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1. 发明授权

EP3880555B1 DOUBLE WING AIRCRAFT 有权
公开(公告)号：EP3880555B1
公开(公告)日：2024-08-28
申请号：EP19884368.2
申请日：2019-10-28
IPC分类号： B64C3/32 , B64C3/10 , B64C39/10 , B64C39/08
CPC分类号： B64C3/10 , B64C3/32 , B64C39/08 , B64C39/10 , B64C2039/10520130101 , Y02T50/10

2. 发明公开

EP3260370A1 DRONE COMPORTANT DES AILES PORTANTES 审中-公开
标题翻译：无声包括便携式的翅膀
公开(公告)号：EP3260370A1
公开(公告)日：2017-12-27
申请号：EP17176471.5
申请日：2017-06-16
申请人： Parrot Drones
发明人： LAVAGEN, Gauthier , MARI-MARI, Marc , BENATAR, Yoni , BARSE, Thomas
IPC分类号： B64C29/00 , A63H27/00
CPC分类号： B64C27/26 , A63H27/12 , B64C3/32 , B64C11/46 , B64C29/0025 , B64C29/02 , B64C39/024 , B64C39/08 , B64C2201/02 , B64C2201/042 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/146 , B64C2201/165 , B64C2201/187
摘要： L'invention concerne un drone à voilure tournante (10) comprenant un corps de drone (12) comprenant une carte électronique contrôlant le pilotage du drone, quatre bras de liaison (16) comprenant fixé solidairement un bloc propulseur (14). Les bras de liaison (16) forment des ailes portantes.
摘要翻译：本发明涉及一种包括无人驾驶飞机主体（12）的旋翼无人机（10），所述无人驾驶飞机主体包括控制无人驾驶飞机驾驶的电子卡，包括固体固定式推进剂单元（14）的四个连杆臂（16）。连接臂（16）形成承重翼。

3. 发明公开

EP3090945A1 A FLYING APPARATUS 有权
标题翻译： FLIEGENDE VORRICHTUNG
公开(公告)号：EP3090945A1
公开(公告)日：2016-11-09
申请号：EP15166221.0
申请日：2015-05-04
申请人： Shchukin, Anton Alexandrovich
发明人： Shchukin, Anton Alexandrovich
IPC分类号： B64C29/00 , B64C39/08 , B64C3/38
CPC分类号： B64C29/0033 , B64C3/385 , B64C39/08
摘要： The invention relate to aircraft and used for civilian purposes, the delivery of people and freights, also for agricultural and fire-fighting purposes, for military tasks, reconnaissance tasks, for the tasks of air defense and air superiority.
Summary of the invention consists in equipping the aircraft carriers of the aerodynamic surfaces each of which can be independently rotated around the axis of the attachment to the fuselage and each of which has assigned to it the device that creates cravings in plane of the aerodynamic surfaces to achieve high maneuverability and flight ability in any direction at any position of the fuselage.
The proposed aircraft uses innovative aerodynamic scheme and contains four or more independently rotatable around the axis of the attachment to the fuselage aerodynamic surfaces installed on each device, each of which creates cravings in the plane of the aerodynamic surfaces.
In horizontal flight, aerodynamic surfaces create lift aimed vertically, and a traction device creates a force that is aimed horizontally in the direction of flight. This configuration is designed for maximum range as minimum fuel consumption. Aircraft can gain altitude when changing the angle of the front or rear pairs of aerodynamic surfaces, that will make the fuselage, also change the angle of attack. When the front and rear surfaces at the same time is reached maneuverability. If necessary, increase altitude without changing the angle of attack of the fuselage or change by a specified amount can be achieved by changing the angle of attack of both pairs of surfaces - (for example, under special conditions of transportation of cargo or passengers or challenges accompany ground or air targets). Similarly, can implement the vertical climb with horizontally locate the fuselage, as well as horizontal flight with vertically located the fuselage or even flying aft forward. Can ensure the aircraft hangs with arbitrary pitch angle. Can ensure the aircraft hangs with arbitrary pitch angle. The increase in the number of aerodynamic surfaces adds new features: add horizontal surfaces can provide aircraft combined flight mode. Using the power control devices creating reactive thrust could provide rotating in place when moving the fuselage in the horizontal plane and vertical plane.
摘要翻译：本发明涉及飞机，用于民用，交运和货物，也用于农业和消防目的，用于军事任务，侦察任务，防空和空中优势任务。本发明的总结在于装备航空母舰的空气动力学表面，每个空气动力学表面可以独立地围绕附件的轴线旋转到机身，并且其中的每一个已经分配给在空气动力学表面的平面中产生渴望的装置在机身的任何位置都能够在任何方向上实现高机动性和飞行能力。所提出的飞行器使用创新的空气动力学方案，并且包含四个或更多个独立地可旋转的轴线，附接到安装在每个装置上的机身空气动力学表面上，每个装置在空气动力学表面的平面中产生渴望。在水平飞行中，空气动力学表面产生垂直方向的牵引力，并且牵引装置产生沿着飞行方向水平瞄准的力。该配置设计用于最大范围作为最小燃料消耗。飞机在改变前后两对空气动力学表面的角度时可以获得高度，这将使机身也改变攻角。当前后表面同时达到机动性。如有需要，可以通过改变两对表面的攻角（例如在特殊的货物或乘客运输条件或挑战条件下）来改变机身的角度或改变一定数量的高度，伴随地面或空中目标）。同样，可以实现垂直爬升，水平定位机身，以及垂直位置的机身或甚至向前飞行的水平飞行。可以确保飞机以任意的俯仰角挂起。可以确保飞机以任意的俯仰角挂起。空气动力表面数量的增加增加了新的特点：添加水平面可以提供飞机组合飞行模式。在水平面和垂直平面上移动机身时，使用产生反作用力的动力控制装置可以提供旋转就位。

4. 发明公开

EP2625094A1 THREE WING, SIX TILT-PROPULSION UNIT, VTOL AIRCRAFT 审中-公开
标题翻译：与6个专门可倾斜驱动单元三翅垂直平面STARTER
公开(公告)号：EP2625094A1
公开(公告)日：2013-08-14
申请号：EP11831080.4
申请日：2011-06-27
申请人： Oliver Vtol LLC
发明人： OLIVER, Richard, David
IPC分类号： B63H3/00
CPC分类号： B64C29/0033 , B64C29/0075 , B64C39/08 , B64D27/06 , B64D27/12 , Y02T50/44
摘要： A vertical takeoff and landing aircraft having a fuselage with, preferably, three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are oriented vertically for vertical flight and horizontally for forward flight. Each propulsion unit comprises a propeller having a plurality of blades, where the pitch angle associated with the distal end of each blade and the proximal end of each blade are independently adjustable. As such, each of the propellers can be adjusted to exhibit a first blade pitch angle distribution optimized for vertical flight and a second blade pitch angle distribution optimized for forward flight.

5. 发明公开

EP2619090A1 AIRPLANE WING 审中-公开
标题翻译：飞机机翼
公开(公告)号：EP2619090A1
公开(公告)日：2013-07-31
申请号：EP11827524.7
申请日：2011-09-22
申请人： Heaton, Clifford D.
发明人： Heaton, Clifford D.
IPC分类号： B64C39/00
CPC分类号： B64C39/068 , B64C3/385 , B64C9/12 , B64C39/04 , B64C39/08 , B64D27/06 , B64D27/18 , Y02T50/14 , Y02T50/32 , Y10T29/49826
摘要： An airplane wing configuration includes a first wing positioned above and forward of a second wing on an airplane fuselage. The first wing is operable to direct airflow over an upper surface of the second wing, whereby the first and second wings are capable of generating greater lift than a sum of their individual lifts. The first wing may include an adjustable wing flap that redirects airflow over the upper surface of the second wing, and the second wing may include a rotatable portion that pivots to vary the angle of attack of the second wing independent of the first wing.

6. 发明授权

EP3868660B1 VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT AND RELATED METHODS 有权
公开(公告)号：EP3868660B1
公开(公告)日：2024-10-02
申请号：EP21157781.2
申请日：2021-02-18
IPC分类号： B64C39/08 , B64C29/00 , B64C27/28 , B64C27/26
CPC分类号： B64C27/28 , B64C27/26 , B64C29/0033 , B64C29/0025 , Y02T50/50 , B64C39/08

7. 发明授权

EP3090945B1 A FLYING APPARATUS 有权
标题翻译：飞行装置
公开(公告)号：EP3090945B1
公开(公告)日：2018-04-18
申请号：EP15166221.0
申请日：2015-05-04
申请人： Shchukin, Anton Alexandrovich
发明人： Shchukin, Anton Alexandrovich
IPC分类号： B64C29/00 , B64C39/08 , B64C3/38
CPC分类号： B64C29/0033 , B64C3/385 , B64C39/08
摘要： The invention relate to aircraft and used for civilian purposes, the delivery of people and freights, also for agricultural and fire-fighting purposes, for military tasks, reconnaissance tasks, for the tasks of air defense and air superiority. Summary of the invention consists in equipping the aircraft carriers of the aerodynamic surfaces each of which can be independently rotated around the axis of the attachment to the fuselage and each of which has assigned to it the device that creates cravings in plane of the aerodynamic surfaces to achieve high maneuverability and flight ability in any direction at any position of the fuselage. The proposed aircraft uses innovative aerodynamic scheme and contains four or more independently rotatable around the axis of the attachment to the fuselage aerodynamic surfaces installed on each device, each of which creates cravings in the plane of the aerodynamic surfaces. In horizontal flight, aerodynamic surfaces create lift aimed vertically, and a traction device creates a force that is aimed horizontally in the direction of flight. This configuration is designed for maximum range as minimum fuel consumption. Aircraft can gain altitude when changing the angle of the front or rear pairs of aerodynamic surfaces, that will make the fuselage, also change the angle of attack. When the front and rear surfaces at the same time is reached maneuverability. If necessary, increase altitude without changing the angle of attack of the fuselage or change by a specified amount can be achieved by changing the angle of attack of both pairs of surfaces - (for example, under special conditions of transportation of cargo or passengers or challenges accompany ground or air targets). Similarly, can implement the vertical climb with horizontally locate the fuselage, as well as horizontal flight with vertically located the fuselage or even flying aft forward. Can ensure the aircraft hangs with arbitrary pitch angle. Can ensure the aircraft hangs with arbitrary pitch angle. The increase in the number of aerodynamic surfaces adds new features: add horizontal surfaces can provide aircraft combined flight mode. Using the power control devices creating reactive thrust could provide rotating in place when moving the fuselage in the horizontal plane and vertical plane.

8. 发明公开

EP3272648A2 SELF-MOVING APPARATUS AND COMPONENTS THEREOF 审中-公开
标题翻译：自走式装置及其部件
公开(公告)号：EP3272648A2
公开(公告)日：2018-01-24
申请号：EP16769146.8
申请日：2016-03-18
申请人： Sapargaliyev, Aldan Asanovich
发明人： Sapargaliyev, Aldan Asanovich
IPC分类号： B64C11/02 , B63H1/20 , B60F5/02 , B64C29/00
CPC分类号： B64C29/0033 , B64C3/56 , B64C11/28 , B64C39/08 , B64D27/24 , B64D29/02 , Y02T70/542
摘要： The present invention relates to SMAs (self-moving apparatuses) which use any type of propulsion means, including, without limitation, an FPGB (propeller-gear block) comprising an FP (propeller) and a drive for supplying power thereto. More particularly, the present invention describes: novel forms of energy-efficient (economical) FPGBs; and novel conceptual designs for SMAs, which make it possible to create economical SMAs with high specific power. The invention can be used for creating novel energy-efficient types of SMAs, and for the widespread (mass) use of compact and environmentally-friendly electric engines instead of environmentally detrimental and bulky internal combustion engines.
摘要翻译：本发明涉及使用任何类型的推进装置的SMA（自动移动装置），所述推进装置包括但不限于包括FP（螺旋桨）和用于向其供电的驱动器的FPGB（螺旋桨式传动机构）。更具体地说，本发明描述了：新型节能（经济）FPGB; 以及SMA的新颖概念设计，这使得可以创造具有高比功率的经济型SMA。本发明可以用于创造新的节能类型的SMA，以及用于广泛（大量）使用紧凑且环境友好的电动发动机，而不是环境有害和笨重的内燃机。

9. 发明公开

EP3261925A1 TILTROTOR WITH DOUBLE MOBILE WING 有权
标题翻译： TILTROTOR与双移动的翼
公开(公告)号：EP3261925A1
公开(公告)日：2018-01-03
申请号：EP16724108.2
申请日：2016-02-26
申请人： Skybox Engineering S.r.l.
发明人： FREDIANI, Aldo , CIPOLLA, Vittorio , OLIVIERO, Fabrizio , RIZZO, Emanuele , CAVALLARO, Rauno
IPC分类号： B64C39/08 , B64C39/00
CPC分类号： B64C39/08 , B64C39/005
摘要： A convertiplane structure (100), having a longitudinal axis x and a plane n orthogonal to it, comprises a main wing (120) arranged to rotate about at least one transversal rotation axis y, an auxiliary wing (130), which is located back with respect to main wing (120), and arranged to rotate about at least one transversal rotation axis y', at least two main propellers (220) located on the main wing (120), and at least two auxiliary propellers (230) located on the auxiliary wing (130). The auxiliary wing (130) is located at a vertical height higher than main wing (120). Two vertical wings (140) are also provided located in such a way that the projections on the plane n of the main wing (120), of the auxiliary wing (130) and of the vertical wings (140) shape a closed polygon, thus reducing the induced drag and increasing the overall aerodynamic efficiency.

10. 发明公开

EP2487371A4 WING STRUCTURE AND FAIRING DEVICE 失效转让
标题翻译：机翼结构和面板THEREFOR
公开(公告)号：EP2487371A4
公开(公告)日：2015-03-25
申请号：EP10822101
申请日：2010-10-07
申请人： TOYOTA MOTOR CO LTD
发明人： KIMURA YUKIHIDE , MORIMOTO TOMOAKI
IPC分类号： F15D1/10 , B64C23/00
CPC分类号： B64C39/08 , B62D35/00 , B64C23/00
摘要： The invention provides a wing structure 1 including: a main wing 2 that extends in a second direction intersecting a first direction as a fluid flow direction; and an auxiliary wing 3 that is disposed so as to be separated from the main wing 2 and faces the main wing 2 at the front part side of the main wing 2, wherein a wing chord length of the auxiliary wing 3 is shorter than a wing chord length of the main wing 2. According to the invention, a fluid contacts the auxiliary wing 3 which is formed at the front part side of the main wing 2, the fluid is guided between the auxiliary wing 3 and the main wing 2, and the fluid is compressed when passing between the auxiliary wing 3 and the main wing 2, thereby appropriately forming a fluid compression process region on the surface of the main wing 2 and increasing an acting force.

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