专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

61. 发明公开

EP0781224A4 HINGED AIRCRAFT SKI FOR IMPROVING EGRESS AND INGRESS FROM AN AIRCRAFT CABIN 失效
标题翻译：折叠FLUGGERÄTKUFE以提高教育和在机舱内可能公司
公开(公告)号：EP0781224A4
公开(公告)日：1999-06-09
申请号：EP95933725
申请日：1995-08-29
申请人： LANDES WESLEY K , LANDES GARY I
发明人： LANDES WESLEY K , LANDES GARY I
IPC分类号： B64C25/52 , B64C25/54 , B64D25/18 , B64D45/04
CPC分类号： B64C25/52 , B64C2025/325
摘要： A flotation apparatus, specifically a ski (27), is provided for use on an aircraft (21) for improving the egress and ingress from the aircraft cabin (20). The ski (27) is particularly applicable to helicopters (21) having fixed wheeled landing gear (23) wherein the helicopter (21) engages in rope repelling missions or wherein egress and ingress from the helicopter cabin (20) may be performed during low hover operations. The ski (27) includes a forward portion (55) substantially fixed in a parallel configuration with respect to the longitudinal axis of the helicopter and an aft portion (57). The aft portion (57) is rotatable from a substantially parallel configuration with respect to the longitudinal axis of the helicopter to a substantially perpendicular configuration with respect to the longitudinal axis of the helicopter; the aft portion (57) is rotatably attached to the forward portion (55) using a fastener, specifically a hinge means (35). During use, an operator uses a grapple hook (77) to release at least one latching mechanism (65) wherein the aft portion (57), under the force of gravity and from the downwash of the rotor blades, rotates into the substantially perpendicular relationship with respect to the longitudinal axis of the helicopter, in this configuration egress and ingress from the helicopter cabin is not impeded. To reconfigure the aft portion (57) into a flight or landing configuration, the operator grasp the aft portion (57) with the grapple hook (77) thereby pulling upward on the aft portion (57) until the aft portion (57) is securely latched to the forward portion (55).

62. 发明授权

EP0512897B1 Train d'atterrissage pour aérodyne, avec arceaux en matériau composite 失效
标题翻译：飞机起落架，具有纤维增强的塑料执行弧。
公开(公告)号：EP0512897B1
公开(公告)日：1995-02-08
申请号：EP92401222.2
申请日：1992-04-29
申请人： AEROSPATIALE Société Nationale Industrielle
发明人： Guimbal, Bruno
IPC分类号： B64C25/52
CPC分类号： B64C25/52 , B64C2025/325

63. 发明授权

EP4279379B1 TRAIN D'ATTERRISSAGE À PATINS MUNI DE PATINETTES ANTI-ENFONCEMENT 有权
公开(公告)号：EP4279379B1
公开(公告)日：2024-03-13
申请号：EP23160794.6
申请日：2023-03-08
发明人： GENELOT, Nicolas
IPC分类号： B64C25/32 , B64C25/52

64. 发明公开

EP4159616A1 ENTRAVE POUR SÉCURISER UN AÉRONEF SUR UNE GRILLE D'ATTERRISSAGE ET AÉRONEF 审中-实审
公开(公告)号：EP4159616A1
公开(公告)日：2023-04-05
申请号：EP22190107.7
申请日：2022-08-12
申请人： Airbus Helicopters
发明人： GAILLARD, Christophe , DURANTET, Joël , RASPIC, Nicolas
IPC分类号： B64C25/32 , B64F1/12 , B64C25/52
摘要： La présente invention concerne une entrave (20) pour un aéronef (1). L'entrave (20) comporte un vérin (50) comprenant un boîtier (51) et une tête (70) mobile en translation par rapport au boîtier (51) selon un axe en élévation (AXALT), ladite tête (70) présentant trois degrés de liberté en rotation respectivement selon un axe longitudinal (AXL) ainsi qu'un axe transversal (AXT) et l' axe en élévation (AXALT), ladite entrave (20) comprenant un organe de reprise d'efforts (40) entourant le vérin (50) et muni d'une fixation (42) apte à être solidarisée à l'aéronef (1).

65. 发明公开

EP4098558A1 AIRCRAFT SAFETY LIFESAVING SYSTEM 审中-实审转让
公开(公告)号：EP4098558A1
公开(公告)日：2022-12-07
申请号：EP21215654.1
申请日：2021-12-17
申请人： Du, Di , Du, Yang
发明人： Du, Di , Du, Yang , Du, Tong
IPC分类号： B64C1/32 , B64C25/58 , B64D17/80 , B64D25/00 , B64D45/04 , B64C1/14 , B64C7/00 , B64C25/00 , B64C25/30 , B64C25/52 , B64C27/00 , B64D45/06
摘要： The present disclosure provides an aircraft safety lifesaving system, which solves the technical problem that the aircraft lacks a device capable of assisting the aircraft to decelerate and land and buffering the descending impact force, and it is difficult to better ensure the safety of the aircraft and its staff. The lifesaving system comprises an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism is provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body. According to the present disclosure, a safety cabin is provided at the top of the aircraft body, and a deceleration device in the safety cabin is ejected in an emergency to assist the aircraft body to decelerate; the damping and buffering mechanism extends below the wheel body, and the damping and buffering mechanism contacts with the ground first, so that the impact force when the aircraft body descends can be buffered, and serious accidents caused by the impact force when the aircraft body descends can be prevented.

66. 发明公开

EP3878736A1 AIRCRAFT HAVING CONVERTIBLE TAILBOOM AND LANDING GEAR SYSTEMS 有权转让
公开(公告)号：EP3878736A1
公开(公告)日：2021-09-15
申请号：EP21155300.3
申请日：2021-02-04
申请人： Bell Textron Inc.
发明人： BERNARD, Guy
IPC分类号： B64C25/52 , B64C29/00 , B64C5/02 , B64C5/12 , B64C25/14
摘要： A tiltwing aircraft (10) convertible between a vertical takeoff and landing flight mode and a forward flight mode includes a fuselage (12), a tiltwing (14, 16) rotatably coupled to the fuselage and a convertible tailboom and landing gear system (38) rotatably coupled to the fuselage. The tiltwing is rotatable between a substantially vertical position in the vertical takeoff and landing flight mode and a substantially horizontal position in the forward flight mode. The convertible tailboom and landing gear system is rotatable between a landing gear position in the vertical takeoff and landing flight mode and a tailboom position in the forward flight mode. The convertible tailboom and landing gear system includes skids (40, 42) and linkages (44, 46) that rotatably couple the skids to the fuselage. The skids are positioned below the fuselage in the landing gear position and extend aft of the fuselage in the tailboom position.

67. 发明公开

EP3326912A1 UNMANNED AERIAL VEHICLE LANDING SYSTEM 审中-公开
公开(公告)号：EP3326912A1
公开(公告)日：2018-05-30
申请号：EP16200519.3
申请日：2016-11-24
申请人： DroneGrid BVBA
发明人： van der Vaeren, Stanislas , Bossens, Maxime
IPC分类号： B64C39/02 , B64C25/52 , B64C27/08
CPC分类号： B64C39/024 , B64C25/52 , B64C27/08
摘要： The present invention generally provides an unmanned aerial vehicle (UAV) and a system comprising the unmanned aerial vehicle and a docking station. The UAV comprises (A) a main body (110) having a central axis; (B) a frame coupled to the main body (110) comprising a plurality of flight arms (120), each flight arm (120) extending laterally outward from the main body (110) and comprising at least one rotor (125) configured for providing flight; and (C) at least three or at least four landing units (150) optionally equally spread out about the central axis of the main body (110), each landing unit comprising (C.i) a support member (160) having at least a first means of attachment for attaching the landing unit (150) to the frame or the main body (110); and (C.ii) a skid (170) attached to the support member (160) and disposed at an angle of incline of at least 20° to at most 70° to the central axis, preferably at least 30° to at most 60°. The plurality of landing units is adapted to allow the UAV to land and rest in a stable position within the docking station as a surface.

68. 发明公开

EP3313732A1 SYSTEM FOR RECHARGING REMOTELY CONTROLLED AERIAL VEHICLE, CHARGING STATION AND RECHARGEABLE REMOTELY CONTROLLED AERIAL VEHICLE, AND METHOD OF USE THEREOF 审中-公开
标题翻译：用于再充电遥控飞行器，充电站和可再充电遥控飞行器的系统及其使用方法
公开(公告)号：EP3313732A1
公开(公告)日：2018-05-02
申请号：EP16800654.2
申请日：2016-05-25
申请人： First Principles, Inc.
发明人： RANIERE, Keith A.
IPC分类号： B64C39/02 , B64C25/52 , B60L11/18 , G08G5/00
CPC分类号： B64C39/024 , B60L11/1816 , B60L11/1844 , B64C25/52 , B64C2201/024 , B64C2201/042 , B64C2201/146 , B64F1/007
摘要： A system including an aerial vehicle having an airframe and a power source onboard the aerial vehicle, wherein the aerial vehicle includes a landing gear structure having a first electrical contact and a second electrical contact, and a charging station having a first electrical contact and a second electrical contact, wherein the aerial vehicle is programmed to dock with the charging station when the power source is in need of recharging, the docking being a mechanical engagement between the first electrical contact and the second electrical contact of the aerial vehicle with the first electrical contact and the second electrical contact of the charging station is provided. A method for continuous surveillance utilizing the aerial vehicles and charging stations is also provided.

69. 发明授权

EP2679490B1 LIGHTWEIGHT LANDING GEAR SKID SHOE ASSEMBLY 有权
标题翻译：轻质SKID LANDING塔架工厂
公开(公告)号：EP2679490B1
公开(公告)日：2016-12-21
申请号：EP12178623.0
申请日：2012-07-31
申请人： Bell Helicopter Textron Inc.
发明人： McCollough, James , Amante, William
IPC分类号： B64C25/52 , B64C25/32
CPC分类号： B64C25/52 , B64C2025/325
摘要： A lightweight skid shoe assembly (100) comprises a body (200) of wear resistant, non-metallic or partially metallic material; and a structure coupling mechanism (300); wherein the body prevents friction-related damage to the structure. Another lightweight skid shoe assembly (150) comprises a body of wear resistant, non-metallic or partially metallic material selected from the group consisting of: a polyamide or polyimide impregnated carbon fiber layup, a peek or PEI injection mold with carbon fiber, compression molded carbon fiber or fiberglass, a resin infusion with carbon fiber preform fabric, a fiber reinforced thermoset, acetal resin, machined acetal or thermoplastic, thermosetting plastic, or a metal-matrix composite; wherein the body prevents friction-related damage to a structure. Another lightweight skid shoe assembly (180) comprises a body of wear resistant, non-metallic or partially metallic material; and a shear-bearing mechanism (400); wherein the shear-bearing mechanism directs shear forces away from the body; and wherein the body prevents friction-related damage to the structure.

70. 发明授权

EP2610173B1 FIXED-PITCH COAXIAL CONTRA-ROTATING HELICOPTER 有权
标题翻译：共轴式直升机反对有固定转子回转
公开(公告)号：EP2610173B1
公开(公告)日：2016-10-05
申请号：EP11819588.2
申请日：2011-08-23
申请人： Gen Corporation
发明人： YOKOYAMA, Yasutoshi
IPC分类号： B64C27/10 , B64C27/52 , B64C39/02 , B64C25/52
CPC分类号： B64C27/10 , B64C25/52 , B64C27/52 , B64C39/026 , B64C2025/325

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式