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1. 发明公开

EP3048048A1 AN AIRCRAFT 失效
公开(公告)号：EP3048048A1
公开(公告)日：2016-07-27
申请号：EP15201624.2
申请日：2015-12-21
申请人： Rolls-Royce plc
发明人： Moxon, Matthew
IPC分类号： B64D27/02 , B64D27/14
CPC分类号： B64D27/10 , B64C39/10 , B64C2039/105 , B64D27/02 , B64D27/14
摘要： An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32 - 42) defining a respective rotational plane (D 32 - D 42 ). The rotational plane (D 32 - D 42 ) of at least one of the rotors (32 - 42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b).
摘要翻译：一种飞行器（2）包括至少第一和第二燃气涡轮发动机（10a，10b），所述第一和第二燃气涡轮发动机（10a，10b）布置成大致垂直于飞机纵轴线（A）延伸的直线，每个发动机（10a，10b）包括至少一个压缩机或涡轮转子盘（32-42）限定相应的旋转平面（D32-D42）。至少一个发动机（10a，10b）的至少一个转子（32-42）的旋转平面（D32-D42）相对于飞机纵向线（A）倾斜，使得爆破盘平面相应的发动机（10a，10b）与另一个发动机（10a，10b）不相交。

2. 发明公开

EP2812241A1 A METHOD FOR GENERATING LIFT AND A DEVICE FOR IMPLEMENTING THE METHOD 审中-公开
标题翻译：方法产生升力装置用于实施过程
公开(公告)号：EP2812241A1
公开(公告)日：2014-12-17
申请号：EP12867734.1
申请日：2012-02-06
申请人： Hirvinen, Raimo , Hirvinen, Jani , Hirvinen, Toni
发明人： Hirvinen, Raimo , Hirvinen, Jani , Hirvinen, Toni
IPC分类号： B64C3/14 , B64C23/00
CPC分类号： B64C1/0009 , B64C3/14 , B64C5/08 , B64C2001/0045 , B64C2003/144 , B64C2039/105
摘要： The object of the invention is a method for generating lift for an airborne flying device, which has a wing part and/or a fuselage part generating lift by means of interactive movement between the air and the device. In the method, in the frontal view area of the lift-generating part of the device is arranged at least one counterflow impulse surface (1), which is formed by a planar or curved surface extending forward in the direction of travel from the lower surface (2) of the wing and/or fuselage and obliquely upwards, and which generates at least the main part of the lift when the airflow hits this inclined impulse surface and bends when the device is airborne.

3. 发明授权

EP2089273B1 AVION A EMPENNAGES ARRIERES ANNULAIRES 有权
标题翻译：平面环形HECK
公开(公告)号：EP2089273B1
公开(公告)日：2011-06-08
申请号：EP07870354.3
申请日：2007-11-29
申请人： AIRBUS OPERATIONS (S.A.S)
发明人： CAZALS, Olivier , DRUOT, Thierry
IPC分类号： B64C5/02 , B64C11/00 , B64C39/06 , B64D27/02
CPC分类号： B64D27/16 , B64C5/02 , B64C2039/105 , Y02T50/44
摘要： The invention relates to a rear tail assembly (1) for an aircraft, including a fuselage (3), a wing (2) and at least one propulsion engine (5, 5a, 5b) attached in the rear portion of the fuselage located behind the wing (2) along the X longitudinal axis of the aircraft, wherein said assembly comprises aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially comprises essentially horizontal aerodynamic surfaces (41a, 41b, 43) and essentially vertical aerodynamic surfaces (42a, 42b) arranged so as to form an annular structure including at least one ring attached to the fuselage. At least one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area.

4. 发明授权

EP1631493B1 AIRCRAFT WITH TOPSIDE ONLY SPOILERS 有权转让
标题翻译：带扰流板只在顶平面
公开(公告)号：EP1631493B1
公开(公告)日：2006-11-22
申请号：EP04809418.9
申请日：2004-05-26
申请人： NORTHROP GRUMMAN CORPORATION
发明人： CLARK, Walter, D.
IPC分类号： B64C1/00 , B64C5/08 , B64C9/12 , B64C9/32 , B64C9/34 , B64C39/02
CPC分类号： B64C1/0009 , B64C5/08 , B64C9/12 , B64C9/32 , B64C9/323 , B64C9/34 , B64C39/024 , B64C2001/0045 , B64C2039/105 , B64C2201/028 , B64C2201/127 , B64C2201/22 , Y02T50/12 , Y02T50/32 , Y02T50/44
摘要： An aircraft (10) with swept back wings (16, 18) and spoilers (30,32) inlaid into the top surface (36) near the tips of the wings. The aircraft also includes an elevator (34) formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings.

5. 发明公开

EP1620310A1 FLUGGERÄT MIT AUFTRIEB ERZEUGENDEM RUMPF 有权
标题翻译： FLUGGERÄTMIT AUFTRIEB ERZEUGENDEM RUMPF
公开(公告)号：EP1620310A1
公开(公告)日：2006-02-01
申请号：EP04741518.7
申请日：2004-05-05
申请人： Team Smartfish GmbH
发明人： SCHAFROTH, Konrad
IPC分类号： B64C1/00 , B64C3/10 , B64C39/10
CPC分类号： B64C1/0009 , B64C3/10 , B64C39/10 , B64C2001/0045 , B64C2039/105 , Y02T50/12
摘要： The invention relates to an aircraft comprising: a lift-generating fuselage (1), the largest span (11) of said fuselage being in the third fifth (15) or the four fifth (17) of the total length thereof, and the outline of the fuselage progressively tapering off in the first fifth (13) and in the last fifth (18); two wings (2), the surface of the projection of said two wings in a horizontal plane representing less than thirty per cent of the entire lift area, and the wings being located in said third fifth (15) or fourth fifth (17) of the total length of the fuselage; and an elevator unit (4) located on the last fifth (18) of the fuselage. The longitudinal central profile of the aircraft has a negative curvature, and the longitudinal profile of the wings has a positive curvature. The form of the inventive aircraft resembles the form of a fish.
摘要翻译：本发明涉及一种飞行器，包括：升力产生机身（1），所述机身的最大跨距（11）在其总长度的第三十五（15）或第四十五（17）中，以及轮廓的机身在前五分之一（13）和后五分之一（18）逐渐减少; 两个翼部（2），所述两个翼部在水平面中的投影表面表示小于整个升力面积的百分之三十，并且所述翼部位于所述第三第五（15）或第四（五）（17）机身的总长度; 和位于机身的最后五（18）处的升降机单元（4）。飞机的纵向中心轮廓具有负曲率，并且翼的纵向轮廓具有正曲率。本发明的飞机的形式类似于鱼的形式。

6. 发明公开

EP1444130A1 FLUGGERÄT MIT EINEM AUFTRIEB ERZEUGENDEN RUMPF 有权
标题翻译：与升力产生船体飞行大队
公开(公告)号：EP1444130A1
公开(公告)日：2004-08-11
申请号：EP02771971.5
申请日：2002-11-06
申请人： Team Smartfish GmbH
发明人： SCHAFROTH, Konrad
IPC分类号： B64C1/00 , B64C3/10 , B64C39/00 , B64C39/10
CPC分类号： B64C1/0009 , B64C3/10 , B64C39/10 , B64C2001/0045 , B64C2039/105 , Y02T50/12
摘要： The invention relates to an aircraft comprising a lift-producing fuselage (1) whose largest span (11) lies in the middle third (14) of the total length and whose horizontal projection progressively diminishes in the front third (13) and in the rear third (15). The aircraft also comprises two wings (2), whereby the surface of the projection of both wings represents, in a horizontal plane, less than thirty percent of the total lift surface, and the wings are located in the middle third (14) of the total length of the fuselage. The aircraft additionally comprises a horizontal tail unit (4) situated in the rear third of the fuselage. The aircraft has a shape similar to that of a fish.

7. 发明授权

EP1099626B1 Aft egress and control device for an aircraft 有权
标题翻译：用于飞行器Hecknotausgangs-和控制装置
公开(公告)号：EP1099626B1
公开(公告)日：2003-04-02
申请号：EP00203468.4
申请日：2000-10-06
申请人： The Boeing Company
发明人： Philips Whitlock, Jennifer , Rawdon, Blaine K. , Wakayama, Sean R.
IPC分类号： B64C39/10
CPC分类号： B64D11/00 , B64C1/22 , B64C3/00 , B64C39/10 , B64C2039/105

8. 发明公开

EP1243782A2 Double jet engine inlet 有权
标题翻译： Doppelter Einlass eines Strahltriebwerks
公开(公告)号：EP1243782A2
公开(公告)日：2002-09-25
申请号：EP02075713.4
申请日：2002-02-22
申请人： THE BOEING COMPANY
发明人： Seidel, Gerhard E.
IPC分类号： F02K1/38
CPC分类号： F02C7/04 , B64C2039/105 , B64D33/02 , B64D2033/026 , F02K3/04 , Y02T50/12
摘要： A dual boundary layer engine inlet for a turbofan propulsion engine of an aircraft having a first air inlet positioned generally within the boundary layer flowing around the exterior surface of the aircraft. A first passageway fluidly interconnects the first air inlet and the turbofan propulsion engine to provide air from the boundary layer to the bypass to reduce aerodynamic drag. A second air inlet is positioned generally outside of the boundary layer. This second passageway fluidly interconnecting the second air inlet and the turbofan propulsion engine to provide air outside of the boundary layer to the core and compressor of the turbofan engine to maintain engine efficiency.
摘要翻译：一种用于飞行器的涡轮风扇推进发动机的双边界层发动机入口，其具有通常位于围绕飞行器的外表面流动的边界层内的第一空气入口。第一通道将第一空气入口和涡轮风扇推进发动机流体地互连，以将空气从边界层提供到旁路以减少气动阻力。第二空气入口通常位于边界层的外侧。该第二通道将第二进气口和涡轮风扇推进发动机流体地相互连接，以将边界层外部的空气提供给涡轮风扇发动机的核心和压缩机，以保持发动机效率。

9. 发明公开

EP1099626A1 Aft egress and control device for an aircraft 有权
标题翻译： Hecknotausgangs- und Steuerungsvorrichtungfürein Flugzeug
公开(公告)号：EP1099626A1
公开(公告)日：2001-05-16
申请号：EP00203468.4
申请日：2000-10-06
申请人： The Boeing Company
发明人： Philips Whitlock, Jennifer , Rawdon, Blaine K. , Wakayama, Sean R.
IPC分类号： B64C39/10
CPC分类号： B64D11/00 , B64C1/22 , B64C3/00 , B64C39/10 , B64C2039/105
摘要： An aircraft (20) having a cabin (26) within a wing (24) of the aircraft includes an access opening (34,38) in an aft end of the cabin adjacent a trailing edge of the wing, and a trailing edge portion (22) of the wing juxtaposed with the access opening and including at least one pivotable panel which is pivotable into an open position so as to form a passage in the trailing edge portion for entry therethrough and through the access opening into the cabin. The trailing edge portion in one embodiment comprises upper and lower panels which are normally in converging relation such that the passage to the access opening of the cabin is normally closed, but which are pivotable relative to each other for creating the passage. The lower panel preferably is pivotable into a generally horizontal position so that it serves as a ramp for loading and unloading persons and cargo into and from the cabin. The upper and/or lower panel in another embodiment may be pivoted during flight so as to serve as a control surface for the aircraft. The lower panel in still another embodiment is pivotable into a downwardly angled position extending down from the wing so as to serve as a slide for emergency evacuation of the cabin.
摘要翻译：在飞行器的翼（24）内具有舱（26）的飞机（20）包括在机舱的后端附近的机翼后缘处的进入开口（34,38）和后缘部分 22），其与所述进入开口并置并且包括至少一个可枢转的可枢转的面板，所述可枢转面板可枢转到打开位置，以便在所述后缘部分中形成通道，以通过所述通道进入所述舱室。在一个实施例中的后缘部分包括通常处于会聚关系的上面板和下面板，使得通向舱室的进入开口的通道是常闭的，但是可相对于彼此枢转以产生通道。下面板优选地可枢转到大致水平的位置，使得其用作用于将人员和货物装载和从客舱中卸载的斜坡。在另一个实施例中，上部和/或下部面板可以在飞行中枢转，以便作为飞行器的控制面。在另一个实施例中的下面板可枢转到从机翼向下延伸的向下成角度的位置，以便用作用于紧急撤离舱室的滑动件。

10. 发明公开

EP3386858A1 BLENDED WING BODY AIRCRAFT 审中-公开
公开(公告)号：EP3386858A1
公开(公告)日：2018-10-17
申请号：EP16805904.6
申请日：2016-11-30
申请人： Bombardier Inc. , Short Brothers Plc
发明人： BANERJEE, Siddhartho , GALIN, Alexandre
IPC分类号： B64C39/10
CPC分类号： B64C39/10 , B64C1/0009 , B64C3/14 , B64C2039/105 , Y02T50/12
摘要： A blended wing body aircraft having an interior cabin with a usable volume of at most 4500 ft3 and a cabin aspect ratio of at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.7 and at most 2.8. Also, a blended wing body aircraft having an interior cabin with a usable volume of at least 1500 ft3 and at most 4500 ft3 and a cabin aspect ratio of at least 2 and at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.9 and at most 2.7. Also, a blended wing body aircraft wherein at least each profile section having normalized half-span values from 0 to 0.3 has a leading edge having a normalized height having a nominal value within the range set forth in Table 4.

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