-
公开(公告)号：EP1594736B1
公开(公告)日：2012-12-19
申请号：EP04809283.7
申请日：2004-02-19
Applicant: AAI CORPORATION
Inventor： MILLER, Stephen, W. , VELAZQUEZ, Matthew, T.
IPC: B64F1/04
CPC classification number: B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/084 , B64C2201/102 , B64C2201/165 , B64C2201/201 , B64C2201/203 , B64F1/06
-
公开(公告)号：EP2516256A2
公开(公告)日：2012-10-31
申请号：EP10843503.3
申请日：2010-12-17
Applicant: Tufts University
Inventor： BRIGHT, Alfram, V. , WLEZIEN, Richard
CPC classification number: B64C3/30 , B64C3/56 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/102 , B64C2201/127 , D06M10/001 , D06M10/10 , D06M15/327 , E04H12/00 , F03D13/20 , H05G2/00 , Y02E10/728
Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements which find use in rapidly deploying and supporting the wing of an aerial vehicle.
-
公开(公告)号：EP2234876A1
公开(公告)日：2010-10-06
申请号：EP08768886.7
申请日：2008-01-31
Applicant: Raytheon Company
Inventor： SANDERSON, Terry, M. , CLARK, Jamie, W.
IPC: B64C3/38
CPC classification number: B64C3/54 , B64C3/56 , B64C2201/102 , F42B10/14 , F42B10/143 , F42B10/20 , Y02T50/14
Abstract: Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator.
-
公开(公告)号：EP1799545A1
公开(公告)日：2007-06-27
申请号：EP05789189.7
申请日：2005-02-14
Applicant: RAYTHEON COMPANY
Inventor： CORDER, David, A. , KOESSLER, Jeffrey, H. , WEBB, George, R.
IPC: B64C39/02
CPC classification number: B64C3/56 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/082 , B64C2201/102 , B64C2201/123 , B64C2201/127 , B64C2201/141 , B64C2201/145 , B64C2201/165 , B64C2201/201
Abstract: An air-launched aircraft (10) includes deployable wings (16, 18), elevons (20, 22), and vertical fins (26, 28) that deploy from a fuselage (12) during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module (14) that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and/or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.
-
公开(公告)号：EP1761430A2
公开(公告)日：2007-03-14
申请号：EP05761246.7
申请日：2005-04-14
Applicant: Arlton, Paul E. , Arlton, David J.
Inventor： Arlton, Paul E. , Arlton, David J.
IPC: B64C27/10
CPC classification number: B64C27/10 , B64C27/22 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/082 , B64C2201/102 , B64C2201/108 , B64C2201/141 , B64C2201/146 , B64C2201/165 , B64C2201/201 , B64C2201/203 , B64C2201/205
Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.
-
Patent Agency Ranking
公开(公告)号：EP1594736A2
公开(公告)日：2005-11-16
申请号：EP04809283.7
申请日：2004-02-19
Applicant: AAI CORPORATION
Inventor： MILLER, Stephen, W. , VELAZQUEZ, Matthew, T.
IPC: B64B1/00
CPC classification number: B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/084 , B64C2201/102 , B64C2201/165 , B64C2201/201 , B64C2201/203 , B64F1/06
Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.
-
公开(公告)号：EP1257466A2
公开(公告)日：2002-11-20
申请号：EP01937143.4
申请日：2001-02-07
Applicant: Aerovironment Inc.
Inventor： MACCREADY, Paul , HIBBS, Bart, D. , COX, Earl, C. , LISOSKI, Derek, L. , KENDALL, Greg, T.
IPC: B64D27/24
CPC classification number: B64C3/42 , B64C3/52 , B64C15/02 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/102 , B64C2201/122 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64D27/24 , B64D31/06 , B64D2211/00 , G05D1/0022 , G05D1/0077 , H04B7/18504 , Y02T50/12 , Y02T50/14 , Y02T50/44 , Y02T50/55 , Y02T50/62
Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.
-
公开(公告)号：EP1257465A2
公开(公告)日：2002-11-20
申请号：EP01934833.3
申请日：2001-02-12
Applicant: Aerovironment Inc.
Inventor： MACCREADY, Paul , HIBBS, Bart, D. , COX, Earl, C. , LISOSKI, Derek, L. , KENDALL, Greg T.
CPC classification number: B64C3/42 , B64C3/52 , B64C15/02 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/102 , B64C2201/122 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64D27/24 , B64D31/06 , B64D2211/00 , G05D1/0022 , G05D1/0077 , H04B7/18504 , Y02T50/12 , Y02T50/14 , Y02T50/44 , Y02T50/55 , Y02T50/62
Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.
-
公开(公告)号：WO2017207666A2
公开(公告)日：2017-12-07
申请号：PCT/EP2017/063221
申请日：2017-05-31
Applicant: HYBRID-AIRPLANE TECHNOLOGIES GMBH
Inventor： SINGER, Csaba
IPC: B64B1/08 , B64C1/08 , B64C1/12 , B64C1/26 , B64C1/34 , B64C3/32 , B64C3/38 , B64C11/00 , B64C13/50 , B64C39/00 , B64D27/24 , B64C37/02 , B64C27/24 , B64B1/18 , B64B1/20 , B64B1/32 , B64B1/38 , B64B1/58 , B64C39/02
CPC classification number: B64B1/58 , B64B1/08 , B64B1/18 , B64B1/20 , B64B1/32 , B64B1/38 , B64B2201/00 , B64C1/08 , B64C1/12 , B64C1/26 , B64C1/34 , B64C3/32 , B64C3/385 , B64C11/001 , B64C17/02 , B64C25/04 , B64C25/06 , B64C27/24 , B64C37/02 , B64C39/001 , B64C39/022 , B64C39/024 , B64C2001/0045 , B64C2001/0072 , B64C2201/021 , B64C2201/022 , B64C2201/024 , B64C2201/042 , B64C2201/101 , B64C2201/102 , B64C2201/108 , B64C2201/127 , B64C2201/128 , B64C2201/162 , B64D27/24 , Y02T50/43 , Y02T50/64
Abstract: Die Erfindung betrifft ein Fluggerät mit einer Tragstruktur (12) und einer von der Tragstruktur (12) aufgespannten, mit einem Gas befüllbaren Hülle (10). Erfindungsgemäß ist vorgesehen, dass die Tragstruktur (12) eine Mehrzahl von Stab- oder Rohrabschnitten (24-30) aufweist, die eine kreisförmige, ovale oder polygonale Hauptspannebene für die Hülle (10) definieren.
Abstract translation: 本发明涉及一种具有支撑结构（12）和由支撑结构（12）跨越的透气船体（10）的飞机。 发明＆AUML;大街 设想支撑结构（12）包括限定用于船体（10）的圆形，椭圆形或多边形主应力平面的多个杆或管段（24-30）。
-
公开(公告)号：WO2017025704A1
公开(公告)日：2017-02-16
申请号：PCT/GB2016/050521
申请日：2016-02-29
Applicant: WIRTH RESEARCH LIMITED
Inventor： WIRTH, Nicholas
CPC classification number: B64C3/56 , B64C3/16 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/141 , B64C2201/146 , B64C2201/201
Abstract: An unmanned aerial vehicle (2) comprising: a fuselage (4); and a wing (6) comprising a central wing section (12) pivotably mounted to the fuselage (4) and a pair of outer wing sections (14a, 14b) pivotably mounted to the central wing section (12); wherein the wing (6) has a folded configuration in which the central wing section (12) and the outer wing sections (14a, 14b) are stacked on top of one another and are aligned with a longitudinal axis of the fuselage (4); and a deployed configuration in which the central wing section (12) is substantially perpendicular to the fuselage (4) and the outer wing sections (14a, 14b) extend from the central wing section (12) away from the fuselage (4).
Abstract translation: 一种无人驾驶飞行器（2），包括：机身（4）; 以及包括可枢转地安装到所述机身（4）的中心翼部（12）和可枢转地安装到所述中心翼部（12）的一对外翼部分（14a，14b）的翼部（6）。 其中所述机翼（6）具有折叠构造，其中所述中心翼部分（12）和所述外翼部分（14a，14b）彼此堆叠并且与所述机身（4）的纵向轴线对齐; 以及中央翼部（12）基本上垂直于机身（4）并且外翼部分（14a，14b）从中心翼部分（12）远离机身（4）延伸的展开构造。
-
-
-
-
-
-
-
-
-
Search Results
568
records
(took 0.037 seconds)
