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1. 发明授权

EP1941148B1 TURBOFAN ENGINE FOR STOL AIRCRAFT 有权
标题翻译：涡扇短距起降的飞机
公开(公告)号：EP1941148B1
公开(公告)日：2011-02-23
申请号：EP06794894.3
申请日：2006-10-25
申请人： Avcen Limited
发明人： DACRE, Mike
IPC分类号： F02K3/02 , B64C29/00 , F02K1/00
CPC分类号： B64C29/0066 , F02K1/386 , F02K3/06 , F02K3/075 , F05D2300/612 , F05D2300/614 , Y02T50/671
摘要： A module (10) for use with a bypass turbofan engine. The module comprises a hot flow channel through which the hot gas flow generated by the engine can flow and a bypass flow channel (14) through which the bypass air generated by the engine can flow. Part of the bypass air may be re-directed to be exhausted from the module at an angle relative to the longitudinal axis of the module so as to create vertical thrust. The hot flow channel may be separated from the bypass flow channel by a porous separator (12) that allows a degree of mixing between the hot gas flowing in the hot gas flow channel and the cold gas flowing in the cold gas flow channel.

2. 发明公开

EP2933188A1 VTOL aircraft with a thrust-to-weight ratio smaller than 0.1 审中-公开
标题翻译： Senkrechtstarterflugzeug mit einemSchubgewichtsverhältniskleiner als 0,1
公开(公告)号：EP2933188A1
公开(公告)日：2015-10-21
申请号：EP14075023.3
申请日：2014-04-17
申请人： Chen, Li Jing
发明人： Chen, Li Jing
IPC分类号： B64C29/00 , B64C21/04
CPC分类号： B64C29/00 , B64C9/00 , B64C15/02 , B64C21/04 , B64C23/005 , B64C29/005 , B64C29/0066 , B64C2009/005 , B64D27/16 , Y02T50/166
摘要： An aircraft includes: ailerons (1,2); a turbofan engine (3) comprising a high-temp duct (4) with an openable/ closable propelling nozzle (5), and a low-temp duct (6) with an openable/closable propelling nozzle (7); a high-temp bypass duct (9) comprising an openable/closable inlet (8) connected to the high-temp duct(4), an outer wall(10) and a rectangle outlet(12) with a height-to-width ratio smaller than 0.1; a low-temp bypass duct (15) comprising an openable/closable inlet (14) connected to the low-temp duct (7), an outer wall (16), an inner wall (17) and a rectangle outlet (19) with a height-to-width ratio smaller than 0.1. During vertical take-off/lading, closing the propelling nozzles (5, 7) of turbofan engine (3), and opening the inlets (8,14) of high-temp and low-temp bypass ducts(9,15), low-temp planar air jet (20) is cause to flow over upper surface of the aircraft, thereby generating lift and no air flow over lower one.
摘要翻译：飞机包括：副翼（1,2）; 涡轮风扇发动机（3）包括具有可打开/关闭的推进喷嘴（5）的高温管道（4）和具有可打开/关闭的推进喷嘴（7）的低温管道（6）; 包括连接到高温管道（4）的可打开/关闭的入口（8）的高温旁通管道（9），外壁（10）和矩形出口（12），高度 - 宽度比小于0.1; 包括连接到低温管道（7）的可打开/关闭的入口（14）的低温旁通管道（15），外壁（16），内壁（17）和矩形出口（19）高度比宽度小于0.1。在垂直起飞期间，关闭涡轮风扇发动机（3）的推进喷嘴（5,7），并打开高温和低温旁通管道（9,15）的入口（8,14），低 - 平面空气喷射（20）导致飞行器的上表面流动，从而产生升力，而不会在较低的空气流中流动。

3. 发明公开

EP1195512A2 Flow blocking exhaust nozzle 有权
标题翻译： VerschliessbareStrahldüse
公开(公告)号：EP1195512A2
公开(公告)日：2002-04-10
申请号：EP01308422.3
申请日：2001-10-02
申请人： GENERAL ELECTRIC COMPANY
发明人： Bentley, David Todd
IPC分类号： F02K1/00 , F02K1/12
CPC分类号： B64C29/0066 , B64C15/02 , B64D33/04 , F02K1/006 , F02K1/1223 , F02K1/62 , F02K1/805
摘要： An exhaust nozzle (10) for an aircraft engine includes a mount (20) for attaching the nozzle (10) to a downstream end of the engine and first and second opposed upstream flaps (30) moveably connected to the mount (20) having inner surfaces (34) defining an upstream exhaust gas flow path. Each upstream flap (30) extends between an upstream end and a downstream end and is moveable relative to the mount (20) between an open position in which the downstream ends of the upstream flaps (30) are spaced by a first distance, and a closed position in which the downstream ends touch to substantially block flow through the exhaust gas flow path. First and second opposed downstream flaps (50) are moveably connected to the first and second upstream flaps (30) having inner surfaces (52) defining a downstream exhaust gas flow path.
摘要翻译：用于飞机发动机的排气喷嘴（10）包括用于将喷嘴（10）附接到发动机的下游端的安装件（20）和可移动地连接到具有内部的安装件（20）的第一和第二相对的上游翼片（30）限定上游废气流动路径的表面（34）。每个上游翼片（30）在上游端和下游端之间延伸并且可相对于安装座（20）在打开位置之间移动，在该打开位置中，上游翼片（30）的下游端部间隔第一距离，关闭位置，其中下游端接触以基本上阻挡通过废气流动路径的流动。第一和第二相对的下游翼片（50）可移动地连接到具有限定下游排气流动路径的内表面（52）的第一和第二上游翼片（30）。

4. 发明授权

EP1474328B1 CONTROL SYSTEM FOR VERTICAL TAKE OFF AND LAND (VTOL) AIRCRAFT 有权
标题翻译：控制系统的垂直起始平面
公开(公告)号：EP1474328B1
公开(公告)日：2013-05-29
申请号：EP03713425.1
申请日：2003-02-10
申请人： Dupont Aerospace Company, Inc.
发明人： DUPONT, Anthony A, Dupont Aerospace Company, Inc.
IPC分类号： B64C1/00
CPC分类号： F02K1/00 , B64C15/02 , B64C29/0066 , B64D33/04 , F02K1/002 , F02K3/025

5. 发明公开

EP1474328A4 CONTROL SYSTEM FOR VERTICAL TAKE OFF AND LAND (VTOL) AIRCRAFT 有权
标题翻译：控制系统的垂直起始平面
公开(公告)号：EP1474328A4
公开(公告)日：2010-07-14
申请号：EP03713425
申请日：2003-02-10
申请人： DUPONT AEROSPACE COMPANY INC
发明人： DUPONT ANTHONY A
IPC分类号： B64C13/30 , B64C15/02 , B64C29/00 , B64D33/04 , F02K1/00 , F02K3/02 , B64C1/00
CPC分类号： F02K1/00 , B64C15/02 , B64C29/0066 , B64D33/04 , F02K1/002 , F02K3/025

6. 发明公开

EP0959000A1 Lift enhancing and drag reducing device for aircraft 审中-公开
标题翻译：自动化系统
公开(公告)号：EP0959000A1
公开(公告)日：1999-11-24
申请号：EP99500030.4
申请日：1999-02-23
申请人： Munoz Saiz, Manuel
发明人： Munoz Saiz, Manuel
IPC分类号： B64C30/00 , B64C29/00
CPC分类号： B64C29/0066 , B64C30/00
摘要： The device for lift and to reduce forward resistance of aircraft consists of a converging input duct of truncated-cone-shaped or truncated-pyramid-shaped, arranged lengthwise inside the fuselage and inclined to the longitudinal axis, with the larger opening coinciding with the front fuselage contour or periphery of maximum cross-section, and reducing in bore backwards so that its generatrix or lower side coincides with the lower surface of the fuselage parallel to the aircraft's longitudinal axis and the generatrix or upper edge forms an acute angle with the aircraft's longitudinal axis. The narrowest end of the duct discharges into the input of the turbofan, UHD, etc. type drive engines which discharge through a rear outlet duct facing backwards with the rear end curved slightly downward.
摘要翻译：用于提升和降低飞机前进阻力的装置包括一个截头锥形或截头棱锥形的会聚输入管道，纵向设置在机身的内侧并且与纵向轴线倾斜，较大的开口与前部机身轮廓或最大横截面的周边，并向下减少孔，使其母线或下侧与机身的下表面平行于飞机的纵向轴线重合，母线或上边缘与飞机纵向形成锐角轴。管道的最窄端部排放到涡轮风扇，UHD等型驱动发动机的输入端，该驱动发动机通过后向后方的出口管道向后排出，后端稍微向下弯曲。

7. 发明公开

EP3263454A1 VTOL AIRCRAFT WITH A THRUST-TO-WEIGHT RATIO SMALLER THAN 0.1 有权
标题翻译： VTOL AIRCRAFT的推重比小于0.1
公开(公告)号：EP3263454A1
公开(公告)日：2018-01-03
申请号：EP17020335.0
申请日：2014-04-17
申请人： Chen, Li Jing
发明人： Chen, Li Jing
IPC分类号： B64C29/00 , B64C21/04
CPC分类号： B64C29/00 , B64C9/00 , B64C15/02 , B64C21/04 , B64C23/005 , B64C29/005 , B64C29/0066 , B64C2009/005 , B64D27/16 , Y02T50/166
摘要： VTOL aircraft with a thrust-to-weight ratio smaller than 0.1, during vertical take-off/landing, obtains an another lift, besides a lift generated by low-temp bypass duct (15) directing the low-temp air (18) from the turbofan engine (3) to flow, through its outlet (19) in form of low-temp planar jet (20), over the upper surface of the wing and in the direction of the wingspan, by high-temp bypass duct (15) directing the high-temp air (18) from the turbofan engine (3) to flow, through its outlet (12) in form of high-temp planar jet (13), above the low-temp planar jet (20) in the direction of the wingspan and enables the ailerons (1, 2) to control the balances of the aircraft more efficiently.
摘要翻译：在垂直起飞/着陆期间推力重量比小于0.1的VTOL飞机除了由低温旁路导管（15）引导低温空气（18）产生的升力之外还获得另一升力涡轮风扇发动机3通过其低温平面射流20形式的出口19流过机翼上表面和翼展方向，并通过高温旁路导管15 ）将来自涡轮风扇发动机（3）的高温空气（18）引导通过其高温平面射流（13）形式的其出口（12），在低温平面射流（20）并且使副翼（1,2）更有效地控制飞机的平衡。

8. 发明授权

EP1195512B1 Flow blocking exhaust nozzle 有权
标题翻译：密封喷
公开(公告)号：EP1195512B1
公开(公告)日：2010-07-07
申请号：EP01308422.3
申请日：2001-10-02
申请人： GENERAL ELECTRIC COMPANY
发明人： Bentley, David Todd
IPC分类号： F02K1/12 , F02K1/80 , F02K1/00
CPC分类号： B64C29/0066 , B64C15/02 , B64D33/04 , F02K1/006 , F02K1/1223 , F02K1/62 , F02K1/805

9. 发明公开

EP1195512A3 Flow blocking exhaust nozzle 有权
标题翻译：密封喷
公开(公告)号：EP1195512A3
公开(公告)日：2004-01-14
申请号：EP01308422.3
申请日：2001-10-02
申请人： GENERAL ELECTRIC COMPANY
发明人： Bentley, David Todd
IPC分类号： F02K1/12 , F02K1/80 , F02K1/00
CPC分类号： B64C29/0066 , B64C15/02 , B64D33/04 , F02K1/006 , F02K1/1223 , F02K1/62 , F02K1/805
摘要： An exhaust nozzle (10) for an aircraft engine includes a mount (20) for attaching the nozzle (10) to a downstream end of the engine and first and second opposed upstream flaps (30) moveably connected to the mount (20) having inner surfaces (34) defining an upstream exhaust gas flow path. Each upstream flap (30) extends between an upstream end and a downstream end and is moveable relative to the mount (20) between an open position in which the downstream ends of the upstream flaps (30) are spaced by a first distance, and a closed position in which the downstream ends touch to substantially block flow through the exhaust gas flow path. First and second opposed downstream flaps (50) are moveably connected to the first and second upstream flaps (30) having inner surfaces (52) defining a downstream exhaust gas flow path.

10. 发明公开

EP0866764A1 MULTI-SERVICE COMMON AIRFRAME-BASED AIRCRAFT 失效
标题翻译：澳大利亚杰出人造林基金会MEHRZWECK-FLUGZEUG
公开(公告)号：EP0866764A1
公开(公告)日：1998-09-30
申请号：EP96945928.0
申请日：1996-12-09
申请人： THE BOEING COMPANY
发明人： BURNHAM, Robert, W. , FITZPATRICK, Michael, F. , MUILENBERG, Dennis, A. , SCHOEBELEN, Joseph, K. , TROLLEN, Laurence, B.
IPC分类号： B64C1 , B64C29
CPC分类号： B64C1/0009 , B64C1/061 , B64C29/00 , B64C29/0066 , B64C2039/105 , B64C2211/00
摘要： A modular approach to the manufacture of high performance military aircraft allows different aircraft to be manufactured at affordable cost and with high part number commonality. An aircraft so constructed includes a delta wing (4); a forebody section (28), including a cockpit (2), which is mounted to the front of the wing (4), and a propulsion system support frame (23) mounted beneath the forebody section (28) and the underside of the wing (4). The propulsion system (10) is supported within this frame. The aircraft can also include an aftbody section (20) mounted to the aft end of the wing (4), which includes a 2-D variable thrust vectoring nozzle (11) and a pair of canted vertical tails (6). The forebody section (28) includes a chin inlet (9) below the cockpit. The wing (4) is preferably constructed using thermoplastic welding.
摘要翻译：制造高性能军用飞机的模块化方法允许不同的飞机以可承受的成本和高数量的共同性制造。如此构造的飞机包括三角翼; 前身部分，包括安装在机翼前部的驾驶舱; 以及安装在机翼的前体部分和下侧之下的推进系统支撑框架。在此框架内支持推进系统。飞机还可以包括安装在机翼的后端的船尾部分，其包括2-D可变推力向量喷嘴和一对倾斜垂直尾部。前身部分包括驾驶舱下方的下巴入口。翼优选地使用热塑性焊接构造。

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