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公开(公告)号：WO2006006151A1
公开(公告)日：2006-01-19
申请号：PCT/IL2005/000714
申请日：2005-07-06
Applicant: ELBIT SYSTEMS LTD. , SIRKIS, Omri
Inventor： SIRKIS, Omri
IPC: B64C39/02
CPC classification number: B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/086 , B64C2201/104 , B64C2201/167 , B64C2201/187
Abstract: There is provided an Unmanned Air Vehicule (uav) (2) including an engine (4) and an airframe (6), including means for performing a deep stall maneouvre; at least one inflatable sleeve (12) connected or connectable to the airframe (6), and means for inflating the sleeve (12) during flight, wherein the inflated sleeve (12) extends along the lower side of the airframe (6) so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.
Abstract translation: 提供了包括发动机（4）和机身（6）的无人驾驶飞机（uav）（2），其中包括用于执行深度失速行动的手段; 连接或连接到机身（6）的至少一个可充气套筒（12）以及用于在飞行期间使套筒（12）膨胀的装置，其中所述充气套筒（12）沿着所述机身（6）的下侧延伸，以便 在深层失速登陆期间保护相同。 还提供了一种用于操作无人机（UAV）的方法，包括发动机和机身。
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公开(公告)号：WO2004063008A3
公开(公告)日：2004-09-23
申请号：PCT/US2004000687
申请日：2004-01-13
Applicant: BOXAIR ENGINEERING LLC , STUPAKIS JOHN S
Inventor： STUPAKIS JOHN S
CPC classification number: B64C39/024 , B64C39/02 , B64C2201/048 , B64C2201/086 , B64C2201/104 , B64C2201/128 , B64C2201/141 , B64C2201/165 , B64C2201/187 , B64C2211/00 , B64D2011/0046 , Y10S244/903
Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.
Abstract translation: 一种模块化的自动航空运输系统，包括具有选择性地可拆卸的控制系统部分和结构空气框架部分的无人自主飞行器，其中所述结构空气框架部分包含内部货舱，具有控制表面的空气动力部件和附接到 结构空气框架部分; 并且其中所述控制系统部分包括用于自主地控制所述空中运输系统从一个已知位置到第二已知位置的飞行的控制计算机。
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公开(公告)号：WO2004063008A2
公开(公告)日：2004-07-29
申请号：PCT/US2004/000687
申请日：2004-01-13
Applicant: BOXAIR ENGINEERING, LLC , STUPAKIS, John, S.
Inventor： STUPAKIS, John, S.
IPC: B64C
CPC classification number: B64C39/024 , B64C39/02 , B64C2201/048 , B64C2201/086 , B64C2201/104 , B64C2201/128 , B64C2201/141 , B64C2201/165 , B64C2201/187 , B64C2211/00 , B64D2011/0046 , Y10S244/903
Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.
Abstract translation: 一种模块化自动化空中运输系统，包括具有选择性可拆卸控制系统部分和结构空气框架部分的无人自主飞机，其中所述结构空气框架部分包含内部货舱，空气动力学构件具有控制表面 以及至少一个连接到结构空气框架部分的推进装置; 并且其中所述控制系统部分包括用于自主地控制所述空中交通系统从一个已知位置到第二已知位置的飞行的控制计算机。
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公开(公告)号：WO0176941A9
公开(公告)日：2002-12-27
申请号：PCT/US0110876
申请日：2001-04-03
Applicant: AEROVIRONMENT INC
Inventor： MACCREADY PAUL , HIBBS BART D , CURTIN ROBERT F JR , SWANSON KYLE D , BELIK PAUL
IPC: B64C1/26 , B64C3/10 , B64C3/14 , B64C3/36 , B64C9/24 , B64C39/02 , B64C39/10 , B64D27/02 , B64D27/24 , B64D37/30 , H01M8/00 , B64C9/22 , F17C9/02 , H01M8/04
CPC classification number: B64D27/24 , B64C1/26 , B64C3/10 , B64C3/14 , B64C9/24 , B64C39/024 , B64C39/10 , B64C2201/021 , B64C2201/028 , B64C2201/042 , B64C2201/086 , B64C2201/104 , B64C2201/122 , B64C2201/141 , B64C2201/146 , B64C2201/165 , B64C2201/187 , B64D27/02 , B64D37/30 , B64D2041/005 , Y02T50/12 , Y02T50/32 , Y02T50/44 , Y02T50/64 , Y02T90/36
Abstract: Disclosed is an aircraft (101), configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft (101) includes an extendable slat (205) at the leading edge of the wing (103), and a reflexed trailing edge. The aircraft comprises a flying wing (103) extending laterally between two ends and a center point. The wing (103) is swept and has a relatively constant chord. The aircraft (101) also includes a power module configured to provide power via a fuel cell (131). The fuel cell (131) stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell (131). A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft (101) of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing (103).
Abstract translation: 公开了一种飞机（101），其被配置为具有宽范围的飞行速度，在较长的时间段内消耗较低的功率水平，同时支撑具有无遮挡的向下看的视图的通信平台。 飞机（101）包括在机翼（103）的前缘处的可伸展缝翼（205）和反折后缘。 该飞机包括在两端和中心点之间横向延伸的飞翼（103）。 翼（103）被扫过并且具有相对恒定的弦。 飞机（101）还包括配置成经由燃料电池（131）提供电力的电力模块。 燃料电池（131）储存液态氢作为燃料，但在燃料电池（131）中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 本发明的飞行器（101）包括包括多个支撑件的支撑结构，其中支撑件形成附着到机翼（103）的四面体。
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公开(公告)号：US09815563B2
公开(公告)日：2017-11-14
申请号：US15090571
申请日：2016-04-04
Applicant: W. Morrison Consulting Group, Inc.
Inventor： William M. Yates , Robert Ussery , Byron Young
CPC classification number: B64D39/00 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/066 , B64C2201/104 , B64C2201/127 , B64C2201/146 , B64C2201/187 , B64D5/00 , B64D27/24
Abstract: Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, through the use of unmanned aerial vehicle (UAV) packs flying independent of and in proximity to the electric aircraft.
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Patent Agency Ranking
公开(公告)号：US20170297706A1
公开(公告)日：2017-10-19
申请号：US15338802
申请日：2016-10-31
Applicant: Ewatt Technology Co., Ltd.
Inventor： Guocheng ZHAO , Wei LUO
CPC classification number: B64C39/024 , B64C1/00 , B64C1/06 , B64C3/00 , B64C5/02 , B64C25/58 , B64C39/028 , B64C2201/021 , B64C2201/042 , B64C2201/08 , B64C2201/104 , B64C2201/146 , B64C2201/162 , B64C2201/165 , B64C2201/187
Abstract: The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.
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公开(公告)号：US09731818B2
公开(公告)日：2017-08-15
申请号：US14372060
申请日：2013-01-10
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Guy Dekel , Lior Zivan , Yoav Efraty , Amit Wolff , Avner Volovick
CPC classification number: B64C27/26 , B64C19/00 , B64C29/00 , B64C29/0033 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/086 , B64C2201/104 , B64C2201/162 , B64C2201/165 , B64C2201/187 , G05D1/0676 , G05D1/0858
Abstract: A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle.
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公开(公告)号：US20170139420A1
公开(公告)日：2017-05-18
申请号：US15419804
申请日：2017-01-30
Applicant: Ford Global Technologies, LLC
Inventor： John A. Lockwood , Joseph F. Stanek
CPC classification number: G05D1/0276 , B60R16/02 , B60W30/00 , B64C29/0008 , B64C29/0091 , B64C29/02 , B64C39/00 , B64C39/02 , B64C39/022 , B64C39/024 , B64C2201/00 , B64C2201/02 , B64C2201/08 , B64C2201/086 , B64C2201/088 , B64C2201/12 , B64C2201/126 , B64C2201/127 , B64C2201/14 , B64C2201/141 , B64C2201/18 , B64C2201/182 , B64C2201/185 , B64C2201/187 , B64C2201/20 , B64C2201/208 , B64C2230/00 , G05D1/0022 , G05D1/0088 , G05D1/0094 , G05D1/0202 , G05D1/0212 , G05D1/0231 , G05D1/0242 , G05D1/0255 , G05D1/0257 , G05D1/028 , G05D2201/0213 , G08C17/00 , G08G1/012 , G08G1/091
Abstract: This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced.
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公开(公告)号：US09555885B2
公开(公告)日：2017-01-31
申请号：US15231579
申请日：2016-08-08
Applicant: Ford Global Technologies, LLC
Inventor： Joseph F. Stanek , John A. Lockwood
CPC classification number: G05D1/0276 , B60R16/02 , B60W30/00 , B64C29/0008 , B64C29/0091 , B64C29/02 , B64C39/00 , B64C39/02 , B64C39/022 , B64C39/024 , B64C2201/00 , B64C2201/02 , B64C2201/08 , B64C2201/086 , B64C2201/088 , B64C2201/12 , B64C2201/126 , B64C2201/127 , B64C2201/14 , B64C2201/141 , B64C2201/18 , B64C2201/182 , B64C2201/185 , B64C2201/187 , B64C2201/20 , B64C2201/208 , B64C2230/00 , G05D1/0022 , G05D1/0088 , G05D1/0094 , G05D1/0202 , G05D1/0212 , G05D1/0231 , G05D1/0242 , G05D1/0255 , G05D1/0257 , G05D1/028 , G05D2201/0213 , G08C17/00 , G08G1/012 , G08G1/091
Abstract: This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced.
Abstract translation: 本公开总体上涉及一种汽车无人机部署系统，该系统至少包括车辆和可部署的无人机，其配置为从车辆附接和分离。 更具体地，本公开描述了当车辆以自主驾驶模式操作时彼此保持通信的车辆和无人机交换信息，使得车辆在自主驾驶模式下的性能得到增强。
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公开(公告)号：US09221557B1
公开(公告)日：2015-12-29
申请号：US13788053
申请日：2013-03-07
Applicant: Lockheed Martin Corporation
Inventor： Mark A. Friesel
IPC: B64F1/02
CPC classification number: B64F1/025 , B64C39/024 , B64C2201/182 , B64C2201/187 , B64F1/02
Abstract: An apparatus for capture of an unmanned aerial vehicle (UAV) comprises a wind tunnel including at least one fan for generating airflow in the wind tunnel; sensors for sensing characteristics of the UAV; and a control system coupled to said sensors and said at least one fan. The control system is configured to cause the at least one fan to generate airflow based on the sensed characteristics of the UAV to bring the UAV that is in the wind tunnel to a low or zero airspeed above a floor of the wind tunnel, thereby allowing the UAV to be dropped onto the floor of the wind tunnel when the airflow and a motive force of the UAV are stopped.
Abstract translation: 用于捕获无人驾驶飞行器（UAV）的装置包括风洞，其包括用于在风洞中产生气流的至少一个风扇; 用于感测无人机特性的传感器; 以及耦合到所述传感器和所述至少一个风扇的控制系统。 控制系统被配置成使得至少一个风扇基于UAV的感测特征产生气流，以使处于风洞中的无人机在风洞地板上方的低空或零空速，从而允许 当无人机的气流和无人机的动力停止时，无人机落在风洞的地板上。
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