| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 261 | HECKROTORVORRICHTUNG EINES HELIKOPTERS | EP16151912.9 | 2016-01-19 | EP3067272A1 | 2016-09-14 | STUCKI, Martin |
Eine Heckrotorvorrichtung (2), befestigbar an einem Heckausleger eines Drehflüglers, insbesondere eines Helikopters, umfassend eine Ummantelung, die einen Luftströmungskanal (200) mit einer Kanaltiefe (T) in Richtung einer Kanalachse (A) senkrecht zur Hochachse (h) und Längsachse (L) verlaufend und einen Kanalinnendurchmesser (202) bildet, sodass in dem Luftströmungskanal (200) ein Heckrotor (21) mit einer Mehrzahl von Rotorblättern (210) drehbar lagerbar ist, wobei die Ummantelung derart ausgestaltet ist, dass ihre Kanaltiefe (T) in negativer Längsachsenrichtung (L) nach hinten verjüngt ausgestaltet ist, soll geschaffen werden, dass im Betrieb die Vorwärtsflugeigenschaften verbessert und die Leistungsaufnahme des Hauptrotors reduziert ist. Dies wird dadurch erreicht, dass die variable Kanaltiefe (T) immer kleiner als ein Viertel des Kanalinnendurchmessers (202) gewählt ist und das Verhältnis der variablen Kanaltiefe (T) der Ummantelung in Richtung Längsachse (L) zum Kanalinnendurchmesser (202) der Ummantelung zwischen (T1/202) 20.5% und (T2/202) 14 % liegt.
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| 262 | Heckrotorsystem sowie Verfahren zur Steuerung eines Heckrotorsystems | EP09014309.0 | 2009-11-16 | EP2186727B1 | 2016-05-25 | Buhl, Andreas; Koros, Michael |
| 263 | Heckrotorsystem sowie Verfahren zur Steuerung eines Heckrotorsystems | EP09014309.0 | 2009-11-16 | EP2186727A3 | 2012-10-24 | Buhl, Andreas; Koros, Michael |
Die vorliegende Erfindung betrifft ein Heckrotorsystem für ein Luftfahrzeug, insbesondere für einen Helikopter, mit einem mehrblättrigen Heckrotor mit festem Blattanstellwinkel sowie ein Verfahren zur Steuerung eines Heckrotorsystems für ein Luftfahrzeug, insbesondere für einen Helikopter. Der Heckrotor wird redundant angetrieben (1). |
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| 264 | Rotary wing aircraft with a tail shroud | US14563054 | 2014-12-08 | US09475578B2 | 2016-10-25 | Sebastian Mores; Alessandro D'Alascio; Rainer Grodau; Qinyin Zhang; Christian Wehle; Stefan Probst |
| 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. | ||||||
| 265 | Rotary wing aircraft with a multiple beam tail | US14679072 | 2015-04-06 | US09592899B2 | 2017-03-14 | Axel Fink |
| A rotary wing aircraft comprising a fuselage, a cabin volume enclosed by the fuselage, a main rotor arranged above the fuselage, a tail rotor mounted on a tail, the tail being attached to a rear part of the fuselage supporting the tail at its rear end, whereas the tail includes two beam boom elements, one element extending at the port side and the other element extending at the starboard side of the rotary wing aircraft, the front root end of each element being hinged to the corresponding lateral side of the fuselage, and both elements being canted with respect to the longitudinal axis of the rotary wing aircraft so as to be interconnected to each other at the rear portion of the tail. | ||||||
| 266 | Tail rotor device of a helicopter | US15041430 | 2016-02-11 | US09701405B2 | 2017-07-11 | Martin Stucki |
| A tail rotor device, which can be attached to a tail boom of a rotary wing aircraft, in particular of a helicopter, encompassing a sheathing, which forms an air flow channel with a channel depth running in the direction of a channel axis perpendicular to the vertical axis and longitudinal axis and an inner channel diameter, so that a tail rotor with rotor blades can be rotatably mounted in the air flow channel, wherein the sheathing is designed in such a way that its channel depth in a negative longitudinal direction tapers toward the back, wherein the objective is to improve the forward flight characteristics during operation and reduce the power consumption of the main rotor. This is achieved by virtue of the selected variable channel depth is always less than one fourth of the inner channel diameter, and the ratio between the variable channel depth of the sheathing in the direction of the longitudinal axis and the inner channel diameter of the sheathing lies between 20.5% and 14%. | ||||||
| 267 | Agencement de rotor de queue de poussée accrue pour aéronef à voilure tournante | EP83401878.0 | 1983-09-26 | EP0107543A1 | 1984-05-02 | Vuillet, Alain; Morelli, Françoise Jeanne |
Agencement de rotor de queue pour aéronef à voilure tournante, comportant un tunnel (4) d'axe X-X transversal audit aéronef et dans lequel est disposé un rotor (10) à pales multiples (11) coaxial audit tunnel (4) et engendrant un écoulement d'air transversal. Selon l'invention, cet agencement est caractérisé en ce qu'il comporte une pluralité d'aubes fixes (18) disposées à l'intérieur dudit tunnel (4) en aval dudit rotor ( 10) par rapport audit écoulement d'air et agencées de façon au moins sensiblement radiale par rapport audit tunnel pour pouvoir récupérer sous forme de poussée axiale l'énergie de rotation de l'écoulement d'air à la sortie du rotor (10). Augmentation de poussée des rotors, notamment carénés. |
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| 268 | TAIL ASSEMBLY FOR A ROTORCRAFT, ROTORCRAFT AND METHOD OF MANUFACTURE OF A STRENGTHENED TAIL ASSEMBLY | EP15400011.1 | 2015-02-27 | EP3061689B1 | 2017-09-27 | Wehle, Christian; Steger, Justus; Nothen, Marc; Probst, Stefan; Horstmann, Antonia |
| 269 | 无人直升机(尾桨推进纵列双旋翼) | CN201930239301.3 | 2019-05-17 | CN305401107S | 2019-10-25 | 付永庆 |
| 1.本外观设计产品的名称：无人直升机(尾桨推进纵列双旋翼)。 2.本外观设计产品的用途：测绘、运输、航拍、巡线、农林植保、军事、侦查、救灾、消防、通信中继、地质勘察、城市管理。 3.本外观设计产品的设计要点：在于形状。 4.最能表明设计要点的图片或照片：立体图。 | ||||||
| 270 | 交叉双旋翼复合推力尾桨无人直升机 | CN201830099029.9 | 2018-03-16 | CN304694297S | 2018-06-22 | 海日汗; 李京阳; 包长春; 印明威; 王贤宇 |
| 1．本外观设计产品的名称：交叉双旋翼复合推力尾桨无人直升机。 2．本外观设计产品的用途：本外观设计产品用于测绘、航拍、勘察、巡线、个人运动等执行飞行任务的无人机。 3．本外观设计产品的设计要点：产品形状。 4．最能表明本外观设计设计要点的图片或照片：设计1立体图。 5．指定基本设计：设计1。 6．本产品为相似外观设计。 | ||||||
| 271 | 尾旋翼(模型直升飞机) | CN200730085421.X | 2007-12-11 | CN300879497D | 2009-01-28 | 曹嘉鸿 |
| 272 | Aft exhaust system for rotary wing aircraft | EP13187935.5 | 2013-10-09 | EP2719621A2 | 2014-04-16 | Pantalone III, Joseph; Chapkovich III, John S.; DeVito, Ashley; Weiner, Steven D. |
An exhaust system (100, 150, 170) for reducing infrared emissions of a rotary wing aircraft (10) includes a duct assembly having an inlet portion (102, 152, 172) and an outlet portion (104, 154, 174); the inlet portion configured to receive exhaust from an engine (E) of the aircraft; and the outlet portion coupled to the inlet portion, the outlet portion having an outlet duct (124, 156, 178) with an outlet opening (126, 158, 180), the outlet duct configured expel an emission containing engine exhaust proximate to a tail fairing (33) of the rotary wing aircraft.
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| 273 | Dispositif anti-couple à rotor arrière et stator redresseur carénés pour hélicoptère | EP95401000.5 | 1995-05-02 | EP0680875B1 | 1998-04-01 | Dequin, André-Michel Louis; Daldosso, Louis Joseph; Barquet, Henri Fernand |
| 274 | Dispositif anti-couple à rotor et stator redresseur carénés, et à aubes redresseuses inclinées | EP95400998.1 | 1995-05-02 | EP0680873B1 | 1998-04-01 | Marze, Henri-James Richard; Routhieau, Vincent Jean-Luc; Arnaud, Gilles Louis; Arnaud, Rémy Elian |
| 275 | Helicopter antitorque tail rotor blade | EP08425368.1 | 2008-05-22 | EP2123557B1 | 2011-04-27 | Brocklehurst, Alan; Scandroglio, Alessandro |
| 276 | DUCTED FAN AND PITCH CONTROLS FOR TAIL ROTOR OF ROTARY WING AIRCRAFT | EP92918217.8 | 1992-07-31 | EP0597038B1 | 1999-01-20 | DESJARDINS, Rene, A.; McCARDLE, Francis, H. |
| A tail rotor (8) for a rotary wing aircraft is located in a laterally directed duct (9) located at the end of a tail cone (7) extending rearward from the aircraft cabin and at the base of an empennage (5) extending upward from the duct. The rotor includes a rotor shaft (50) driveably connected to a power source, a rotor hub (10) connected to the rotor shaft (50), a rotating control shaft (64), a stationary control shaft (124), and an actuator (132) connected to the stationary control shaft (124) for moving the rotating control shaft (64) axially. The rotor hub (10) includes rotor arms (12) each supporting a pitch shaft-blade spar (18, 16) assembly for pivotable movement about a pitch axis. A pitch beam (96) supports flexures (94), each connected to a pitch arm (80) offset laterally from the associated pitch axis. The flexures (94) driveably connect the pitch arms (80) to the pitch beam (96) and transmit pitch control motion to the blades (14) as the pitch beam (96) moves along the rotor axis. Pitch bearings (20, 22), on which the pitch shafts (18) turn about the pitch axes, are supported on a rotor hub shell (46) fixed to the rotor hub (10). | ||||||
| 277 | Aéronef à voilure tournante muni d'un rotor arrière et procédé pour optimiser le fonctionnement d'un rotor arrière | EP13000285.0 | 2013-01-21 | EP2631174B1 | 2017-03-15 | Dyrla, Nadine |
| 278 | Helicopter antitorque tail rotor blade | EP08425367.3 | 2008-05-22 | EP2123556B1 | 2010-12-08 | Brocklehurst, Alan; Scandroglio, Alessandro |
| 279 | Aéronef à voilure tournante muni d'un rotor arrière et procédé pour optimiser le fonctionnement d'un rotor arrière | EP13000285.0 | 2013-01-21 | EP2631174A1 | 2013-08-28 | Dyrla, Nadine |
La présente invention concerne un aéronef (1) à voilure tournante muni d'un rotor principal (2) de sustentation, d'un rotor arrière (5), d'une installation motrice (4) entraînant une boîte de transmission de puissance (3) coopérant avec ledit rotor principal (2), ledit rotor arrière (5) étant pourvu d'une pluralité de pales (10) à pas (I) variable et d'un dispositif de modification du pas (20), ledit aéronef (1) ayant un moyen de commande (30) dudit dispositif de modification du pas (20). L'aéronef (1) inclut un moteur électrique (9) pour mettre en rotation ledit rotor arrière (5) et un moyen de régulation (TRCU) relié au moyen de commande (30) ainsi qu'au moteur électrique (9) et au dispositif de modification du pas (20).
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| 280 | ROTARY WING AIRCRAFT WITH AN INTERFACE FRAME JOINING THE FUSELAGE TAIL BOOM AND THE TAIL CONE | US15416067 | 2017-01-26 | US20170327200A1 | 2017-11-16 | Stefan PROBST; Philipp WALCH; Marc NOTHEN; Christian BUXEL; Romed SCHWEIZER; Thomas WUERFL |
| A rotary wing aircraft comprising a fuselage tail boom, a tail cone and an interface frame, the interface frame in turn having a connecting structure directly attached to the tail cone by means of a tail cone mechanical connection and a connecting sleeve fitting axially the fuselage tail boom, the connecting sleeve and the fuselage tail boom being directly attached by means of a one boom mechanical connection; the interface frame thereby joining the fuselage tail boom and the tail cone. | ||||||
