-
公开(公告)号：EP4382414A1
公开(公告)日：2024-06-12
申请号：EP22315306.5
申请日：2022-12-06
发明人： Fink, Axel , Achard, Aurélien , Bertin, Didier
摘要： A rotorcraft with at least one non-retractable wheel-type landing gear (8) and a fuselage comprising a lower shell, an inner floor (14), and at least one lower fuselage compartment arranged between the inner floor (14) and the lower shell, wherein the at least one non-retractable wheel-type landing gear (8) is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber (8b) connected to the at least one wheel and comprising a shock absorber tube (8c) and a shock absorber rod (8d) telescopically mounted to the shock absorber tube (8c); at least two mounting arms (8e) extending laterally from the shock absorber tube (8c); and a mounting pin (16) extending from the shock absorber tube (8c) toward a floor fitting (14d) provided at the inner floor (14), wherein the mounting pin (16) is connected to the floor fitting (14d).
-
公开(公告)号：EP3184424A1
公开(公告)日：2017-06-28
申请号：EP16154604.9
申请日：2016-02-08
发明人： DU, Hao , HU, Huazhi , LI, Zhiyi
IPC分类号： B64C27/10
CPC分类号： B64C27/08 , B64C25/06 , B64C27/10 , B64C27/14 , B64C29/0025
摘要： A multi-rotor passenger-carrying aircraft, including an aircraft body with a passenger-carrying cabin and at least three aircraft arms arranged on the aircraft body. Each of the at least three aircraft arms is provided with a first propeller above the aircraft arm and driven to rotate by a first driving device, and a second propeller below the aircraft arm and driven to rotate by a second driving device. The aircraft can effectively reduce the area it occupies and meet the requirement of carrying capacity by arranging propellers of smaller size both above and below each aircraft arm instead of separately arranging a propeller of larger size on each aircraft arm in traditional means. Meanwhile, the multi-rotor passenger-carrying aircraft can implement various flight actions during flight by adjusting the rotate speed of the different driving devices respectively, which is convenient to control, with good maneuverability and controllability.
摘要翻译： 一种多旋翼载客飞机，包括一架载有客舱的飞机机身和至少三个布置在飞机机身上的飞机臂。 所述至少三个飞行器臂中的每一个在所述飞机臂上方设置有第一螺旋桨，所述第一螺旋桨由第一驱动装置驱动旋转，所述第二螺旋桨在所述飞机臂下方并由第二驱动装置驱动旋转。 通过在每个飞行器臂的上方和下方布置较小尺寸的螺旋桨，而不是以传统方式在每个飞行器臂上单独布置较大尺寸的螺旋桨，飞机可以有效地减小其占用的面积并满足承载能力的要求。 同时，多旋翼载客飞机可以通过分别调整不同驱动装置的转速来实现飞行中的各种飞行动作，控制方便，操控性好，可控性强。
-
-
公开(公告)号：EP2763896A4
公开(公告)日：2015-03-11
申请号：EP13795150
申请日：2013-11-13
发明人： WANG TAO , ZHAO TAO , CHEN SHAOJIE , OU ZHIGANG
IPC分类号： B64C39/02
CPC分类号： B64C27/08 , A63H27/12 , B64C1/30 , B64C25/06 , B64C25/32 , B64C27/00 , B64C27/54 , B64C39/024 , B64C2025/325 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2201/128 , B64C2201/14 , B64C2201/141 , B64C2201/20 , B64D31/14 , B64D43/00 , G01R33/0047 , G01V3/16 , G05D1/00 , Y10T29/49117
-
公开(公告)号：EP4389598A1
公开(公告)日：2024-06-26
申请号：EP22215343.9
申请日：2022-12-21
发明人： FINK, Axel , OIOLI-NETO, Reynaldo
摘要： A rotorcraft comprising a fuselage (2) forming at least one lower lateral fuselage compartment (2c) with at least a first fitting (10a), a second fitting (11c), and a third fitting (11d); and at least one non-retractable wheel-type landing gear (8) that comprises: at least one wheel (8a); a shock absorber (8b) with a shock absorber tube (8c) having an open end (8g) and an axially opposed closed end (8f), and a shock absorber rod (8d) telescopically mounted to the shock absorber tube via the open end; a first fixation (8p) provided close to the open end on the shock absorber tube and connected to the first fitting; a second fixation (8e) provided close to the closed end on the shock absorber tube and connected to the second fitting; and a third fixation (8i) provided close to the closed end on the shock absorber tube and connected to the third fitting.
-
公开(公告)号：EP4382415A1
公开(公告)日：2024-06-12
申请号：EP22315307.3
申请日：2022-12-06
发明人： Fink, Axel , Achard, Aurélien , Bertin, Didier
摘要： A rotorcraft with at least one non-retractable wheel-type landing gear (8) and a fuselage comprising a lower shell, an inner floor (14), and at least one lower fuselage compartment arranged between the inner floor (14) and the lower shell, wherein the at least one non-retractable wheel-type landing gear (8) is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber (8b) connected to the at least one wheel and comprising a shock absorber tube (8c) and a shock absorber rod (8d) telescopically mounted to the shock absorber tube (8c); at least two mounting arms (8e) extending laterally from the shock absorber tube (8c); and a mounting pin device (12) extending laterally from the shock absorber tube (8c) and comprising a mounting pin (16) connected to a floor fitting provided at the inner floor (14).
-
公开(公告)号：EP3242832A1
公开(公告)日：2017-11-15
申请号：EP16771469.0
申请日：2016-01-08
申请人： Vickers, Paul
发明人： Vickers, Paul
CPC分类号： B64C25/06 , B64C25/34 , B64C25/50 , B64C35/008
摘要： An aircraft comprising a fuselage and an undercarriage dependent from the fuselage, the undercarriage including at least one caster assembly mounting a landing wheel to provide vertical support for the aircraft when on land and able to caster relative the fuselage.
-
公开(公告)号：EP2763896B1
公开(公告)日：2017-09-20
申请号：EP13795150.5
申请日：2013-11-13
发明人： WANG, Tao , ZHAO, Tao , CHEN, Shaojie , OU, Zhigang
CPC分类号： B64C27/08 , A63H27/12 , B64C1/30 , B64C25/06 , B64C25/32 , B64C27/00 , B64C27/54 , B64C39/024 , B64C2025/325 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2201/128 , B64C2201/14 , B64C2201/141 , B64C2201/20 , B64D31/14 , B64D43/00 , G01R33/0047 , G01V3/16 , G05D1/00 , Y10T29/49117
-
公开(公告)号：EP4428031A1
公开(公告)日：2024-09-11
申请号：EP23160297.0
申请日：2023-03-06
申请人： Lilium GmbH
IPC分类号： B64C25/06
CPC分类号： B64C25/06 , B64C25/60 , B64C29/0008
摘要： The invention related to a Landing gear (10) for a vertical take-off and landing aircraft (100), comprising a wheel (20), a shock absorber (30) with an absorber connection (32) to connect to a fuselage (110) of the aircraft (100) and at least one attachment lever (40) with a lever connection (42) to connect to the fuselage (110) of the aircraft (100) spaced apart from the absorber connection (32), the wheel (20) being attached to the attachment lever (40) spaced apart from the lever connection (42), wherein the shock absorber (30) is connected to the wheel (20) directly or indirectly via a wheel connection (34) to provide a load path (LP) for vertical load from the wheel (20) to the absorber connection (32), and wherein the shock absorber (30) comprises a fuse pin (36) at the absorber connection (32) and/or the wheel connection (34) having a predetermined breaking load to break and release the connection at the absorber connection (32) and/or the wheel connection (34), and wherein the attachment lever (40) comprises a rotary bearing (41) providing a folding movement for the wheel (20) from an extended landing position (ELP) into a crash position (CP) when the fuse pin (36) breaks.
-
公开(公告)号：EP3150483A4
公开(公告)日：2017-09-20
申请号：EP16811654
申请日：2016-06-15
申请人： NAKAMURA KOHEI
发明人： NAKAMURA KOHEI
CPC分类号： B64B1/30 , B64B1/58 , B64C25/06 , B64C27/08 , B64C39/02 , B64C39/024 , B64C2201/022 , B64C2201/027 , B64C2201/101 , B64C2201/108 , B64C2201/127
摘要： Provided is a buoyant aerial vehicle which can secure high safety by reducing the risk of crashing, and which can facilitate control of movement by suppressing the influence of wind and exhibit high mobility capability. The buoyant aerial vehicle is configured by including: a buoyant vehicle body in which gas having a specific gravity smaller than air is hermetically filled; a vertical propulsion propeller which provides vertical propulsive force to the buoyant vehicle body; and a horizontal propulsion propeller which provides horizontal propulsive force to the buoyant vehicle body, and is configured such that the buoyant vehicle body has horizontal wind passages formed in at least two directions, and has outer peripheral edges each formed into an acute angle in side view.
摘要翻译： 本发明提供一种浮力飞行器，其能够通过降低碰撞风险来确保较高的安全性，并且能够通过抑制风的影响来促进对运动的控制，并且具有高运动能力。 所述浮力飞行器通过包括：浮力车体，在所述浮力车体中气密地填充比重小于空气的气体; 向浮力车体提供垂直推进力的垂直推进螺旋桨; 以及向浮力车体提供水平推进力的水平推进螺旋桨，并且浮力车体具有形成在至少两个方向上的水平风道，并且具有在侧视图中形成为锐角的外周边缘 。
-
-
-
-
-
-
-
-
-
搜索结果
19 条记录 (耗时 0.015 秒)
