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公开(公告)号：WO2021037463A1
公开(公告)日：2021-03-04
申请号：PCT/EP2020/071244
申请日：2020-07-28
Applicant: SONY CORPORATION , SONY EUROPE B.V.
Inventor： SCHAEFER, Henrik , BECKER, Florian
Abstract: A method for autonomous in-flight transfer of a load from a first Aerial Vehicle, AV, to a second AV is provided. Each of the first AV and the second AV includes a frame with a vertical opening for receiving the load. A plurality of rotors are attached to the frame. The method comprising autonomously performing the following in-flight: fastening means of the first AV hold the load in the vertical opening of the first AV such that a bottom end of the load is accessible by the second AV; the second AV approaches the first AV from below in order to couple a fastening means of the second AV to the bottom end of the load; the fastening means of the first AV releases the load after the fastening means of the second AV couples to the bottom end of the load; and the fastening means of the second AV lower the load with respect to the frame of the second AV in order to move the load into a flight position.
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公开(公告)号：WO2018133640A1
公开(公告)日：2018-07-26
申请号：PCT/CN2017/119375
申请日：2017-12-28
Applicant: 秦赵修
Inventor： 秦赵修
IPC: B64F1/10
Abstract: 一种低风阻管道式轨道、内置轨道的模拟平流层低风阻管道、运载火箭航天器发射系统及降低管道式轨道阻力的方法，涉及运载火箭航天器发射技术领域，该低风阻管道式轨道包括路基（1）和固设在路基（1）上的多个管道本体（2），多个管道本体（2）依次连续固接，所述路基（1）上铺设有轨道（3），各所述管道本体（2）沿所述轨道（3）的铺设方向跨设在所述轨道（3）的上方，管道本体（2）包括设置在其两端的第一固定件（21）、第二固定件（22）、多个风管（23）和多个加热单元（24），且相邻两管道本体（2）的多个风管（23）分别对应相通，多个风管（23）上分别对应连通有多个鼓风件（4），且多个风管（23）上沿轴向等间距分别设有多个出风口（231），多个出风口（231）处的气流能够彼此交汇。低风阻管道式轨道具有能够使得火箭运输装置在低海拔地区向高海拔地区高速运行的特点。
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公开(公告)号：WO2007043463A1
公开(公告)日：2007-04-19
申请号：PCT/JP2006/320080
申请日：2006-10-06
Abstract: 【課題】 高速で重量の大きな航空機であっても安全に、しかも効率よく加速できる加速装置の提供。 【解決手段】 航空機を加速中に後退、浮上させず、しかもピッチングさせないように支持する支持台と、所定の経路に沿って設けられたガイドウェイと、前記ガイドウェイに沿って前記支持台を案内する案内手段と、前記支持台を前記ガイドウェイに沿って駆動する駆動手段とを備える加速装置。
Abstract translation: [问题]即使是能够安全有效地加速飞机的加速装置也是高速重型的。 [解决问题的手段]加速装置具有用于支撑飞机的支撑基座，使得其不回退，不抬起，并且不执行俯仰; 沿着预定路线放置的引导方式; 用于沿着所述引导方向引导所述支撑基座的引导装置; 以及用于沿着引导方向驱动支撑基座的驱动装置。
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公开(公告)号：WO01044048A1
公开(公告)日：2001-06-21
申请号：PCT/AU2000/001540
申请日：2000-12-13
CPC classification number: B64F1/22
Abstract: An articulated tractor (10) for towing an aircraft comprising a front section (10A) including an engine means (18) and a rear section (10B) pivoted to the front section (10a), the rear section (10B) defining a nose wheel clamp means (34) for engaging and raising the nose wheel (36) of an aircraft. In another embodiment the clamping force applied to the nose wheel (36) by the nose wheel clamp means (34) is proportional to the mass of the nose wheel (32). Still in another embodiment the nose wheel clamp means (34) are provided with relief valve means to relieve if the raising force applied to the nose wheel (36) increases beyond a predetermined limit.
Abstract translation: 一种用于牵引飞行器的铰接式拖拉机（10），包括一个包括发动机装置（18）的前部（10A）和枢转于前部（10a）的后部（10B）的前部， 用于接合和提升飞行器前轮（36）的夹紧装置（34）。 在另一个实施例中，前轮夹紧装置（34）施加到前轮（36）的夹紧力与前轮（32）的质量成比例。 在另一个实施例中，前轮夹紧装置（34）设置有安全阀装置以减轻施加到前轮（36）的提升力是否增加超过预定极限。
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公开(公告)号：WO2022182803A1
公开(公告)日：2022-09-01
申请号：PCT/US2022/017585
申请日：2022-02-23
Applicant: ZIPLINE INTERNATIONAL INC.
Inventor： BOOMGAARD, Brian , LASZLO, Zoltan , WYROBEK, Keenan A.
Abstract: An autonomous vehicle (AV) delivery system is configured to deliver a payload or package in a rural and/or urban environment. The AV delivery system includes a first autonomous vehicle (AV). The first AV is configured to travel between a payload receiving location and a payload drop location. The AV delivery system further includes a second autonomous vehicle (AV) coupled to the first AV. The second AV is coupled to a payload and configured to travel between the first AV and a designated drop target adjacent to a ground or receiving surface at the payload drop location.
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Patent Agency Ranking
公开(公告)号：WO2016094543A3
公开(公告)日：2016-08-04
申请号：PCT/US2015064771
申请日：2015-12-09
Applicant: LOCKHEED CORP
Inventor： MCKEE THOMAS SANDLIN , RODEN STEVE CONRAD
CPC classification number: B64F1/10 , B60P3/11 , B64C39/024 , B64C2201/08 , B64C2201/14 , B64C2201/182 , G05D1/021
Abstract: A UAV support vehicle carries a UAV support apparatus for launching and/or recovering a UAV while the UAV support vehicle is moving. The UAV support apparatus releases the UAV during launch and receives the UAV during recovery. An active suspension may be connected between the UAV support vehicle and at least a portion of the UAV support apparatus and reduce motion imparted to that portion of the UAV support apparatus. During UAV recovery, data from a synchronization link between the UAV and the UAV support vehicle may be used to maneuver the UAV and/or the UAV support vehicle.
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公开(公告)号：WO2016094543A2
公开(公告)日：2016-06-16
申请号：PCT/US2015/064771
申请日：2015-12-09
Applicant: LOCKHEED MARTIN CORPORATION
Inventor： MCKEE, Thomas, Sandlin , RODEN, Steve, Conrad
CPC classification number: B64F1/10 , B60P3/11 , B64C39/024 , B64C2201/08 , B64C2201/14 , B64C2201/182 , G05D1/021
Abstract: A UAV support vehicle carries a UAV support apparatus for launching and/or recovering a UAV while the UAV support vehicle is moving. The UAV support apparatus releases the UAV during launch and receives the UAV during recovery. An active suspension may be connected between the UAV support vehicle and at least a portion of the UAV support apparatus and reduce motion imparted to that portion of the UAV support apparatus. During UAV recovery, data from a synchronization link between the UAV and the UAV support vehicle may be used to maneuver the UAV and/or the UAV support vehicle.
Abstract translation: 无人机支援车载有无人机支援装备，用于在无人机支援车辆正在移动时发射和/或恢复无人机。 UAV支持设备在发射过程中释放无人机，并在恢复期间接收UAV。 主动悬架可以连接在无人机支援车辆与无人机支援装置的至少一部分之间，并减少赋予该无人机支援装置部分的动作。 在UAV恢复期间，可以使用来自UAV和UAV支持车辆之间的同步链路的数据来操纵UAV和/或UAV支持车辆。
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8.发明申请A CARRIER-BORNE AIRCRAFT TAKEOFF/LANDING SYSTEM AND METHODS OF USING THE SAME 审中-公开载波飞行器起飞/起飞系统及其使用方法
公开(公告)号：WO2010113030A3
公开(公告)日：2011-05-12
申请号：PCT/IB2010000886
申请日：2010-03-10
Applicant: WANG LIFENG
Inventor： WANG LIFENG
Abstract: The present invention provides a carrier-borne aircraft takeoff/landing system comprising a takeoff auxiliary mechanism and/or an integrated runway which are/is positioned on the aircraft carrier. The takeoff auxiliary mechanism can be a sliding vehicle or a simple pendulum type projectile mechanism, the integrated runway is a carrier-borne aircraft runway which can be extended out of the aircraft carrier. The carrier-borne aircraft takeoff/landing system of the present invention concentrates the advantages of current ways of catapult launch and ski-jump takeoff and abandons the faults existed, which can reduce the difficulties and risks involved during the traditional landing. The takeoff/landing system which is outstanding for its simple structure, significantly reduced research cost and energy consumption, with improved efficiency, easy operation and maintenance, high reliability, which are applicable to various carrier-borne aircraft for take off and/or landing.
Abstract translation: 本发明提供一种载体飞行器起飞/着陆系统，其包括位于航空母舰上的起飞辅助机构和/或集成跑道。 起飞辅助机构可以是滑动车辆或简单的摆锤式抛射机构，综合跑道是可以延伸出航空母舰的载体飞机跑道。 本发明的载波飞机起飞/着陆系统集中了当前弹射发射和滑雪起飞方式的优点，放弃了存在的故障，可以减少传统降落过程中的困难和风险。 起飞/着陆系统结构简单，大大降低了研究成本和能耗，提高了效率，操作维护方便，可靠性高，适用于起飞和/或降落的各种载体飞机。
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公开(公告)号：WO01026968A1
公开(公告)日：2001-04-19
申请号：PCT/GB2000/003823
申请日：2000-10-06
Abstract: A system for warning the driver (8) of a vehicle (2) towing an aircraft (1) comprises four transmitters (9a to 9d) which are carried by observers positioned adjacent to the nose, the tail and the wing tips of the aircraft. A receiver (4) and a siren (7) are positioned within the vehicle (2). The siren (7) is operatively associated with the receiver (4). The system is such that actuation of a transmitter (9a, 9b, 9c or 9d) transmits a warning signal to the receiver (4) which triggers the siren (7).
Abstract translation: 用于警告牵引飞行器（1）的车辆（2）的驾驶员（8）的系统包括四个发射器（9a至9d），其由与飞机的鼻子，尾翼和翼尖相邻定位的观察者携带。 接收器（4）和警报器（7）位于车辆（2）内。 警报器（7）可操作地与接收器（4）相关联。 该系统使得发射器（9a，9b，9c或9d）的致动将警告信号发送到触发警报器（7）的接收器（4）。
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公开(公告)号：WO2023285851A1
公开(公告)日：2023-01-19
申请号：PCT/IB2021/000490
申请日：2021-07-13
Applicant: ATHENA PI
Inventor： CLERMONT, Lionel
IPC: B64F1/00 , B64F5/00 , B64F1/10 , B64F1/22 , B64F1/28 , B64F1/30 , B64F1/32 , B64F1/34 , B64F1/36 , B64F5/20 , B64F5/30
Abstract: The invention relates to an aircraft ground support unit (1) (GSU) for supplying a specific service according to a specific set of service parameters to an aircraft (2) on the ground and consuming a specific service energy for supplying the specific service as a whole in a given available service duration, the GSU comprising: a rechargeable energy storage unit (3) (RESU) which, when fully charged, is configured for autonomously delivering the specific service energy required for supplying the specific service in the given available service duration, an energy sensor (4) configured for measuring an instantaneous state of energy parameters of the RESU, a control unit (5) configured for, • identifying the aircraft (2), preferably including an aircraft type and an airline, • identifying in the database the specific set of service parameters of the specific service to the thus identified aircraft, • establishing a specific service energy budget estimate corresponding to the specific set of service parameters in various ways, • determining an instantaneous charge level of the RESU based on the instantaneous state of the energy variables, • comparing the specific service energy budget estimate with the instantaneous charge level of the RESU, and for • generating an output signal representative of a capacity of the RESU to deliver the specific service energy budget estimate as a function of the instantaneous charge level of the RESU.
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