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公开(公告)号：EP3444185A1
公开(公告)日：2019-02-20
申请号：EP17193024.1
申请日：2017-09-25
摘要： An unmanned aircraft system (10) has a vertical takeoff and landing flight mode and a forward flight mode. The unmanned aircraft system (10) includes an airframe (12), a rotor assembly (34) rotatably coupled to the airframe (12) and a propeller (48) rotatably coupled to the airframe (12). The rotor assembly (34) includes at least two rotor blades (40a-b) having tip jets (42a-b) that are operably associated with a compressed gas power system (50). The propeller (48) is operably associated with an electric power system (52). In the vertical takeoff and landing flight mode, compressed gas from the compressed gas power system (50) is discharged through the tip jets (42a-b) to rotate the rotor assembly (34) and generate vertical lift. In the forward flight mode, the electric power system (52) drives the propeller (48) to generate forward thrust and autorotation of the rotor assembly (34) generates vertical lift.
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公开(公告)号：EP3434592A1
公开(公告)日：2019-01-30
申请号：EP18184104.0
申请日：2018-07-18
摘要： An aircraft (10) having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft (10) includes a fuselage (12) and a dual tiltwing assembly (18) having a vertical lift orientation and a forward thrust orientation relative to the fuselage (12). The dual tiltwing assembly (18) includes a forward wing (20) and an aft wing (22) coupled together and to the fuselage (12) by a quadrilateral linkage (70). A distributed propulsion system is coupled to the dual tiltwing assembly (18) and includes a plurality of forward propulsion assemblies (24) coupled to the forward wing (20) and a plurality of aft propulsion assemblies (24) coupled to the aft wing (22). A flight control system (60) is operably associated with the distributed propulsion system and the dual tiltwing assembly (18). The flight control system (60) is operable to independently control each of the propulsion assemblies (24) and is operable to transition the dual tiltwing assembly (18) between the vertical lift orientation and the forward thrust orientation.
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公开(公告)号：EP3486170B1
公开(公告)日：2019-08-28
申请号：EP17206154.1
申请日：2017-12-08
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公开(公告)号：EP3385160A1
公开(公告)日：2018-10-10
申请号：EP17205736.6
申请日：2017-12-06
IPC分类号： B64C27/26
CPC分类号： B64C27/26 , B64C9/04 , B64C27/28 , B64C2027/8245 , B64C2201/024 , B64D27/10 , B64D27/24
摘要： A helicopter (100) has a fuselage (102), a main rotor system (110) connected to the fuselage (102) and configured to rotate in a rotor direction, the main rotor system (110) comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing (106) extending from the fuselage (102) on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counterrotating rotor system coaxial with the main rotor system (110).
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公开(公告)号：EP3290338B1
公开(公告)日：2018-09-12
申请号：EP17163295.3
申请日：2017-03-28
IPC分类号： B64C29/02
摘要： A tail sitter aircraft (10) includes a fuselage (12) having a forward portion (14) and an aft portion (16). The forward portion (14) of the fuselage (12) includes first and second rotor stations (18, 20). A first rotor assembly (22) is positioned proximate the first rotor station (18). A second rotor assembly (24) is positioned proximate the second rotor station (20). A tailboom assembly (26) extends from the aft portion (16) of the fuselage (12). The tailboom assembly (26) includes a plurality of landing members (28). In a vertical takeoff and landing mode of the aircraft (10), the first and second rotor assemblies (22, 24) rotate about the fuselage (12) to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly (22) rotates about the fuselage (12) to provide forward thrust and the second rotor assembly (24) is non-rotatable about the fuselage (12) forming wings to provide lift.
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公开(公告)号：EP3415424B1
公开(公告)日：2019-06-12
申请号：EP18167037.3
申请日：2018-04-12
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公开(公告)号：EP3486170A1
公开(公告)日：2019-05-22
申请号：EP17206154.1
申请日：2017-12-08
摘要： A stacked motor assembly (100) for an aircraft (10) includes a forward motor (102) having an exhaust port and an aft motor (104) disposed aft of the forward motor (102), the aft motor having an intake port (120). The stacked motor assembly (38) includes an exhaust conduit (140) originating from the exhaust port (118) of the forward motor (102) and disposed at least partially around the aft motor (104) such that exhaust from the forward motor (102) bypasses the aft motor (104). The stacked motor assembly (38) also includes an intake conduit (142) terminating at the intake port (120) of the aft motor (104) and disposed at least partially around the forward motor (102) such that intake air for the aft motor (104) bypasses the forward motor (102).
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公开(公告)号：EP3290336A1
公开(公告)日：2018-03-07
申请号：EP17163296.1
申请日：2017-03-28
CPC分类号： B64C27/82 , B64C27/28 , B64C27/52 , B64C29/0033 , B64C39/008 , B64C2027/8245 , B64C2027/8254
摘要： In some embodiments, an aircraft (10) includes a fuselage (12) having a forward portion (23) and an aft portion (13). First and second ducted fans (24, 28) are supported by the forward portion (23) of the fuselage (12). The first and second ducted fans (24, 28) are tiltable relative to the fuselage (12) between a generally horizontal orientation, in a vertical takeoff and landing mode, and a generally vertical orientation, in a forward flight mode. A tailboom (14) having an aft station (62) extends from the aft portion (13) of the fuselage (12). A cross-flow fan (64) is disposed in the aft station (62) of the tailboom (14) and is operable to generate a pitch control moment.
摘要翻译： 在一些实施例中，飞机（10）包括具有前部（23）和后部（13）的机身（12）。 第一和第二管道风扇（24,28）由机身（12）的前部（23）支撑。 在向前飞行模式下，第一和第二管道风扇（24,28）相对于机身（12）在垂直起飞和着陆模式下的大致水平取向与大致垂直取向之间可倾斜。 具有后部站（62）的尾杆（14）从机身（12）的后部（13）延伸。 横流式风扇（64）设置在尾梁（14）的尾部站（62）中并且可操作以产生桨距控制力矩。
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公开(公告)号：EP3444185B1
公开(公告)日：2020-02-19
申请号：EP17193024.1
申请日：2017-09-25
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