141. 垂直離着陸機

申请号: JP2015546507

申请日: 2013-11-22

公开（公告）号: JP2016501154A

公开（公告）日: 2016-01-18

发明人: ジェイ．デロリアン ポール

本開示は、一般的に、胴体および少なくとも1つの固定翼を備える垂直離着陸(VTOL)機に関する。航空機は、胴体の長手方向軸にほぼ沿って配置された少なくとも2つの駆動されるロータを備え得る。ロータユニットは、回転台座を介して胴体に結合されてもよく、これは、ロータが少なくとも1つの軸を中心としたロータユニットの動作により配向された推力を生成することを可能にする。ロータユニットを動かすことにより、航空機は、ホバーモードから移行モードにおよび次いで前進飛行モードに移行し、ならびに戻ることが可能である。

142. 垂直離着陸飛行機

申请号: JP2010047092

申请日: 2010-02-13

公开（公告）号: JP5728688B2

公开（公告）日: 2015-06-03

发明人: 松田 篤志; 大高 悦裕

143. VERTICAL TAKE-OFF AND LANDING AIRCRAFT

申请号: PCT/RO2016/050011

申请日: 2016-12-27

公开（公告）号: WO2018063019A1

公开（公告）日: 2018-04-05

发明人: GIURCA, Liviu Grigorian

The present invention relates to a vertical take-off and landing ("VTOL") aircraft and especially to this having hybrid or electric drive, used to transport people or goods from one point to the other without the necessity of airport runways. An aircraft (1), with vertical take-off and landing, comprises a fuselage (2) and some wings (3), extensible, located side by side from the fuselage (2). The fuselage (2) contains a cockpit (4) which has an aerodynamic shape and is extended with two members (5), distanced by an opening (6). The aircraft (1) uses a modular propulsion system (7) which contains two multiple propellers (8), rotatable mounted on the cockpit (4) in the front of the wings (3), side by side from the fuselage (2), and another multiple propeller (9) located in the opening (6) and which is rotatable mounted between the two members (5).

144. VERTICAL TAKE-OFF AND LANDING AIRCRAFT

申请号: PCT/IB2015/055376

申请日: 2015-07-16

公开（公告）号: WO2016009376A1

公开（公告）日: 2016-01-21

发明人: MIA, Mohamed, Reza

A vertical take-off and landing (VTOL) aircraft is provided comprising a fuselage (12) defining a forward end and an aft end, the fuselage accommodating at least one engine (56), a left wing (18) and a right wing (20) extending from either side of the fuselage, a lift fan drive system (22) accommodated within each wing, a forward thrust fan drive system (24) fitted proximate the aft end of the fuselage, and a stabiliser arrangement (26) proximate the forward thrust fan drive system. In an embodiment, each wing comprises a rotor housing portion (18.1, 20.1) extending away from the fuselage and a wing tip portion (18.2, 20.2) extending away from the rotor housing portion, the wing tip portion being angled towards the rear and side of the aircraft. In an embodiment, the rotor housing portion comprises two rotor housings, one forward of the aircraft's centre of gravity and one aft of the aircraft's centre of gravity.

145. Aérodyne à décollage et atterrissage verticaux

申请号: EP97400469.9

申请日: 1997-02-28

公开（公告）号: EP0808768B1

公开（公告）日: 2003-11-12

发明人: Soulez-Lariviere, Jean

146. 垂直離着陸飛行体

申请号: JP2015511830

申请日: 2014-10-29

公开（公告）号: JP5943289B2

公开（公告）日: 2016-07-05

发明人: 荒井 優章

147. 垂直離着陸飛行体

申请号: JP2012192458

申请日: 2012-08-16

公开（公告）号: JP5791033B2

公开（公告）日: 2015-10-07

发明人: 荒井 優章

148. VERTICAL TAKE-OFF AND LANDING AIRCRAFT

申请号: PCT/GB2017/053247

申请日: 2017-10-27

公开（公告）号: WO2018078386A1

公开（公告）日: 2018-05-03

发明人: MORGAN, Brian

A lift rotor or 'thrust' system or assembly for a VTOL aircraft, comprising first and second lifting thrusters or rotors contained within a housing, the housing containing a leading edge, a trailing edge, a upper surface and a lower surface; wherein the housing includes one or more airflow manipulation devices provided on or associated with the housing configured to manage the airflow into or through at least one of the first and second rotors. In other aspects, the invention embraces an aircraft wing including a lift thruster system as defined above, and also an aircraft comprising such a lift thruster system.

149. VERTICAL TAKE-OFF AND LANDING AIRCRAFT

申请号: PCT/US2004/003891

申请日: 2004-02-10

公开（公告）号: WO2005023644A2

公开（公告）日: 2005-03-17

发明人: BILLIU, Charles, R.

An impeller (16) driven ring wing (12) aircraft (10) whose lifting forces are augmented by the release of jets of air (113) from Coanda slots (42) disposed around the exterior edge (32) of t-he ring wing (12). These jets of air (113) entrain the air passing by the ring wing (12) downwardly to act as thrust to lift the aircraft (10).

150. VERTICAL TAKE-OFF AND LANDING AIRCRAFT

申请号: EP15771708.3

申请日: 2015-07-16

公开（公告）号: EP3169586A1

公开（公告）日: 2017-05-24

发明人: MIA, Mohamed Reza

A vertical take-off and landing (VTOL) aircraft is provided comprising a fuselage (12) defining a forward end and an aft end, the fuselage accommodating at least one engine (56), a left wing (18) and a right wing (20) extending from either side of the fuselage, a lift fan drive system (22) accommodated within each wing, a forward thrust fan drive system (24) fitted proximate the aft end of the fuselage, and a stabiliser arrangement (26) proximate the forward thrust fan drive system. In an embodiment, each wing comprises a rotor housing portion (18.1, 20.1) extending away from the fuselage and a wing tip portion (18.2, 20.2) extending away from the rotor housing portion, the wing tip portion being angled towards the rear and side of the aircraft. In an embodiment, the rotor housing portion comprises two rotor housings, one forward of the aircraft's centre of gravity and one aft of the aircraft's centre of gravity.

151. VERTICAL TAKEOFF AND LANDING AIRCRAFT

申请号: EP13873269.8

申请日: 2013-12-17

公开（公告）号: EP2899122A1

公开（公告）日: 2015-07-29

发明人: TSUNEKAWA, Masayoshi; TAMURA, Tetsuya

A vertical take-off and landing aircraft including a propulsion mechanism 2 that generates lift and thrust, a main frame 4 that supports seating 41 and a landing undercarriage 42, a subframe 5 which supports the propulsion mechanism 2 and which is arranged so as to be swingable back and forth relative to the main frame 4, motive power supply means 3 supported by the main frame 4 and supplying motive power to the propulsion mechanism 2, and a control stick 6 connected to the subframe 5, in which the propulsion mechanism 2 includes a pair of ducted fans 21L, 21R arranged on a left side and a right side, respectively, of the main frame 4, swing shafts 22 arranged in the ducted fans 21L, 21R and extending in a horizontal direction, and control vanes 23 connected to the swing shafts 22, and swinging the control vane 23 enables the subframe 5 to move relative to the main frame 4. Maneuverability can be improved with addition of control mechanisms restrained.

152. Aérodyne à décollage et atterrissage verticaux

申请号: EP03000470.9

申请日: 1997-02-28

公开（公告）号: EP1300336A3

公开（公告）日: 2004-05-06

发明人: Soulez-Lariviere, Jean

L'aérodyne à décollage et atterrissage verticaux selon l'invention comprend deux hélices droite et gauche (37) portées chacune par une nacelle (33, 35), et un moyen de commande de roulis à la disposition du pilote. Les nacelles sont montées de façon pivotante pour s'incliner entre des orientations verticale et horizontale, chaque hélice incluant des moyens pour faire varier son pas de façon cyclique suivant l'azimut latéral.

Cet aérodyne est caractérisé en ce que le moyen de commande de roulis constitue l'unique gouverne de roulis et est relié de façon antisymétrique aux moyens de variation cyclique latérale du pas des pales, quelle que soit l'inclinaison des nacelles (33,35), et en ce que le sens de rotation des hélices est le sens supradivergent dans lequel l'hélice droite tourne dans le sens horaire tandis que l'hélice gauche tourne dans le sens antihoraire, l'action en roulis des composantes radiales cycliques des forces aérodynamiques sur les pales étant ainsi dans le même sens que celle des composantes axiales et s'y ajoutant puis s'y substituant à mesure que l'inclinaison des nacelles passe de la verticale à l'horizontale.

153. Vertical take-off/landing aircraft

申请号: JP2004239645

申请日: 2004-08-19

公开（公告）号: JP2006056364A

公开（公告）日: 2006-03-02

发明人: ISHIBA MASAJI

PROBLEM TO BE SOLVED: To suppress the generation of temperature distribution of a tip turbine fan in a vertical take-off/landing aircraft utilizing the tip turbine fan as a propulsion force source. SOLUTION: In the vertical take-off/landing aircraft provided with the tip turbine fan 2 and performing vertical take-off/landing, the fan is rotated by blowing compression gas to the tip turbine mounted to the fan 10 in an annular turbine chamber 15 provided making a rotation shaft 17 of the fan 10 as a center. Three or more compression gas inlets 14 for feeding the compression gas to a turbine chamber 15 are arranged on a circumference of the turbine chamber 15 at equal intervals. COPYRIGHT: (C)2006,JPO&NCIPI

154. 垂直離着陸（ＶＴＯＬ）航空機

申请号: JP2016512112

申请日: 2014-05-05

公开（公告）号: JP2016517821A

公开（公告）日: 2016-06-20

发明人: ジェイ． テイラー，ダナ; ティー． トクマル，フィリップ; ディーン ヒッブス，バート; マーティン パークス，ウィリアム; ウェイン ガンザー，デイヴィッド; ユージン フィッシャー，クリストファー; シッダールタデヴ ムーカジ，ジェイソン; フレデリック キング，ジョセフ

固定翼機の飛行制御装置が、第1の左翼(115)および第1の右翼(120)と、第1の左ロータ(155)と第1の左翼(115)に連結された第1の左電気モータ(135)との間に連結された第1の左スワッシュプレート(145)と、第1の右ロータ(130)と第1の右翼(120)に連結された第1の右電気モータ(140)との間に連結された第1の右スワッシュプレート(150)と、を有する。【選択図】図3A

155. VERTICAL TAKE-OFF AND LANDING AIRCRAFT

申请号: PCT/US2014/060166

申请日: 2014-10-10

公开（公告）号: WO2015108578A2

公开（公告）日: 2015-07-23

发明人: GODLASKY, Robert; OGAWA, Nate; STREETT, Andrew

A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

156. VERTICAL TAKEOFF AND LANDING AIRCRAFT

申请号: PCT/US2013/071531

申请日: 2013-11-22

公开（公告）号: WO2014120331A2

公开（公告）日: 2014-08-07

发明人: DELOREAN, Paul, J.

The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. By moving the rotor units, the aircraft can transition from a hover mode to a transition mode and then to a forward flight mode and back.

157. Vertical take-off/landing of aircraft

申请号: EP93305707.7

申请日: 1993-07-20

公开（公告）号: EP0581513B1

公开（公告）日: 1997-05-21

发明人: Milner, Paul

158. VERTICAL TAKE-OFF AND LANDING AIRCRAFT

申请号: EP14798021.3

申请日: 2014-05-15

公开（公告）号: EP2998221A1

公开（公告）日: 2016-03-23

发明人: TSUNEKAWA, Masayoshi; TAMURA, Tetsuya

A vertical take-off and landing aircraft includes a propulsion mechanism 2 that generates lift and thrust, a main frame 4 that supports seating 41 and a landing undercarriage 42, a sub-frame 5 which supports the propulsion mechanism 2 and is arranged so as to be swingable back and forth relative to the main frame 4, a motive power supply unit 3 supported by the main frame 4 and supplying motive power to the propulsion mechanism 2, a control stick 6 connected to the sub-frame 5, and a main wing 7 arranged on the propulsion mechanism 2, wherein the main wing 7 is formed to be retracted to a position not interfering with an air flow of the propulsion mechanism 2 in a normal time and to be movable to a position where lift is generated when thrust is lost. Gliding is made possible even if thrust is lost while increasing in size of a fuselage is avoided.