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公开(公告)号：EP3168147A4
公开(公告)日：2017-12-13
申请号：EP15819516
申请日：2015-08-14
CPC分类号： B64D27/20 , B64C15/02 , B64C25/00 , B64C27/10 , B64C27/18 , B64C27/22 , B64C29/00 , B64C39/001 , B64D2221/00 , F01D5/02 , F01D5/12 , F01D7/00 , F02K7/00 , F04D19/02 , F05D2220/90
摘要： The invention relates to aviation technology, specifically to vertical take-off and landing aircraft. The vertical take-off and landing aircraft comprises two turbines, the lower of which is of plate-like shape, and the upper is of flat or plate-like shape. Each turbine comprises a reactive power plant. The body of each turbine is mounted on a metallic disc connected to a vertical shaft of the aircraft, and is equipped with vanes. The vanes are mounted such that the position thereof can be changed. The aircraft can comprise intermediate turbines which are mounted between the upper and lower turbine and are flat or plate-like. The reactive power plant of each turbine comprises an air engine and receivers which are connected to a compressor. The body of each turbine is metallic and comprises two rings, one of which is connected to the disc, and also radial struts which are mounted along the perimeter of the turbine body and are connected to the rings and vanes. The vanes are mounted in a single row along the perimeter of the body or are arranged in a single tier. The result is an increase in the reliability and economy of the aircraft, and the possibility of the latter moving vertically, horizontally or at any inclination.
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公开(公告)号：EP2814734A1
公开(公告)日：2014-12-24
申请号：EP13709050.2
申请日：2013-02-13
申请人： Reiter, Johannes
发明人： Reiter, Johannes
CPC分类号： B64C27/00 , B64C3/385 , B64C27/001 , B64C27/16 , B64C27/18 , B64C29/00 , B64C29/0033 , B64C29/0075 , B64C29/02 , B64C39/008 , B64C39/024 , B64C2201/088 , B64C2201/102 , B64C2201/104 , B64C2201/108 , B64C2201/165
摘要： The present invention relates to a device for generating aerodynamic lift and in particular an aircraft (100) for vertical take-off and landing. A wing arrangement (110) comprises at least one propulsion unit (111), wherein the propulsion unit (111) comprises a rotating mass which is rotatable around a rotary axis (117). The wing arrangement (110) is mounted to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis (112) of the wing arrangement (110) and such that the wing arrangement (110) is rotatable with respect to the fuselage (101) around a further rotary axis that differs to the longitudinal wing axis (112). An adjusting mechanism adjusts a tilting angle of the wing arrangement (110) around the longitudinal wing axis (112) under influence of a precession force (Fp) which forces the wing arrangement (110) to tilt around the longitudinal wing axis (112).
摘要翻译： 用于产生气动升力的装置技术领域本发明涉及一种用于产生气动升力的装置，尤其涉及一种用于垂直起飞和着陆的飞机（100）。 机翼装置（110）包括至少一个推进单元（111），其中推进单元（111）包括可围绕旋转轴线（117）旋转的旋转质量。 机翼装置（110）安装到机身（101），使得机翼装置（110）可围绕机翼装置（110）的纵向机翼轴线（112）倾斜并且使得机翼装置（110）可旋转 相对于机身（101）绕与纵向机翼轴线（112）不同的另一旋转轴线旋转。 调节机构在迫使机翼布置（110）围绕纵向机翼轴线（112）倾斜的进动力（Fp）的影响下调节机翼布置（110）围绕纵向机翼轴线（112）的倾斜角度。
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公开(公告)号：EP1799543B1
公开(公告)日：2008-06-11
申请号：EP05858416.0
申请日：2005-09-14
申请人： The Boeing Company
摘要： A rotational position-adjusting system (6) for a vertical takeoff and landing aircraft (4) . The system (6) includes multiple detectors (60) that generate rotor signals. The rotor signals are indicative of the position of each rotor (8) of the aircraft (4) . The rotors (8) provide lift to the aircraft (4) . A controller (24) is coupled to the detectors (60) and adjusts the rotational speed of one or more of the rotors (8) in response to the rotor signals.
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公开(公告)号：EP2814735A1
公开(公告)日：2014-12-24
申请号：EP13710309.9
申请日：2013-02-13
申请人： Reiter, Johannes
发明人： Reiter, Johannes
CPC分类号： B64C27/00 , B64C3/385 , B64C27/001 , B64C27/16 , B64C27/18 , B64C29/00 , B64C29/0033 , B64C29/0075 , B64C29/02 , B64C39/008 , B64C39/024 , B64C2201/088 , B64C2201/102 , B64C2201/104 , B64C2201/108 , B64C2201/165
摘要： The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).
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公开(公告)号：EP2209714A1
公开(公告)日：2010-07-28
申请号：EP08847942.3
申请日：2008-11-06
申请人： Heliscandia Aps
发明人： LADING, Gert
摘要： A rotor system for an aircraft including a rotor (1) with a drive part (2) mounted rotatable about a rotation axis (8) and supporting the proximal end (9) of at least one rotor blade (3).The rotor system comprises a jet turbine (4) for providing pressurised exhaust gas to a rotary structure(7) having at least one jet nozzle outlet (6) and at least one jet stream duct (5) for transporting the pressurised exhaust gas from the turbine (4) to the jet nozzle outlet (6) to cause rotation of the rotary structure (7) by expelling the pressurised exhaust gas through the nozzle outlet (6). In addition, only the rotary structure(7) and not the rotor blade (3) comprise a jet stream duct (5) and a nozzle outlet (6).
摘要翻译： 一种用于飞行器的转子系统，所述转子系统包括具有绕旋转轴线（8）可旋转地安装并且支撑至少一个转子叶片（3）的近端（9）的驱动部分（2）的转子（1）。所述转子系统包括 用于将加压排气提供给具有至少一个喷嘴出口（6）的旋转结构（7）的喷气涡轮机（4）和用于将来自涡轮机（4）的加压排气输送的至少一个喷流管道（5） 到喷嘴出口（6）以通过将加压排气通过喷嘴出口（6）排出而引起旋转结构（7）的旋转。 另外，只有旋转结构（7）而不是转子叶片（3）包括喷射流管道（5）和喷嘴出口（6）。
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公开(公告)号：EP2117927A2
公开(公告)日：2009-11-18
申请号：EP08787768.4
申请日：2008-03-06
摘要： The invention relates to a rotary seal that comprises first (7, 8) and second (7, 8) parts mobile relative to each other about a rotation axis (A). The first and second mobile parts (7, 8) each include an interface area (30) having a plurality of protruding and recessed members with complementary shapes, the protruding and recessed members of one part (7, 8) engaging the protruding and recessed members of the other part (7, 8) in order to define decompression chambers with an increasing volume, the interface areas being located at a distance from each other without any friction between them.
摘要翻译： 本发明涉及一种旋转密封件，其包括围绕旋转轴线（A）相对于彼此可移动的第一部件（7,8）和第二部件（7,8）。 第一移动部件和第二移动部件（7,8）各自包括界面区域（30），该界面区域具有多个具有互补形状的突出和凹陷构件，一个部件（7,8）的突出和凹陷构件接合突出和凹陷构件 的另一部分（7,8），以便限定具有增大的体积的减压腔室，所述界面区域彼此间隔开设置而彼此间没有任何摩擦。
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9.发明公开Engine propulsion system having first and second exhaust ducts 有权Antriebssystem eines Triebwerks mit einem ersten und zweiten Abgaskanal
公开(公告)号：EP1936173A2
公开(公告)日：2008-06-25
申请号：EP07254054.5
申请日：2007-10-12
发明人： Peck, Robert Andrew
摘要： An engine assembly (10) includes a first engine (102), a first exhaust duct (114) coupled in fluid communication only to the first engine, and a first exhaust duct includes a primary outlet and a secondary outlet. An engine assembly (10) further includes a second engine (104) including a second exhaust duct (116) coupled in fluid communication only to the second engine, the second exhaust duct includes a primary outlet and a secondary outlet, and a portion of the first engine secondary outlet is aligned substantially concentrically within a portion of the second engine secondary outlet. The first and second exhaust ducts (114,116) are coupled to a first and second wing outlet (632,654) and a first and second rotor outlet.
摘要翻译： 发动机组件（10）包括第一发动机（102），仅与第一发动机流体连通的第一排气管道（114），以及包括主出口和次级出口的第一排气管道。 发动机组件（10）还包括第二发动机（104），其包括仅与第二发动机流体连通的第二排气管道（116），第二排气管道包括主出口和次级出口，以及一部分 第一发动机二次出口在第二发动机次级出口的一部分内基本上同心地排列。 第一和第二排气管道（114,116）联接到第一和第二翼出口（632,654）和第一和第二转子出口。
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公开(公告)号：EP0140914A1
公开(公告)日：1985-05-15
申请号：EP84901289.0
申请日：1984-03-01
申请人： RAMME, Maurice , RAMME, Monte
发明人： RAMME, Maurice , RAMME, Monte
IPC分类号： B64C27
摘要： Un gyrodyne biréacteur à aile haute possède des rotors contra-rotatifs à réaction de jet d'air (4 et 5) entraînés par l'air de dilution provenant de deux moteurs à double flux (6). Des tuyères (7) montées depuis les moteurs à double flux (6) sont disposées parallèlement et de chaque côté d'un conduit longitudinal (10) permettant de décharger vers l'arrière l'air de dilution. Des soupapes de commande (91) peuvent commander sélectivement l'alimentation en air de dilution au mât creux (3) des rotors pour entraîner les rotors (4 et 5) ainsi qu'au conduit longitudinal de décharge d'air (10). Les parties arrière des tuyères (7) et du conduit de décharge d'air (10) sont reliées par un stabilisateur horizontal (18) et des gouvernes (93 et 92) sont situées dans le souffle de l'hélice déchargé par les tuyères (7) et le conduit de décharge d'air (10). L'aile (2) possède des sections de bouts d'aile inclinables vers le bas (14) servant de balancines de flottaison dans leur position verticale vers le bas.
摘要翻译： 高翼双引擎金字塔具有反向旋转的喷气式空气转子（4和5），由两个双流引擎（6）的稀释空气驱动。 从双流发动机（6）安装的喷嘴（7）平行布置并且在纵向管道（10）的每侧上用于向后排出稀释空气。 控制阀（91）可选择性地控制稀释空气供给至转子的中空桅杆（3），用于驱动所述转子（4和5）与纵向空气排放管（10）。 喷嘴（7）和所述排气管道（10）的后端部分由一个水平稳定器（18）和控制面（93和92）位于从所述喷嘴喷出的滑流（连接 7）和排气管道（10）。 机翼（2）具有向下呈锥形的翼尖部分（14），用作处于垂直向下位置的漂浮巴拉琴。
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