| 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 | 高安全性的飞行器 | CN200580051008.X | 2005-07-07 | CN101223079B | 2012-08-01 | A·卡布阿尼 |
| 飞行器(10)包括设置有推进装置和方向控制安定面的细长框架结构(26)。框架结构联接到气腔(16)，该气腔适于填充比空气轻的气体并包括两个连接成V形外形的管状分支(12、14)，且在两管状分支之间延伸有空气动力学升力表面(22、24)。 | ||||||
| 2 | 一种适宜水、陆两栖起降飞行的动力三角翼飞行器 | CN200810031506.3 | 2008-06-16 | CN101607596A | 2009-12-23 | 何清华; 邹湘伏 |
| 本发明公开了一种适宜水、陆两栖起降飞行的动力三角翼飞行器，包括底部平台，该底部平台通过操纵机构与机翼相连，底部平台上安装有承载支架，该承载支架的前端设有乘员位置，该承载支架的后端安装发动机，发动机连接螺旋桨，所述底部平台的底部安装有可收缩的起降着陆轮装置，所述操纵机构与所述起降着陆轮装置连接，当通过操纵机构控制起降着陆轮装置伸出时，该动力三角翼飞行器能够在陆地起降，当通过操纵机构控制起降着陆轮装置收回到底部平台内部时，该动力三角翼飞行器能够实现在水面起降。 | ||||||
| 3 | 一种能垂直起降的三角翼飞行器 | CN201710139330.2 | 2017-03-10 | CN106882372A | 2017-06-23 | 王志成; 李玉龙; 罗哲远; 谭俭辉 |
| 一种能垂直起降的三角翼飞行器，属于航空技术领域，尤其涉及一种三角翼飞行器；包括机身、操纵杆、航电设备、动力系统和控制计算机；当飞行器起飞时，控制计算机开启四轴飞行模式，在操纵杆上控制飞行器垂直升起向前飞行，抬升悬挂翼；在达到一定速度后，控制计算机开启动力滑翔模式，后方向的发动机带动旋翼为飞行器产生向前推力，使飞行器变为动力三角翼飞行器；当飞行器需要降落时，控制计算机开启四轴飞行模式，后方向的后支架还原到水平位置，开启发动机，在操纵杆上控制飞行器垂直降落。本发明能利用多旋翼飞行器能垂直起降的特点，使多旋翼飞行器与三角翼飞行器组合，让三角翼飞行器能够垂直起降，同时能让飞行器进行飞行模式转换。 | ||||||
| 4 | 高安全性的飞行器 | CN200580051008.X | 2005-07-07 | CN101223079A | 2008-07-16 | A·卡布阿尼 |
| 飞行器(10)包括设置有推进装置和方向控制安定面的细长框架结构(26)。框架结构联接到气腔(16)，该气腔适于填充比空气轻的气体并包括两个连接成V形外形的管状分支(12、14)，且在两管状分支之间延伸有空气动力学升力表面(22、24)。 | ||||||
| 5 | JPS498993A - | JP5134772 | 1972-05-24 | JPS498993A | 1974-01-26 | |
| 6 | Aircraft | JP2005239228 | 2005-08-19 | JP2009012487A | 2009-01-22 | WATANABE TAKAMOTO |
| PROBLEM TO BE SOLVED: To provide an aircraft capable of easily changing a payload box according to purpose of use. SOLUTION: In this aircraft, the payload box 400 mounted with various equipment including a camera, is installed in an aircraft body 100 on which a kite wing 300 and a propeller 500 are installed. The aircraft is characterized in that an installation hole section open toward an installation portion of the other is arranged in any one of the payload box 400 or the aircraft body 100, and the other is provided with a slide section 420 that can be slid and inserted into the installation hole section. COPYRIGHT: (C)2009,JPO&INPIT | ||||||
| 7 | Aircraft | JP2005239227 | 2005-08-19 | JP2009012486A | 2009-01-22 | WATANABE TAKAMOTO |
| PROBLEM TO BE SOLVED: To provide an aircraft carriable in a small space, and having high performance. SOLUTION: This aircraft is formed by rotatably pivoting a propeller 500 by installing a kite wing 300 on an aircraft body 100 via struts 210 and 220. The aircraft is characterized in that a propeller guard part 120 is arranged in the aircraft body 100 for guarding the outer periphery of the propeller 500, and the struts 210 and 220 are fixably arranged in the propeller guard part 120. COPYRIGHT: (C)2009,JPO&INPIT | ||||||
| 8 | HIGH-SECURITY AIRCRAFT | EP05769453.1 | 2005-07-07 | EP1899220A1 | 2008-03-19 | CAPUANI, Alfredo |
| The aircraft (10) comprises an elongated framework (26) provided with propelling means and direction-control planes. The framework is coupled to a pneumatic chamber (16) suited to be filled with lighter-than-air gas and comprising two tubular branches (12, 14) joined to form a V-shaped profile, with an aerodinamic-lift surface (22, 24) extending therebetween. | ||||||
| 9 | AIRBORNE ENHANCEMENT DEVICE | EP04776551.6 | 2004-06-09 | EP1638841A2 | 2006-03-29 | Rebelle, Monique |
| An airborne enhancement device with harness (14), collar (24), and wing (18) coupled to the collar.The wing being adjustably deployable and stowed in a pack (34). | ||||||
| 10 | Ultraleicht-Fluggerät mit der Möglichkeit der Fortbewegung in der Luft sowie auf der Strasse | EP03028070.5 | 2003-12-09 | EP1541465B1 | 2007-07-18 | Hegger, Christof |
| 11 | TOWING WINCH APPARATUS FOR PARAGLIDERS AND HANG-GLIDERS | EP04803021.7 | 2004-12-16 | EP1706317A1 | 2006-10-04 | TVINGSHOLM, John |
| A towing winch apparatus for paragliders and hang-gliders (4,6) is provided which comprises a line (3) and a towing winch mechanism (5) adapted to apply tension to said line (3) during towing, where one end (15) of the line (3) is releaseably attached to the ground (16) during towing and the towing winch mechanism (5) is attached to the paraglider or hang-glider (4,6). In this way a towing winch apparatus is provided which is useable by a pilot (1) of a paraglider or hang-glider (4,6) without needing a helper on the ground (16). In addition, after the tow process, the pilot (1) of a paraglider or hang-glider (4,6) doesn't need to go back to the ground (16) in order to collect the towing winch mechanism (5). | ||||||
| 12 | HIGH-SECURITY AIRCRAFT | EP05769453.1 | 2005-07-07 | EP1899220B1 | 2011-04-13 | CAPUANI, Alfredo |
| The aircraft (10) comprises an elongated framework (26) provided with propelling means and direction-control planes. The framework is coupled to a pneumatic chamber (16) suited to be filled with lighter-than-air gas and comprising two tubular branches (12, 14) joined to form a V-shaped profile, with an aerodinamic-lift surface (22, 24) extending therebetween. | ||||||
| 13 | Ultraleicht-Fluggerät mit der Möglichkeit der Fortbewegung in der Luft sowie auf der Strasse | EP03028070.5 | 2003-12-09 | EP1541465A1 | 2005-06-15 | Hegger, Christof |
Gegenstand der Erfindung ist ein Ultraleicht- Fluggerät, das eine Zulassung als Ultraleicht-Fluggerät, sowie eine Straßenzulassung erhält. Beide Zulassungen erfüllen die üblichen nationalen Bestimmungen des Landes, in dem das Ultraleicht-Fluggerät zugelassen wird. Erfindungsgemäß wird eine Ultraleicht-Fluggerät Gondel vorgestellt, die aus einen Rahmen (11), der einen Motor (12) mit einem Getriebe umschließt, vier Rädern und einer Sitzbank für zwei Personen besteht. |
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| 14 | Low speed, high performance hang glider | US13986285 | 2013-04-19 | US20130299627A1 | 2013-11-14 | Richard Boone |
| Sail deflection, from large resultant moments, creates excess aerodynamic twist and limits hang glider performance. Incorporating a rear spar and sail attachment system, as a design feature, allows control and definition of this critical performance component. Hang gliders with this design feature will produce more total lift which in turn will produce lower stall speeds and less drag. | ||||||
| 15 | Hang glider electric propulsion system and method | US13010275 | 2011-01-20 | US08561936B2 | 2013-10-22 | Francois Matte |
| The system includes a keel fitting that can be rigidly attached directly to the keel of the hang glider. It also includes two elongated frame members symmetrically mounted on opposite sides of the keel fitting. At least one electrical motor is mounted on each frame member and there are at least two propellers, each in driving engagement with a corresponding one of the electrical motors. The system further includes an electrical power unit mounted on the back of the pilot. The electrical power unit includes at least one battery and a pilot-actuated control circuit to vary the electrical power supplied to the electrical motors. The system gives the pilot the capability of taking off from a flat terrain. Once airborne, the system is not operated and the hang glider can then be used as an unpowered one. | ||||||
| 16 | Safety flier—a parachute-glider air-vehicle with vertical take-off and landing capability | US12655546 | 2010-01-04 | US08408488B2 | 2013-04-02 | Glenn Leaver |
| One embodiment of a Vertical Take-off and Landing (VToL) air-vehicle (FIG. 1.) having a horizontal rotor, a. providing lift and propulsion, and communicating at or near its centre to structural elements, or fuselage, b. Upon or within the fuselage structure is attached a platform, to which a payload, or occupant or pilot, d. is secured in such a manner as to permit a movement, or range-of-motion, of the payload, as a means of weight-shifting, or mass-balancing, of the vehicle for stability and control in flight. At least two planar elements, or descent-vanes, c.i & c.ii are connected to a structural element of the fuselage at a location which provides vertical and horizontal separation between the rotor and the descent-vanes, thus creating a tandem, biplane arrangement of two aerodynamically active elements which are aerodynamically balanced to provide stability and controllability in hovering flight, in forward flight, and in un-powered gliding and vertical descents. Other embodiments are described and shown. | ||||||
| 17 | HUMAN-POWERED, BIRD-LIKE WINGS FLYING DEVICE | US12947060 | 2010-11-16 | US20110114784A1 | 2011-05-19 | Viatcheslav Abramian |
| The human-powered, bird-like flying device of the present invention has wings which may rotate around the keel and legs that let the pilot control rotation of the wings, which is to make the wings flap. The present invention develops one of the more efficient methods of ascending, which is to increase the angle of attack by moving the control bar forward while shifting the pilot's weight to efficiently strike onto the legs that make the wings flap downward. The present invention is secure and stable in the air, particularly while ascending and descending. This is done by selecting the proper shape and sail area of the wings and by proper attachment of the arm, legs and the hang loop, which hold the pilot's body. | ||||||
| 18 | High-Security Aircraft | US11922506 | 2005-07-07 | US20090108126A1 | 2009-04-30 | Alfredo Capuani |
| The aircraft (10) comprises an elongated framework (26) provided with propelling means and direction-control planes. The framework is coupled to a pneumatic chamber (16) suited to be filled with lighter-than-air gas and comprising two tubular branches (12, 14) joined to form a V-shaped profile, with an aerodinamic-lift surface (22, 24) extending therebetween. | ||||||
| 19 | Airborne enhancement device | US10865553 | 2004-06-09 | US07051973B2 | 2006-05-30 | Monique Rebelle |
| An airborne enhancement device comprises a harness adapted to secure to a body of a user. A collar is coupled to the harness. A wing is coupled to the collar by at least one structural member. The wing is adjustably deployable. The wing is configured to adjust between an extended position and a folded position. A pack is coupled to the collar and is configured to store the wing in the folded position. | ||||||
| 20 | Hang glider wheel apparatus | US11139898 | 2005-05-27 | US20060038089A1 | 2006-02-23 | Brad Kushner |
| A hub includes an inner surface that defines a noncircular, and preferably airfoil-shaped, aperture. The aperture is sufficiently sized and shaped for the inner surface to circumscribe a member having a noncircular cross section for retaining the hub to the member. A wheel is rotatable around the periphery of the hub. The hub thus functions as an adapter to enable a wheel to rotate about the noncircular member. | ||||||
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