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61.发明申请公开(公告)号：US20050151009A1
公开(公告)日：2005-07-14
申请号：US10760150
申请日：2004-01-16
Applicant: Cory Roeseler , Andreas von Flotow
Inventor： Cory Roeseler , Andreas von Flotow
CPC classification number: B64C39/024 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/084 , B64C2201/102 , B64C2201/146 , B64C2201/165 , B64C2201/182 , B64C2201/201 , B64C2201/205 , B64F1/06
Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that operates with a wedge action. A launch carriage carrying an unmanned aircraft is positioned on first and second launch members. At least one of the launch members moves relative to the other from a first position to a second position, causing the launch carriage to move from a first launch carriage position to a second launch carriage position. As the launch carriage moves, it accelerates the aircraft and releases the aircraft for takeoff.
Abstract translation: 描述了发射无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从用楔形动作操作的装置发射。 携带无人机的发射架位于第一和第二发射构件上。 发射构件中的至少一个相对于另一个从第一位置移动到第二位置，使得发射托架从第一发射托架位置移动到第二发射托架位置。 随着发射架移动，它加速飞机并释放飞机起飞。
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62.发明申请Methods and apparatuses for capturing unmanned aircraft and constraining motion of the captured aircraft 有权用于捕获无人驾驶飞机并限制所捕获的飞行器的运动的方法和装置公开(公告)号：US20050133665A1
公开(公告)日：2005-06-23
申请号：US10759545
申请日：2004-01-16
Applicant: Brian Dennis , Brian McGeer , Cory Roeseler
Inventor： Brian Dennis , Brian McGeer , Cory Roeseler
CPC classification number: B64C39/024 , B64C25/68 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/084 , B64C2201/102 , B64C2201/146 , B64C2201/165 , B64C2201/182 , B64C2201/205 , B64F1/02 , B64F1/04 , B64F1/06
Abstract: Methods and apparatuses for capturing and constraining motion of unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. A trigger mechanism coupled to the recovery line can actuate a hoist device to reduce slack in the recovery line. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft on the recovery line.
Abstract translation: 描述了用于捕获和约束无人驾驶飞机和其他飞行装置或射弹的运动的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 联接到回收管线的触发机构可以启动提升装置以减少回收管线中的松弛。 耦合到回收管线的张紧装置可以吸收与飞机在回收管线上的冲击相关联的力。
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公开(公告)号：US6086015A
公开(公告)日：2000-07-11
申请号：US307016
申请日：1999-05-07
Applicant: Paul B. MacCready, Jr.
Inventor： Paul B. MacCready, Jr.
CPC classification number: B64C29/02 , B64C39/024 , B64D1/08 , B64D1/22 , B64C2201/048 , B64C2201/088 , B64C2201/104 , B64C2201/127 , B64C2201/128 , B64C2201/146 , B64C2201/165
Abstract: Apparatus for transporting a load between source and destination locations, comprising an aircraft having a body, power plant carried by the body to drive the aircraft both generally vertically and also generally horizontally, the aircraft also having a wing structure that has a leading edge remaining presented in the direction of flight; and load pick-up, carry and set-down means connected to the aircraft to elevate the load from the source location, transport the elevated and air-borne load generally horizontally, and set the load down at the destination location, the body and power plant configured for vertical flight mode to elevate and set down the load, and for generally horizontal flight mode to transport the elevated load generally horizontally below the level of the aircraft body.
Abstract translation: 用于在源和目的地之间运输负载的装置，包括具有主体的飞行器，由所述主体承载的动力装置，以大致垂直地并且大致水平地驱动飞行器，飞行器还具有保持呈现的前缘的翼结构 在飞行方向; 以及连接到飞机的负载拾取，携带和设置装置，以提高源头的负载，大体上水平地运输高空和空载负载，并将负载设置在目的地，机体和功率 配置用于垂直飞行模式的设备可提升和降低负载，并且大体上为水平飞行模式，以将升高的载荷大致水平地运送到飞机主体的水平面以下。
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公开(公告)号：US4478379A
公开(公告)日：1984-10-23
申请号：US545609
申请日：1983-10-27
Applicant: John P. Kerr
Inventor： John P. Kerr
CPC classification number: B64C27/10 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/048 , B64C2201/108 , B64C2201/146 , B64C2201/148 , B64C2201/165 , B64C2201/22
Abstract: An unmanned aircraft of the remotely piloted type that is characterized by its configuration and outline using rigid counter rotating propellers, positioned substantially at the height of its center of mass or slightly below to allow producing a sufficiently large control moment to use a tether line for landing the aircraft and to allow using two substantially spheroidal surfaces at the top and bottom respectively rather than a single one relatively larger and more detectable surface as when the propellers are at the top.
Abstract translation: 一种遥控飞行器类型的无人驾驶飞机的特点是其配置和轮廓使用刚性的反向旋转螺旋桨，其基本上位于其质心或稍低于其高度的高度，以便产生足够大的控制力矩以使用系绳进行着陆 并且允许在顶部和底部分别使用两个基本上球形的表面，而不是当螺旋桨在顶部时相对较大和更可检测的表面。
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公开(公告)号：US3669385A
公开(公告)日：1972-06-13
申请号：US3669385D
申请日：1970-10-08
Applicant: FAIRCHILD INDUSTRIES
Inventor： GLANTZ EARL , MCCOMAS JEAN W
CPC classification number: B64D5/00 , B64C1/00 , B64C39/024 , B64C2001/0045 , B64C2201/048 , B64C2201/104 , B64C2201/128 , B64C2201/146 , B64C2201/162 , B64C2201/167 , B64C2201/185
Abstract: An aircraft of improved of simplified construction having forward and aft generally cylindrical and substantially identical fuselage sections that are connected to a central fuselage section that houses an engine that has an inlet located above the forward fuselage section for powering the aircraft in flight. The central long axis of the aft fuselage section is located above the central long axis of the forward fuselage section. Wings are connected to the central fuselage section and a tail assembly is connected to the aft portion of the aft fuselage section. Many of the component parts of the aircraft are interchangeable and the aircraft is especially suited for use as a drone for towing aerial targets.
Abstract translation: 具有改进的简化结构的飞机具有前后大体上圆柱形和基本相同的机身部分，其连接到中央机身部分，该中央机身部分容纳具有位于前机身部分上方的入口的发动机，用于为飞行器提供动力。 后部机身部分的中心长轴位于前机身部分的中心长轴上方。 翼连接到中央机身部分，尾部组件连接到后机身部分的后部。 飞机的许多组成部分是可互换的，飞机特别适用于作为无人驾驶用于拖曳空中目标的飞机。
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Patent Agency Ranking
公开(公告)号：US2763447A
公开(公告)日：1956-09-18
申请号：US44894054
申请日：1954-08-10
Applicant: CARRAU MARIO J
Inventor： CARRAU MARIO J
CPC classification number: B64C39/024 , B64C2201/024 , B64C2201/046 , B64C2201/048 , B64C2201/108 , B64C2201/127 , B64C2201/146 , F42B15/08
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公开(公告)号：US20180281942A1
公开(公告)日：2018-10-04
申请号：US15544698
申请日：2015-11-19
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark W. Scott , Colin Kemater Bunting
CPC classification number: B64C29/02 , B64C25/04 , B64C2201/028 , B64C2201/048 , B64C2201/088 , B64D31/06
Abstract: A flying wing vertical take-off and landing (VTOL) aircraft is provided and includes an empennageless-fuselage from which foldable wings extend outwardly, an empennageless-nacelle supported on each of the wings and a rigid rotor propeller disposed on each empennageless-nacelle, each of the propellers being drivable to rotate about only a single rotational axis defined along a longitudinal axis of the corresponding empennageless-nacelle and being fully cyclically controllable.
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公开(公告)号：US20180037321A1
公开(公告)日：2018-02-08
申请号：US15670100
申请日：2017-08-07
Applicant: Christopher Wilkinson
Inventor： Christopher Wilkinson
CPC classification number: B64C39/024 , B64C2201/046 , B64C2201/048 , B64C2201/123 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/22 , F41H3/00 , F41H13/0012 , F41H13/0093 , G01S7/38
Abstract: A law enforcement drone system is provided. The system features an unmanned aerial vehicle, having a wireless transceiver, an airframe, a propulsion system, a navigation mechanism, a processor, a memory, a power source, and at least one fuel tank. The system also features a control system having a wireless transceiver, an input device, capable of receiving a user's input and converting the user's input to electrical signals, a processor, and a memory. The control system is in wireless communication with the vehicle such that the control system is capable of utilizing the propulsion system in substantially real-time.
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公开(公告)号：US09797309B2
公开(公告)日：2017-10-24
申请号：US13859424
申请日：2013-04-09
Applicant: David J. Podrog
Inventor： David J. Podrog
IPC: F02C1/05
CPC classification number: F02C1/05 , B64C2201/048 , F02G2254/90 , F05D2220/76 , Y02E30/00 , Y02T50/678 , Y02T70/5227
Abstract: A device powered by a method of heating a gas by directing X-rays at a mass of hafnium 178 to induce gamma rays. The gamma rays are directed at a heat exchanging apparatus, resulting in a stream of heated gas. This process powers a Hafnium gas turbine engine capable of providing shaft power or thrust to mechanical devices.
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公开(公告)号：US20170203839A1
公开(公告)日：2017-07-20
申请号：US15403818
申请日：2017-01-11
Applicant: Aurora Flight Sciences Corporation
Inventor： Francesco Giannini , Martin Gomez , Dan Cottrell , Jean-Charles Lede , Tom Roberts , Carl G. Schaefer, JR. , Dorian Colas , Brian Whipple , Tim Nuhfer , Herb Hunter , Jonathan Grohs , Steve Petullo
CPC classification number: B64C29/0033 , B64C3/385 , B64C5/04 , B64C5/16 , B64C39/024 , B64C39/12 , B64C2201/021 , B64C2201/042 , B64C2201/048 , B64D27/24 , B64D29/02 , B64D2027/026 , Y02T50/14 , Y02T50/44 , Y02T50/64
Abstract: A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.
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