angles 21a, 22a being comprised in a range between -60° and +60°, and preferably amounting to 0°, and wherein the first rotor assembly 7d is arranged outside of the internal volume 20c of the shrouding 6d.

3. 发明授权

EP2878536B1 Advanced pitch stabilizer 有权
标题翻译：高级音调稳定器
公开(公告)号：EP2878536B1
公开(公告)日：2017-05-24
申请号：EP13400035.5
申请日：2013-11-29
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Mores, Sebastian , D'Alascio, Alessandro , Kiesewetter, Uwe , Probst, Stefan , Wehle, Christian , Bebesel, Marius
IPC分类号： B64C27/82
CPC分类号： B64C5/10 , B64C9/06 , B64C27/82 , B64C2027/8254 , B64C2027/8272 , B64C2027/8281

4. 发明公开

EP3050794A1 AIRCRAFT WITH INWARDLY FOLDABLE REAR DOOR 有权
标题翻译：里面折返门平面
公开(公告)号：EP3050794A1
公开(公告)日：2016-08-03
申请号：EP15400004.6
申请日：2015-01-28
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Probst, Stefan , Hünecke, Wolfgang , Löser, Frank , Frese, Johannes , Mores, Sebastian , Matt, Michael
IPC分类号： B64C1/14
CPC分类号： B64C1/1415 , B64C1/24 , B64D11/00
摘要： An aircraft comprising a rear opening (4) and a rear door (11) to close such rear opening (4), wherein the rear door is attached to the fuselage (3) of the aircraft by means of an arrangement having two links (26, 27) due to which the rear door (11) can be displaced longitudinally and in elevation up to a position at the interior of the fuselage (3).

5. 发明授权

EP3333064B1 AN AIRCRAFT WITH AN AIRFRAME AND AT LEAST ONE ELECTRICALLY POWERED THRUST PRODUCING UNIT 有权
公开(公告)号：EP3333064B1
公开(公告)日：2020-04-22
申请号：EP16400060.6
申请日：2016-12-07
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Mores, Sebastian , Blacha, Martin , Reichensperger, Christian , Rittel, Klaus , Schneeberger, Marco , Geiss, Michael , Paschek, Markus , Bebesel, Marius
IPC分类号： B64C1/06 , B64C27/04 , B64D27/24

6. 发明公开

EP3470332A1 A MULTIROTOR AIRCRAFT WITH AN AIRFRAME AND AT LEAST ONE WING 有权
公开(公告)号：EP3470332A1
公开(公告)日：2019-04-17
申请号：EP17400058.8
申请日：2017-10-13
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Pfaller, Rupert , Kiesewetter, Uwe , Mores, Sebastian , Bebesel, Marius
IPC分类号： B64C27/20 , B64C29/00
摘要： The invention is related to a multirotor aircraft 1 with an airframe 2 and at least one wing 4 that is mounted to the airframe 2, the at least one wing 4 being provided with at least four thrust producing units 3a, 3b, 3c, 3d, 3e, 3f that are arranged in spanwise direction 1b of the at least one wing 4, wherein each one of the at least four thrust producing units 3a comprises at least one rotor assembly that is accommodated in an associated shrouding 6a, the associated shrouding 6a being integrated into the at least one wing 4, characterized in that the associated shrouding 6a defines an air duct that is axially delimited by an air inlet region and an air outlet region, wherein the air inlet region exhibits in circumferential direction of the air duct at least two different aerodynamic profiles.

7. 发明授权

EP3225543B1 A PROPELLER ASSEMBLY WITH AT LEAST TWO PROPELLER BLADES 有权
公开(公告)号：EP3225543B1
公开(公告)日：2018-11-14
申请号：EP16400009.3
申请日：2016-04-01
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Kiesewetter, Uwe , Haisch, Stefan , Bebesel, Marius , Mores, Sebastian
IPC分类号： B64C27/43 , A63H27/00
CPC分类号： B64C11/06 , A63H27/12 , B64C11/008 , B64C27/43
摘要： The invention is related to a propeller assembly (7) with at least two propeller blades (1a, 1b) that are interconnected by associated connection means (1c), the associated connection means (1c) defining a common pitch axis (4) for the at least two propeller blades (1a, 1b) in operation, each one of the at least two propeller blades (1a, 1b) comprising associated leading and trailing edges (2a, 2b) that define a respective chord and quarter chord line (2e) thereof, wherein the common pitch axis (4) is arranged with a predetermined offset (4b) relative to the quarter chord line (2e) of each one of the at least two propeller blades (1a, 1b), and wherein the associated connection means (1c) is adapted to enable, at least in operation in a non-axial inflow field (6), a passive pitch adjustment of the at least two propeller blades (1a, 1b) around the common pitch axis (4).

8. 发明授权

EP3056423B1 AN AIRCRAFT WITH A FUSELAGE THAT DEFINES AT LEAST AN INTERIOR REGION AND A DRIVE SYSTEM ACCOMMODATING REGION 有权
标题翻译：拥有至少定义内陆地区和驾驶系统住宿地区的飞机的飞机
公开(公告)号：EP3056423B1
公开(公告)日：2017-12-13
申请号：EP15400008.7
申请日：2015-02-16
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Mores, Sebastian , Löser, Frank , Frese, Johannes , Bräutigam, Ralf , Wehle, Christian
IPC分类号： B64C1/10 , B64D33/08 , B64D41/00
CPC分类号： B64C1/40 , B64C1/10 , B64C1/16 , B64C27/82 , B64D33/04 , B64D33/08 , B64D41/00
摘要： The invention is related to an aircraft (1) with a fuselage (2) that defines at least an interior region (2a) and a drive system accommodating region (1f), said drive system accommodating region being arranged inside said fuselage (2) and comprising at least one fire protection zone (11) that is defined by at least one associated firewall arrangement (10), said at least one fire protection zone (11) accommodating at least one engine (5) within said at least one associated firewall arrangement (10) such that said associated firewall arrangement defines a fire-resistant separation between said at least one engine (5) and said interior region (2a) of said fuselage (2), wherein said at least one associated firewall arrangement (10) comprises at least one air duct for ducting a hot air flow that is generated in operation of said aircraft (1) independent from heat generation of said at least one engine (5).

9. 发明授权

EP2727832B1 Rotor head of a rotary wing flying machine and method of manufacturing and assembling such a rotor head 有权转让
标题翻译：旋翼飞行器的旋翼头，并且这样的转子头的制造和组装方法
公开(公告)号：EP2727832B1
公开(公告)日：2016-06-22
申请号：EP12400045.6
申请日：2012-10-31
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： D'Alascio, Alessandro , Mores, Sebastian , Denecke, Ulrich , Kuntze-Fechner, Gerald , Schimke, Dieter , Wehle, Christian , Klam, Hans-Philipp
IPC分类号： B64C27/04 , B64C27/32 , B64C7/00
CPC分类号： B64C27/04 , B64C7/00 , B64C27/32

10. 发明公开

EP2883791A1 Helicopter with a Tail shroud 有权
标题翻译： Hubschrauber mit Heckschutz
公开(公告)号：EP2883791A1
公开(公告)日：2015-06-17
申请号：EP13400034.8
申请日：2013-12-10
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Mores, Sebastian , D'Alascio, Alessandro , Grodau, Rainer , Zhang, Qinyin , Wehle, Christian , Probst, Stefan
IPC分类号： B64C27/82
CPC分类号： B64C27/82 , B64C2027/8254 , B64C2027/8272
摘要： The invention is related to a helicopter (1) with a fuselage (2) and a tail rotor in a rotor duct (8) of a shroud (7) mounted to a rear end of a tail boom (3). A vertical fin (6) projects from an upper transition region of said shroud (7) having a left hand and a right hand upper transition edge (11) between respectively a left hand and a right hand annular surface (57) around the rotor duct (8) of the shroud (7) and the vertical fin (6). A bumper (9) projects from a lower transition region of said shroud (7), 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 (57) around the rotor duct (8) of the shroud (7) and the bumper (9). Upper leading edges (12, 32) of said vertical fin (6) and of said shroud (7) are provided and left hand and right hand trailing edges (13, 17) of said shroud (7). A projection of the upper transition edge (11a) to the x-z plane is defined by a spline curve through points Pi (i=1..5) and a projection of the lower transition edge (1 1 b) to the x-z plane is defined by a spline curve through points Pi (i=6..10) defined by their respective coordinates (xi, zi) relative to a Fenestron-Rotor's centre.
摘要翻译：本发明涉及一种具有机身（2）的直升机（1）和安装在尾臂（3）的后端的护罩（7）的转子导管（8）中的尾部转子。垂直翅片（6）从所述护罩（7）的上过渡区域突出，左右手上过渡边缘（11）分别在转子导管周围的左手和右手环形表面（57）之间（7）和垂直翅片（6）之间的距离（8）。缓冲器（9）从所述护罩（7）的下过渡区域突出，所述下过渡区域在转子周围分别具有左手和右手环形表面（57）之间的左手和右手下过渡边缘护罩（7）的导管（8）和保险杠（9）。所述垂直翅片（6）和所述护罩（7）的上前缘（12,32）设置有所述护罩（7）的左手和右手后缘（13,17）。上部过渡边缘（11a）到xz平面的投影由通过点Pi（i = 1..5）的样条曲线定义，并且下部过渡边缘（11b）到xz平面的投影被定义通过相对于Fenestron-Rotor中心由它们各自坐标（xi，zi）定义的点Pi（i = 6..10）的样条曲线。

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