| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 沿着翼展具有可变的掠过分布的航空器升力表面 | CN201310294209.9 | 2013-07-12 | CN103538717A | 2014-01-29 | 安赫尔·帕斯夸尔富埃尔特斯; 塞尔希奥·罗德里格斯桑切斯 |
| 本发明提供了航空器升力表面(43，73)，连接至航空器机身的后端或前端(11，10)，且在内侧部分(45，75)中具有可变的掠角α和在外侧部分(47，77)中具有恒定的掠角α1。航空器升力表面可以例如是连接至后端机身(11)的水平尾部平面(43)或竖直尾部平面或连接前端机身(10)的水平稳定面(73)。 | ||||||
| 2 | 飞机结构的罩盖件 | CN200580011410.5 | 2005-04-18 | CN100532196C | 2009-08-26 | 克里斯蒂安·曼茨 |
| 本发明涉及一种具有表皮和支撑结构的飞机的垂直尾翼和水平尾翼及机翼的整流装置的端头部件，所述表皮(2)设置在支撑结构(4，6)上。所述支撑结构设置有多个肋(6)和多个桁条(4)。多个桁条设置在多个肋上，以支撑表皮，并且所述多个桁条(4)适于在物体(10)撞击所述表皮(2)时发生变形，从而吸收由所述撞击所产生的大部分能量。有利地，例如在有鸟撞击的情形下可获得改进的变形，同时通过设置桁条将重量和成本降到最小。 | ||||||
| 3 | 飞机结构的罩盖件 | CN200580011410.5 | 2005-04-18 | CN1942363A | 2007-04-04 | 克里斯蒂安·曼茨 |
| 本发明涉及一种具有表皮和支撑结构的飞机的垂直尾翼和水平尾翼及机翼的整流装置的端头部件，所述表皮(2)设置在支撑结构(4，6)上。所述支撑结构设置有多个肋(6)和多个桁条(4)。多个桁条设置在多个肋上，以支撑表皮。有利地，例如在有鸟撞击的情形下可获得改进的变形，同时通过设置桁条将重量和成本降到最小。 | ||||||
| 4 | Fairing for aircraft structure | JP2007507775 | 2005-04-18 | JP2007532397A | 2007-11-15 | クリスティアン メンツ |
| 本発明は、外板及び支持構造を有する、航空機の垂直尾翼及び水平尾翼並びに主翼のフェアリングのノーズ部に関する。 外板（２）は支持構造（４、６）上に配置されている。 この支持構造は、複数のリブ（６）及び複数のストリンガー（４）を有する。 複数のストリンガーは、外板を支持するために、複数のリブ上に配設されている。 有利には、ストリンガーを配設することにより、例えば、鳥の衝突時における変形の挙動について改善するとともに、重量及びコストを最小限に抑えることができる。
【選択図】図１ |
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| 5 | Assembly and method for operating rotatable member around rotary shaft rotatably, aircraft, assembly for controlling aircraft, and canard assembly for aircraft | JP2004133508 | 2004-04-28 | JP2004323012A | 2004-11-18 | JONES KELLY T |
| PROBLEM TO BE SOLVED: To provide a device and a method for operating a rotatable member. SOLUTION: In one embodiment, the assembly for operating the rotatable member includes an extendable actuator having a first end part and a second end part and a driving member having a first part pivotally coupled to the second end part and a second part non-pivotally coupled to the rotatable member. The second part of the driving member is arranged apart from the first part. The driving member has a third part arranged apart from the first and second parts in orientation in which they are not arranged in parallel in the same linear order. This assembly includes a reaction link having a fixed end pivotally coupled to the first end part of the extendable actuator and a driving end pivotally coupled to the third part of the driving member. COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 6 | Aircraft, apparatus, and method for manufacturing aircraft | JP2003359643 | 2003-10-20 | JP2004142737A | 2004-05-20 | JONES KELLY T |
| <P>PROBLEM TO BE SOLVED: To provide a method and an apparatus for actuating movable elements including a canard over a plurality of ranges. <P>SOLUTION: The apparatus includes a canard 120 connected to a plurality of actuators 160. One of the actuator moves the canard over a first moving range, and the other actuator moves it over a second extended moving range. A lockout device can prevent the actuation over the second range except when a selected condition is satisfied. <P>COPYRIGHT: (C)2004,JPO | ||||||
| 7 | Fairing for aircraft structure | JP2007507775 | 2005-04-18 | JP4699448B2 | 2011-06-08 | クリスティアン メンツ |
| 8 | For the movable wing of the aircraft, to operate the rotatable member device | JP2004133508 | 2004-04-28 | JP4646543B2 | 2011-03-09 | ケリー・ティ・ジョーンズ |
| 9 | High manoeuverable aircraft and flight method thereof | JP8196286 | 1986-04-09 | JPS621695A | 1987-01-07 | TOOMASU EICHI SUTOROOMU |
| 10 | Canard assembly for an aircraft system and aircraft | JP2003359647 | 2003-10-20 | JP4319004B2 | 2009-08-26 | ケリー・ティ・ジョーンズ; ジョゼフ・アール・ピネダ; デービッド・エル・バス; ピィ・ブライアン・マッキニー |
| 11 | Method for manufacturing an aircraft, the apparatus and the aircraft | JP2003359643 | 2003-10-20 | JP4319003B2 | 2009-08-26 | ケリー・ティ・ジョーンズ |
| 12 | Canard assembly for aircraft system and aircraft | JP2003359647 | 2003-10-20 | JP2004142738A | 2004-05-20 | BATH DAVID L; JONES KELLY T; MCKINNEY P BRIAN; PINEDA JOSEPH R |
| <P>PROBLEM TO BE SOLVED: To provide a method and a device for supporting moving elements including a canard so that it can rotate. <P>SOLUTION: The canard assembly contains a wing type formed so that it is located outside the aircraft fuselage, and its connection 140 can have an attachment part 641 which can hang from the wing type part and formed so that it is attached to the aircraft inside the aircraft body. A roller supported by one side of the connection and the fuselage can come into contact with a raceway supported by the other side of the connection and the fuselage so that it can rotate. <P>COPYRIGHT: (C)2004,JPO | ||||||
| 13 | High-mobility aircraft and how flight | JP8196286 | 1986-04-09 | JP2534666B2 | 1996-09-18 | TOOMASU EICHI SUTOROOMU |
| 14 | 드론의 부속기기 결합장치 | KR1020160031749 | 2016-03-16 | KR101776951B1 | 2017-09-08 | 이건희 |
| 본발명은기기고정장치에관한것으로, 더욱상세하게는무인조정비행기의동체에 주변기기의고정위치를쉽게찾아삽입에의해고정함으로써기기의고정이용이하고고정된기기가외부충격에의해분리가가능하여외부충격시무인조정비행기의동체또는주변기기의추가파손을방지할수 있는드론의부속기기결합장치에관한것이다. 상기의본 발명은비행기본체에가이드홀이형성된고정판을이중으로형성한본체부와, 상기본체부의가이드홀에삽입되어가이드되도록기기에형성된밀착판에카본으로형성된가이드돌기를형성한기기부와, 상기기기부의밀착판과본체부의고정판과동일한위치에고정자석을형성하여기기부와본체부가자력에의해고정되도록형성한고정부로구성되는것을특징으로한다. | ||||||
| 15 | HYBRID PROPULSION VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP17701961.9 | 2017-01-12 | EP3402718A1 | 2018-11-21 | GIANNINI, Francesco; GOMEZ, Martin; COTTRELL, Dan; LEDE, Jean-Charles; ROBERTS, Tom; SCHAEFER, Carl, Jr.; COLAS, Dorian; WHIPPLE, Brian; NUHFER, Tim; HUNTER, Herb; GROHS, Jonathon; PETULLO, Steve |
| A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft. | ||||||
| 16 | CANARD-LOCKED OBLIQUE WING AIRCRAFT | EP14709508.7 | 2014-02-25 | EP2961652B1 | 2017-01-04 | SOMMER, Geoffrey S.; COTE, Kenneth A. |
| An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for supersonic flight and disconnected from each other for subsonic flight. | ||||||
| 17 | Apparatus and methods for actuating rotatable members | EP04076261.9 | 2004-04-28 | EP1473223B1 | 2008-01-09 | Jones, Kelly T. |
| 18 | Method and apparatus for rotatably supporting movable components, including canards | EP03078323.7 | 2003-10-21 | EP1413782B1 | 2006-06-21 | Bath, David L.; Jones, Kelly T.; McKinney, P. Brian; Pineda, Joseph R. |
| 19 | Efficient wing tip devices and methods for incorporating such devices into existing wing designs | EP04076872.3 | 2004-06-29 | EP1493660A1 | 2005-01-05 | McLean, James D. |
Efficient wing tip devices (110) for use with aircraft wings (104). In one embodiment, an aircraft wing/winglet combination (105) includes a wing having a wing (104) root portion (236) and a wing tip portion (238) spaced apart from the wing root portion (236). The wing tip portion (238) can have a wash-out twist relative to the wing root portion. The aircraft wing/winglet combination (105) can further include a winglet (110) extending from the wing tip portion (238) of the wing. The winglet (110) can be swept at least generally forward relative to the wing (104) to favorably change the lift distribution on the wing and in turn reduce the induced drag on the wing. |
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| 20 | CANARD-LOCKED OBLIQUE WING AIRCRAFT | EP14709508.7 | 2014-02-25 | EP2961652A1 | 2016-01-06 | SOMMER, Geoffrey S.; COTE, Kenneth A. |
| An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for supersonic flight and disconnected from each other for subsonic flight. | ||||||
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