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公开(公告)号：US09623967B2
公开(公告)日：2017-04-18
申请号：US14611271
申请日：2015-02-01
Applicant: Aero Machining, LLC
Inventor： Brad Mallard
CPC classification number: B64C29/0033 , B64C27/28 , B64C39/024 , B64C2201/042 , B64C2201/104 , B64C2201/108 , B64C2201/126 , B64C2201/146 , G01S19/13
Abstract: The invention is directed toward a UAV having a plurality of rotors position on axles extending longitudinally from a fuselage. The axles articulate the rotors from a vertical position, where the rotors provide lift, to a horizontal position, where the rotors provide thrust. The UAV is configured such that the voltage provided to each rotor may be varied to adjust rotor speed, and thus thrust, independently, giving the UAV enhanced maneuverability.
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公开(公告)号：US20170088253A1
公开(公告)日：2017-03-30
申请号：US15052558
申请日：2016-02-24
Applicant: David R. Williams , Jürgen Seidel
Inventor： David R. Williams , Jürgen Seidel
CPC classification number: B64C15/14 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/104 , B64D33/00
Abstract: An apparatus and method for controlling a yaw moment of a flight vehicle, such as an aircraft. A wing structure of the flight vehicle has a first opening or actuator positioned by a first apex section of a first side of the wing, and has a second opening or actuator positioned away from or at a distance from a second apex section of a second side of the wing. The first side and the second side can each be positioned or located opposite a centerline of the wing or wing structure. A pressure source or other pressure supply device is in communication with the first opening or actuator and the second opening or actuator to which a pressurized fluid, such as air, is controlled and delivered to control or vary the yaw moment of the flight vehicle.
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公开(公告)号：US20170029111A1
公开(公告)日：2017-02-02
申请号：US15264487
申请日：2016-09-13
Applicant: Astigan Limited
Inventor： Andrew Charles ELSON
CPC classification number: B64D5/00 , B64B1/40 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/066 , B64C2201/082 , B64C2201/104 , B64C2201/122 , B64C2201/123 , B64C2201/162 , B64C2201/187 , B64D2211/00
Abstract: An embodiment of an unmanned aerial vehicle, which may be connected to a lighter-than-air carrier, may have a ratio of a lifting force of the carrier to a weight of the vehicle from 1.1:1 to 3:1. The vehicle, excluding payload, may have a mass of from 30 kg to 150 kg. The vehicle may have a wingspan of from 20 m to 60 m.
Abstract translation: 可以连接到轻型承载人的无人驾驶飞行器的实施例可以具有从1.1:1到3:1的载体的提升力与车辆重量之比。 车辆（不包括有效载荷）的质量可能为30公斤至150公斤。 车辆可能具有20米至60米的翼展。
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公开(公告)号：US20170029091A1
公开(公告)日：2017-02-02
申请号：US14810109
申请日：2015-07-27
Applicant: JONATHON J. LINCH , KYLE M. RAHRIG
Inventor： JONATHON J. LINCH , KYLE M. RAHRIG
CPC classification number: B64C11/001 , B64C39/024 , B64C39/10 , B64C2039/105 , B64C2201/028 , B64C2201/104 , B64C2201/165
Abstract: A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. The ring shroud includes an inner ring surface and a radially spaced, oppositely facing outer ring surface. At least one propeller blade is fixedly attached to both the hub and the inner ring surface and extends radially therebetween for mutual rotation therewith. At least one extending blade has a first extending blade end radially spaced from a second extending blade end. The first extending blade end is fixedly attached to the outer ring surface. The second extending blade end is cantilevered from the first extending blade end and is radially spaced from the ring shroud.
Abstract translation: 螺旋桨包括同轴地围绕纵向轴线的轮毂。 环形护罩同轴地围绕纵向轴线并与轮毂径向间隔开。 环形护罩包括内环表面和径向间隔开的相对的外环表面。 至少一个螺旋桨叶片固定地附接到轮毂和内环表面并且在其间径向延伸以与其相互旋转。 至少一个延伸叶片具有与第二延伸叶片端部径向间隔开的第一延伸叶片端部。 第一延伸叶片端固定地附接到外环表面。 第二延伸叶片端部从第一延伸叶片端部悬臂并且与环形护罩径向间隔开。
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105.发明申请SITE MANAGEMENT SYSTEM, IN-FLIGHT DETECTION METHOD, AND NON-TRANSITORY COMPUTER READABLE MEDIUM STORING PROGRAM OF SITE MANAGEMENT SYSTEM 有权站点管理系统，飞行检测方法和非终端计算机可读介质存储程序的站点管理系统公开(公告)号：US20170001723A1
公开(公告)日：2017-01-05
申请号：US14860072
申请日：2015-09-21
Applicant: Kabushiki Kaisha TOPCON
Inventor： Atsushi Tanahashi
CPC classification number: B64C29/0033 , B64C39/024 , B64C2201/021 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/12 , B64C2201/123 , B64C2201/145 , B64D47/08 , E02F9/205 , E02F9/2054 , E02F9/262 , G05D1/0011 , G05D1/0027 , G05D1/0094 , G05D1/102 , G05D2201/0202 , G06K9/00637
Abstract: A site management system includes an unmanned airplane being switchable between an airplane mode for high speed flight and a VTOL mode for low speed flight, a working vehicle working in a civil construction site, a shape detection sensor provided in the unmanned airplane to detect a shape of the civil construction site, and an external control apparatus that controls flight of the unmanned airplane, driving of the working vehicle, and driving of the shape detection sensor. The external control apparatus moves the unmanned airplane to an observation area by performing the high speed flight. Further, the external control apparatus detects a shape of the observation area by driving the shape detection sensor while performing the high speed flight or by driving the shape detection sensor while performing low speed flight by switching from the airplane mode to the VTOL mode.
Abstract translation: 现场管理系统包括可在飞行高速飞行模式和低速飞行的垂直起降模式之间切换的无人驾驶飞机，在民用建筑工地工作的作业车辆，设置在无人驾驶飞机中以检测形状的形状检测传感器 以及控制无人驾驶飞行的驾驶，工作车辆的驾驶和形状检测传感器的驱动的外部控制装置。 外部控制装置通过执行高速飞行将无人驾驶飞机移动到观察区域。 此外，外部控制装置通过在执行高速飞行的同时驱动形状检测传感器或者通过从飞机模式切换到垂直起动模式来执行低速飞行来驱动形状检测传感器来检测观察区域的形状。
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Patent Agency Ranking
公开(公告)号：US20160311553A1
公开(公告)日：2016-10-27
申请号：US15070599
申请日：2016-03-15
Applicant: Sikorsky Aircraft Corporation
Inventor： Mark R. Alber , Charles Gayagoy , Jeffrey Parkhurst , Glenn D. Tiongson
IPC: B64D39/04 , B64C39/02 , B64C11/28 , B64D41/00 , B64C25/36 , B64C25/04 , B64D37/04 , B64C29/02 , B64C23/06
CPC classification number: B64D39/04 , B64C3/56 , B64C11/28 , B64C23/072 , B64C25/04 , B64C27/50 , B64C29/02 , B64C39/024 , B64C2201/028 , B64C2201/063 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64D7/00 , B64D37/04 , B64D37/16 , B64D39/00 , B64D41/00 , B64D2041/002 , Y02T50/164 , Y02T50/44
Abstract: An aircraft is provided and includes a fuselage, first and second wings extending outwardly from opposite sides of the fuselage, proprotors operably disposed on each of the first and second wings to drive vertical take-off and landing aircraft operations and horizontal flight aircraft operations and a refueling system including at least one fuel tank disposed in at least one or more of the fuselage, the first wing or the second wing and a refueling apparatus. The refueling apparatus is coupled to the at least one fuel tank such that fuel is movable with respect to the at least one fuel tank during aircraft ground and aerial operations.
Abstract translation: 提供飞机并且包括机身，从机身的相对侧向外延伸的第一和第二翼，可操作地设置在第一和第二翼中的每一个上的推进器，以驱动垂直起飞和着陆飞机操作和水平飞行飞行器操作，以及 加油系统，包括设置在机身，第一翼或第二翼中的至少一个或多个中的至少一个燃料箱和加油装置。 加油装置联接到至少一个燃料箱，使得燃料在飞机地面和空中操作期间相对于至少一个燃料箱可移动。
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公开(公告)号：US20160288918A1
公开(公告)日：2016-10-06
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.
Abstract translation: 电动飞机，包括飞行中可充电电动飞机，以及运行电动飞机的方法，包括通过使用独立于飞机和飞机附近飞行的无人驾驶飞行器（UAV）组件，在飞行中为电动飞机充电的方法。
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公开(公告)号：US20160272312A1
公开(公告)日：2016-09-22
申请号：US14611271
申请日：2015-02-01
Applicant: Aero Machining, LLC
Inventor： Brad Mallard
CPC classification number: B64C29/0033 , B64C27/28 , B64C39/024 , B64C2201/042 , B64C2201/104 , B64C2201/108 , B64C2201/126 , B64C2201/146 , G01S19/13
Abstract: The invention is directed toward a UAV having a plurality of rotors position on axles extending longitudinally from a fuselage. The axles articulate the rotors from a vertical position, where the rotors provide lift, to a horizontal position, where the rotors provide thrust. The UAV is configured such that the voltage provided to each rotor may be varied to adjust rotor speed, and thus thrust, independently, giving the UAV enhanced maneuverability.
Abstract translation: 本发明涉及一种具有从机身纵向延伸的轴上的多个转子的UAV。 轴从垂直位置将转子铰接到转子提供电梯的水平位置，转子提供推力。 UAV被配置成使得提供给每个转子的电压可以改变以调节转子速度，并且因此独立地推动给予UAV增强的机动性。
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公开(公告)号：US20160244160A1
公开(公告)日：2016-08-25
申请号：US14454200
申请日：2014-08-07
Applicant: FourthWing Sensors, LLC
Inventor： Todd Michael Colten , Christopher Scott Gibson , Ryan Nelson , Adem Rudin
CPC classification number: B64C39/024 , B60F5/02 , B64C2201/027 , B64C2201/042 , B64C2201/104 , B64C2201/108 , B64C2201/125 , B64C2201/126 , B64C2201/141 , B64C2201/146 , B64C2211/00
Abstract: In one example, an unmanned aerial vehicle includes a fuselage and a lift assembly. The lift assembly is selected from a plurality of lift assemblies, each of the plurality of lift assemblies having a different flight modality. The fuselage includes a mounting portion configured to mount with any of the plurality of lift assemblies.
Abstract translation: 在一个示例中，无人驾驶飞行器包括机身和升降组件。 电梯组件选自多个提升组件，多个提升组件中的每一个具有不同的飞行模态。 机身包括安装部分，该安装部分构造成与多个提升组件中的任一个安装。
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110.发明申请CONVERTIPLANE WITH NEW AERODYNAMIC AND TECHNICAL SOLUTIONS WHICH MAKE THEAIRCRAFT SAFE AND USABLE 有权具有新的航空和技术解决方案，使安全可靠的安全公开(公告)号：US20160167780A1
公开(公告)日：2016-06-16
申请号：US14908850
申请日：2014-08-07
Applicant: UNIT 1SRL
Inventor： Pietro GIOVENGA
CPC classification number: B64C29/0033 , B64C3/385 , B64C3/54 , B64C39/024 , B64C2201/021 , B64C2201/104 , B64C2201/108 , B64C2201/162 , B64D27/08 , Y02T50/14
Abstract: A convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft includes a variable incidence front wing of variable span located below the fuselage and mounted on a structure in the form of a venturi tube, a rear wing having two propellers for controlling the stability of the vehicle in pitch and roll installed therein, two counter-rotating, pivotally mounted ducted propellers equipped with four flaps orthogonal to each other provided on the sides of the cockpit, engines placed behind the cockpit close to the center of gravity, a static balancing system for controlling the center of gravity of the aircraft consisting of a weight placed in the lower part of the fuselage, self-propelled on the track rack longitudinally to the fuselage, and a digital flight control system.
Abstract translation: 转换飞机具有像直升机一样起飞的能力，然后像常规飞机一样水平飞行。 飞机包括位于机身下方的可变跨度的可变入射前翼，并安装在文丘里管形式的结构上，后翼具有两个螺旋桨，用于控制安装在其中的俯仰和滚动中的车辆的稳定性，两个计数器 旋转的，枢转安装的管道螺旋桨，其配备有四个彼此正交的翼片，设置在驾驶舱的两侧，放置在靠近重心的驾驶舱后面的发动机，用于控制飞行器重心的静态平衡系统， 放置在机身下部的重量，纵向自动推进到机身，以及数字飞行控制系统。
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