| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | Foldable aircraft | US29121810 | 2000-04-13 | USD444512S1 | 2001-07-03 | Carlos T. Miralles; Bart D. Hibbs |
| 162 | Variable body helicopter with tandem lifting rotors | US217128 | 1998-12-21 | US6164590A | 2000-12-26 | Tom Kusic |
| A variable bodied helicopter is disclosed. The helicopter is of a type that has tandem lifting rotors (1, 2) with a body consisting of a front section (3) and a rear section (4). The rear section of the body is narrower than the front section of the body, thereby allowing the rear section to travel into the front section. Channelled railings (5, 6) attached to the front section of the body firmly hold the rear section through railings (7, 8) attached to the rear section. These railings guide the movement of the rear section relative to the front section. A shaft consisting of two sections (9, 10) is used to synchronize the tandem arranged rotors. The narrower section (9) of the shaft slides into the wider section (10) of the shaft when the rear section of the body moves into the front section of the body. Bearings (11, 12, 13) support the synchronizing shaft. One bearing (13) is firmly fixed to the front section (3) of the body while another bearing (12) is attached to the rear section (4) but is linked to the front section thus causing it to move against the rear section when the rear section moves relative to the front section. Another bearing (11) positioned on the rear section (4) is linked by a telescopic connection (14) to the front section of the body so that it is placed at the optimum position on the rear section as the body expands from a compressed state. | ||||||
| 163 | Releasable coupling for a helicopter tail rotor power transmission line | US124188 | 1998-07-28 | US6050521A | 2000-04-18 | Roberto Regonini |
| A releasable coupling for a power transmission line to a tail rotor of a foldable-tail-section helicopter, the coupling having a first and a second coupling assembly fitted respectively to the body and the tail of the helicopter, and which cooperate with each other when the tail is in the work position; the two coupling assemblies having respective transmission members in turn having respective radial toothings cooperating telescopically with each other, and respective conical male and female lead-in members which are brought into contact with each other prior to the respective toothings to guide connection of the transmission members; at least one of the transmission members being supported orientably. | ||||||
| 164 | Airplane efficiency, safety and utilization | US725217 | 1991-06-26 | US5201478A | 1993-04-13 | Don H. Wooley |
| This invention involves a simple but radical approach to airplane design. Many advantages and benefits result therefrom including improved flight efficiency, better handling and control response, less tail area required, increased safety, increased utility of airplanes, and reduced ground handling and hangar facility requirements. A solution is provided for the inherent problems of combining the utility of a surface conveyance with the freedom and swiftness of flight. | ||||||
| 165 | Aircraft | US696165 | 1985-01-29 | US4706907A | 1987-11-17 | Eduard Kopylov |
| An aircraft has a geometrically transformable pilot compartment, and further parts including a fuselage boom, wings and tail, wherein at least one of these parts are movable between an unfolded position in which it is ready for flying and a folded position in which it is accommodated in the pilot compartment. | ||||||
| 166 | Vertical takeoff and landing aircraft | US799510 | 1977-05-23 | US4085911A | 1978-04-25 | Richard J. Nahodyl |
| A vertical takeoff and landing aircraft having a tail assembly supporting structure which is pivotally connected to the fuselage, and having a shrouded fan driven by an engine submerged in the fuselage, the shrouded fan being connected to and rotatable with the tail supporting structure so as to direct the slipstream of the shrouded fan over the tail assembly at all times. | ||||||
| 167 | Knockdown airplane-fuselage and process therefor | US22731418 | 1918-04-08 | US1354677A | 1920-10-05 | MIX MELVILLE W |
| 168 | MULTIKOPTER MIT MULTIFUNKTIONALEN AUSLEGERN MIT ZUMINDEST EINEM ANTRIEB | EP15726514.1 | 2015-04-28 | EP3140191B1 | 2018-06-13 | HOFSTÄTTER, Lukas |
| 169 | SELF-CONTAINED AERIAL CARGO VEHICLE | EP17203694.9 | 2017-11-27 | EP3330176A1 | 2018-06-06 | NEWMAN, Daniel I. |
An aerial vehicle includes one or more rotors and a cargo container. The one or more rotors are configured to propel the aerial vehicle. The cargo container defines a cargo volume and is configured to travel with the aerial vehicle during propulsion by the one or more rotors. The cargo container is further configured to contain, at least, the one or more rotors, when the aerial vehicle is not configured for moving cargo.
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| 170 | FULLY-PROTECTED UNMANNED AERIAL VEHICLE | EP15875205.5 | 2015-12-29 | EP3241758A1 | 2017-11-08 | ZHANG, Tong; WANG, Mengqiu; WANG, Zhaozhe; ZHANG, Xuyang; ZHANG, Guanqun; GONG, Shuang; ZHANG, Yalin; WANG, Jinglong; LIU, Lixin |
A fully-protected unmanned aerial vehicle comprises an unmanned aerial vehicle body (1) and a rotor (2) connected to the unmanned aerial vehicle body (1), and further comprises a protection housing (3) connected to the unmanned aerial vehicle body (1). The protection housing (3) is a hollowed-out closed housing and has a hollow cavity (31), and the rotor (2) is installed in the hollow cavity (31). Because the rotor is installed in the hollow cavity of the protection housing, the rotor cannot make contact with a human body, so that the unmanned aerial vehicle can be released or reclaimed by an operator with the hand, and the operation portability and safety of the rotor are improved. The hollowed-out structure provides a forming space of lift for the rotor and normal flight of the unmanned aerial vehicle is ensured. The rotor is installed in the protection housing that is connected to the unmanned aerial vehicle body, so that the overall height of the unmanned aerial vehicle is reduced, and the portability of the unmanned aerial vehicle is further improved. |
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| 171 | FOLDABLE UNMANNED AERIAL VEHICLE | EP15875204.8 | 2015-12-29 | EP3241741A1 | 2017-11-08 | ZHANG, Tong; WANG, Mengqiu; WANG, Zhaozhe; ZHANG, Xuyang; ZHANG, Guanqun; GONG, Shuang; ZHANG, Yalin; WANG, Jinglong; LIU, Lixin |
A foldable unmanned aerial vehicle for improving the portability of unmanned aerial vehicles comprises an unmanned aerial vehicle body (1) and a rotor portion connected to the unmanned aerial vehicle body (1). The rotor portion comprises a first rotor module (2) and a second rotor module (3) each having at least one rotor. The first rotor module and the second rotor module can be folded or unfolded by rotation around their own hinge shafts (4). According to the unmanned aerial vehicle, the rotor is designed in a modular manner: first, two rotor modules that can be folded or unfolded relatively are formed, and the folding and unfolding are implemented by the rotation of the rotor modules, so that the state of the unmanned aerial vehicle is changed, the folding and flying demands for the unmanned aerial vehicle are satisfied, and the portability of the unmanned aerial vehicle is improved; a flight path and a control module that the unmanned aerial vehicle needs can be arranged in the unmanned aerial vehicle body and do not need to be separately arranged in the rotor modules, so that the control reliability is improved. |
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| 172 | SYSTEMS AND METHODS FOR FOLDABLE ARMS | EP15874388 | 2015-06-01 | EP3206947A4 | 2017-11-01 | WU XUMIN; WU XIAOLONG; LEE SUNGKI; AO JIYUAN; FENG ZHUANG |
| An unmanned aerial vehicle (UAV) includes a central body, a plurality of arms extending out from the central body and in fluid communication with the central body, and a plurality of propulsion units. The plurality of arms are configured to route fluid away from the central body of the UAV. Each propulsion unit attached to a corresponding arm of the plurality of arms. | ||||||
| 173 | A MULTI-ROTOR UNMANNED AERIAL VEHICLE | EP13795150.5 | 2013-11-13 | EP2763896B1 | 2017-09-20 | WANG, Tao; ZHAO, Tao; CHEN, Shaojie; OU, Zhigang |
| 174 | Verriegelungssystem | EP10157279.0 | 2010-03-23 | EP2233393B1 | 2016-01-06 | Schnoell, Gregor |
| 175 | A MULTI-ROTOR UNMANNED AERIAL VEHICLE | EP13795150 | 2013-11-13 | EP2763896A4 | 2015-03-11 | WANG TAO; ZHAO TAO; CHEN SHAOJIE; OU ZHIGANG |
| 176 | VEHICLE | EP12794527.7 | 2012-11-09 | EP2776259A1 | 2014-09-17 | STEKELENBURG, Michael Alwin William; KLOK, Christiaan Cornelis; VAN RIJN, Louis Petrus Valentijn Marie; SOETHOUDT, Wouter Adriaan; WEGERIF, Robert Christiaan |
| The present invention discloses a vehicle (1) capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail (10) comprising a first tubular tail segment (11) and a second tail segment (12) disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members (21, 35; 31, 36) located at an axial distance (LI) from each other for providing a force-transferring coupling between the second tail segment (12) and the first tubular tail segment (11) in the extended state of the second tail segment (12), each of said form-closing coupling members (21, 35; 31, 36) capable of transferring torque and transverse forces, and each of said form-closing coupling members (21, 35; 31, 36) coming into engagement by axial displacement of the second tail segment (12) in the outward direction. | ||||||
| 177 | A MULTI-ROTOR UNMANNED AERIAL VEHICLE | EP13795150.5 | 2013-11-13 | EP2763896A1 | 2014-08-13 | WANG, Tao; ZHAO, Tao; CHEN, Shaojie; OU, Zhigang |
| Methods and apparatus for unmanned aerial vehicle (UAV) with improved reliability are provided, wherein onboard sensors are located on said UAV at a position separated from onboard electrical components. Therefore, interference experienced by onboard sensors from onboard electrical components is reduced. In addition, user-configuration or assembly of electrical components is minimized to reduce user's errors. | ||||||
| 178 | DISMOUNTABLE HELICOPTER | EP09851908 | 2009-12-02 | EP2507129A4 | 2013-11-13 | CARDELL PER-ERIK; STENBOM KJELL; LIDSTROEM ROBERT |
| 179 | Pivotable aircraft nose portion | EP03075275.2 | 2003-01-28 | EP1334905B1 | 2006-06-21 | Salmon, James J. |
| 180 | AIRCRAFT SUPPORT LEG, AIRCRAFT AND CONTROL METHOD | US16090030 | 2016-08-02 | US20190193844A1 | 2019-06-27 | WEIFENG ZHENG; CHUNHONG JIA; YI ZHENG; BUWEI WEI; GUOZHI ZENG |
| An aircraft support leg (2), the support leg (2) being movably connected to a main body of an aircraft. The support leg (2) can rotate to at least a first position and a second position. At the first position, an angle is provided between the support leg and the main body of the aircraft, and at the second position, the support leg (2) substantially abuts against the main body of the aircraft or is at least partly arranged in the main body of the aircraft. Such a support leg is convenient for the storage of the aircraft. Also disclosed are a control method for said support leg and an aircraft having said support leg and a control method for the aircraft. | ||||||
