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21. 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。

22. 发明公开

EP3016859A4 PROPULSION SYSTEM FOR AN AERIAL VEHICLE 有权
标题翻译： ANTRIEBSSYSTEMFÜREINE FLUGVORRICHTUNG
公开(公告)号：EP3016859A4
公开(公告)日：2017-04-26
申请号：EP14816561
申请日：2014-06-25
申请人： FÖRSVARETS MATERIELVERK
发明人： PRISELL ERIK
IPC分类号： B64C39/00 , B64C15/02 , B64C21/04
CPC分类号： B64C39/005 , B64C15/02 , B64C21/04 , B64C21/06 , B64C21/08 , B64C29/0025 , B64C2039/105 , B64D27/18 , Y02T50/166
摘要： The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, “CTOL” (Conventional Take Off and Landing), “Chair” and for vertical takeoff and landing, “V (t) OL” (Vertical (Take) Off and Landing’) and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles.
摘要翻译：本发明涉及一种推进系统概念，其是集成在飞行器（1）的船体中的推进系统，该推进概念包括至少一个差速风扇（4），该差速风扇布置在由一个或更多动力装置（2）。推进概念旨在提供短距起飞和着陆距离，高飞行速度（高亚音速到超音速），并能够提供低红外特征，低雷达特征，小横截面和低空气阻力。推进概念被称为HPVO（高性能优化多功能推进）。本发明对于常规起飞和着陆类型的飞行器，“CTOL”（常规起飞和着陆），“椅子”和用于垂直起飞和着陆，“V（t）OL”（垂直（Take）关和着陆'）和飞翼（混合体）。该概念适用于大型和小型飞机，载人飞行器和无人飞行器。

23. 发明授权

EP2591996B1 ELLIPTICAL FUSELAGE WITH WING TO BODY VOLUME INTEGRATED IN PRESSURISED CABIN 有权
标题翻译： DIL DRUCKKABINE INTEGRIERTEM的身体健康
公开(公告)号：EP2591996B1
公开(公告)日：2017-01-18
申请号：EP12192304.9
申请日：2012-11-12
申请人： The Boeing Company
发明人： Campbell, Lowell B.
IPC分类号： B64C1/00
CPC分类号： B64C1/00 , B64C2001/0045 , B64C2039/105

24. 发明公开

EP2991896A1 RECESSED LIFT SPOILER ASSEMBLY FOR AIRFOILS 有权
标题翻译： RECESSED升降扰流组件技术WINGS
公开(公告)号：EP2991896A1
公开(公告)日：2016-03-09
申请号：EP14792283.5
申请日：2014-04-28
申请人： Northrop Grumman Systems Corporation
发明人： EMERICK, Mark F.
IPC分类号： B64C21/02
CPC分类号： B64C21/02 , B64C39/10 , B64C2039/105 , B64C2230/06 , Y02T50/166
摘要： A spoiler assembly is provided that is engageable to a UAV that defines a body, an outer surface and an inner surface. The spoiler assembly comprises a spoiler, translatably connected to the UAV inner surface adjacent a first portion of the spoiler aperture. The spoiler defines an upper surface and an outer surface, the upper surface being substantially the same size and shape as the spoiler aperture. A spoiler shroud is connected to the UAV inner surface and extends within the UAV body about at least a portion of the spoiler aperture. A spoiler activating mechanism is secured to the UAV inner surface and connected the spoiler lower surface. The mechanism is operative to translate the spoiler between a first position wherein the spoiler upper surface is substantially flush with the UAV outer surface, and second a position, wherein the spoiler upper surface is disposed substantially within the UAV body.

25. 发明授权

EP2193079B1 OBLIQUE BLENDED WING BODY AIRCRAFT 有权
标题翻译：具有集成的船体CANT无尾飞机
公开(公告)号：EP2193079B1
公开(公告)日：2015-04-22
申请号：EP08798974.5
申请日：2008-08-29
申请人： Advanced Product Development, Llc
发明人： MCDONNELL, William, Randall
IPC分类号： B64C39/10 , B64C3/10 , B64C30/00
CPC分类号： B64C3/10 , B64C30/00 , B64C39/10 , B64C2039/105 , Y02T50/12
摘要： An oblique wing aircraft (1) designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment (27) on one side of the wing and an aft swept wing segment (29) on the opposite side of the wing. A center oblique airfoil section (25) connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. The center oblique airfoil section is not shaped solely to function as a circular fairing to fill the gap between an oblique wing and a fuselage at different oblique wing angles, nor is it a second wing in an X wing configuration. Preferably, the aircraft is an all-wing aircraft.

26. 发明公开

EP2582581A2 ANGETRIEBENES FLUGGERÄT, INSBESONDERE ALS NURFLÜGLER UND/ODER MIT GERINGER RADARSIGNATUR AUSGEBILDETES FLUGGERÄT 有权转让
标题翻译：动力飞行仪器，特别是作为一个飞翼和/或低雷达信号飞行大队经过培训
公开(公告)号：EP2582581A2
公开(公告)日：2013-04-24
申请号：EP11785286.3
申请日：2011-06-14
申请人： EADS Deutschland GmbH
发明人： BICHLER, Bartholomäus , DORNWALD, Jochen , WEDEKIND, Gerhard
IPC分类号： B64D33/02 , B64C39/10 , B64D27/16
CPC分类号： B64D33/02 , B64C39/10 , B64C2039/105 , B64D27/16 , B64D2033/0286
摘要： The invention relates to an aircraft (10), comprising a fuselage body, a wing body (12), and at least one drive flow passage (16), which extends from an air inlet (18) directed forward (+x) on the body surface (14) via a jet engine (20) through the body (12) to a propelling nozzle (22) that opens toward the rear (-x) on the body surface (14). In order to enable greater design freedom in regard to the shape of the body (12), in particular in the manner of a flying wing having improved flight properties compared to known aircrafts, and/or to achieve an extreme reduction in the radar signature of the aircraft (10), at least one part of the jet engine (20), in particular the entire jet engine (20), is arranged upstream of the air inlet (18) as viewed in the flying direction (+x) of the aircraft (10) and the drive flow passage (16) has curvature sections (24, 28) designed and arranged suitably therefor.

27. 发明授权

EP1924496B1 EINRICHTUNG ZUR NOT-EVAKUIERUNG, INSBESONDERE FÜR EIN NURFLÜGEL-FLUGZEUG 有权
标题翻译：设备进行紧急疏散，特别是对于一个飞翼式飞机
公开(公告)号：EP1924496B1
公开(公告)日：2009-03-25
申请号：EP06792072.8
申请日：2006-09-14
申请人： Airbus Deutschland GmbH
发明人： ANGER, André , SCHÖNE, Wolfram
IPC分类号： B64C39/10 , B64D25/08
CPC分类号： B64C39/10 , B64C2039/105 , B64D25/08 , B64D25/14
摘要： A system for selective emergency evacuation of persons from a first level (I) to a second level (II) located above the first level (I) or to a third level (III) located under the first level comprises for evacuation to the upper level a stairs-shaped arrangement (1). According to the invention, the system is connected at one end with the first level (I) and at the other end it can be displaced between the upper level (II) and the lower level (III) or vice-versa, and can be altered to take the form of a slide (2) for evacuation to the lower level (III). In particular, the system can be advantageously used for selective emergency evacuation of persons from a deck which forms the first level (I), in particular a passenger deck (17) of a tailless aeroplane (20), to the upper side (18) of the tailless aeroplane (20), which forms the second, upper level (II), or to the underside (19) of the tailless aeroplane (20), which forms the third, lower level (III).

28. 发明公开

EP1818257A2 Integrated inward turning inlets and nozzles for hypersonic air vehicles 审中-公开
标题翻译： Integrierte，nach innen gedrehteEinlassöffnungenundDüsenfürhypersonische Luftfahrzeuge
公开(公告)号：EP1818257A2
公开(公告)日：2007-08-15
申请号：EP07102293.3
申请日：2007-02-13
申请人： Lockheed Martin Corporation
发明人： Elvin, John D.
IPC分类号： B64C30/00 , B64D27/20 , B64D33/02
CPC分类号： B64C30/00 , B64C2039/105 , B64D2033/026 , Y02T50/12
摘要： A hypersonic waverider aircraft is disclosed that includes a first engine (106) and an inlet including a throat (108). The inlet is configured to generate three-dimensional flow compression during hypersonic flight with a weak shock wave that begins at the leading edge surfaces of the inlet and coalesces ahead of the throat, and a weak shock wave that begins at the point of coalescence of the weak shock wave and extends to the throat. The inlet includes a v-shaped lip open to freestream airflow in one side of the inlet.
摘要翻译：公开了一种超音速摇摆飞机，其包括第一发动机（106）和包括喉部（108）的入口。入口被配置为在超音速飞行期间产生三维流动压缩，其中弱冲击波从入口的前缘表面开始并在喉部之前聚结，并且在聚结点处开始的弱冲击波弱冲击波延伸到喉咙。入口包括一个v形嘴，可以在入口一侧的自由气流中开口。

29. 发明授权

EP1620310B1 FLUGGERÄT MIT AUFTRIEB ERZEUGENDEM RUMPF 有权
标题翻译： WITH LIFT-产生船体FLIGHT UNIT
公开(公告)号：EP1620310B1
公开(公告)日：2006-06-28
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.

30. 发明授权

EP1167183B1 Blended wing and multiple-body airplane configuration 无效
标题翻译：集成的翅膀和几个船体飞机配置
公开(公告)号：EP1167183B1
公开(公告)日：2005-08-24
申请号：EP01115913.4
申请日：2001-06-29
申请人： The Boeing Company
发明人： Sankrithi, Mithra M.K.V. , Wald, Steven J.
IPC分类号： B64C39/04
CPC分类号： B64C39/04 , B64C2039/105 , Y02T50/12

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