公开(公告)号：US08366055B2

公开(公告)日：2013-02-05

申请号：US12818826

申请日：2010-06-18

Applicant: Evan R. Ulrich ,  Darryll J. Pines ,  Joseph Park ,  Steven Gerardi

Inventor： Evan R. Ulrich ,  Darryll J. Pines ,  Joseph Park ,  Steven Gerardi

IPC: B64C27/00 ,  B64C27/06 ,  B64C27/57

CPC classification number: B64C27/00 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/028

Abstract: Micro/nano mono-wing aircraft with the wing configured as a winged seed (Samara) is uniquely suited for autonomous or remotely controlled operation in confined environments for surrounding images acquisition. The aircraft is capable of effective autorotation and steady hovering. The wing is flexibly connected to a fuselage via a servo-mechanism which is controlled to change the wing's orientation to control the flight trajectory and characteristics. A propeller on the fuselage rotates about the axis oriented to oppose a torque created about the longitudinal axis of the fuselage and is controlled to contribute in the aircraft maneuvers. A controller, either ON-board or OFF-board, creates input command signals to control the operation of the aircraft based on a linear control model identified as a result of extensive experimentations with a number of models.

Abstract translation: 具有配置为翼状种子（Samara）的翼的微/纳单翼飞机特别适用于围绕图像采集的有限环境中的自主或远程控制操作。 该飞机能够有效的自转和稳定的悬停。 机翼通过伺服机构灵活地连接到机身，伺服机构被控制以改变机翼的方向以控制飞行轨迹和特性。 机身上的推进器围绕轴线旋转，以抵抗围绕机身的纵向轴线产生的扭矩，并被控制以在飞机机动中作出贡献。 控制器，无论是板载还是板外，都会创建输入命令信号，以便根据多个模型的广泛实验确定的线性控制模型来控制飞机的运行。

公开(公告)号：US08328131B2

公开(公告)日：2012-12-11

申请号：US13466343

申请日：2012-05-08

Applicant: Harry George Dennis Gosling

Inventor： Harry George Dennis Gosling

IPC: B64C39/06

CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis.

Abstract translation: 一种机载车辆，其具有限定翼体轴线的翼体，并且当沿翼体轴线观察时呈现大致环形，所述环形空间的内部限定在两端敞开的管道。 提供了包括一对或多对推进装置的推进系统，每对推进装置包括安装到翼体上并定位在包括翼体轴线的平面的第一侧上的第一推进装置，以及安装到 翼体并且定位在包括翼体轴线的平面的第二侧上。

公开(公告)号：US20120290164A1

公开(公告)日：2012-11-15

申请号：US13470866

申请日：2012-05-14

Applicant: Bruce Hanson ,  Mark Everly

Inventor： Bruce Hanson ,  Mark Everly

IPC: G05D1/00

CPC classification number: B60F5/00 ,  B63B1/042 ,  B63B1/322 ,  B63B2001/206 ,  B63B2035/006 ,  B63B2035/007 ,  B63G8/22 ,  B63G8/26 ,  B63G2008/002 ,  B63G2008/004 ,  B64C35/00 ,  B64C39/024 ,  B64C2201/028 ,  Y02T70/12

Abstract: An unmanned vehicle may include a vehicle body that comprises an enclosed hull. The unmanned vehicle may include a propulsion, a ballast control system, a center of gravity system, a pressurization system, a control surface system, a navigation control system, and an on board master control system. The on board master control system may execute local control over operation of the various systems of the unmanned vehicle. The unmanned vehicle may also include a power supply carried by a portion of the vehicle body to provide power to the various systems. The various systems of the unmanned vehicle may be independently operable to support selective operation of the unmanned vehicle in the air, on the surface of the water, and below the surface of the water.

Abstract translation: 无人驾驶车辆可以包括包括封闭船体的车体。 无人驾驶车辆可以包括推进，镇流器控制系统，重心系统，加压系统，控制面系统，导航控制系统和车载主控制系统。 车载主控制系统可以执行对无人驾驶车辆的各种系统的操作的本地控制。 无人驾驶车辆还可以包括由车身的一部分承载的电力供应给各种系统。 无人驾驶车辆的各种系统可以独立地可操作以支持无人驾驶车辆在空气中，水面上以及水面以下的选择性操作。

公开(公告)号：US08262016B2

公开(公告)日：2012-09-11

申请号：US12594719

申请日：2008-04-16

Applicant: Harry George Dennis Gosling

Inventor： Harry George Dennis Gosling

IPC: B64C15/00

CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis. A direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device and/or a magnitude of thrust of the first propulsion device can be adjusted independently of the magnitude of thrust of the second propulsion device. In certain embodiments the wing-body appears swept forward when viewed from a first viewing angle, and swept backward when viewed from a second viewing position at right angles to the first viewing angle.

Abstract translation: 一种机载车辆，其具有限定翼体轴线的翼体，并且当沿翼体轴线观察时呈现大致环形，所述环形空间的内部限定在两端敞开的管道。 提供了包括一对或多对推进装置的推进系统，每对推进装置包括安装到翼体上并定位在包括翼体轴线的平面的第一侧上的第一推进装置，以及安装到 翼体并且定位在包括翼体轴线的平面的第二侧上。 可以独立于第二推进装置的推力方向来调节第一推进装置的推力方向，和/或可以独立于第二推进装置的推力的大小来调节第一推进装置的推力的大小。 在某些实施例中，当从第一视角观察时，翼体呈向前扫掠，并且当从与第一视角成直角的第二观察位置观看时向后扫掠。

公开(公告)号：US20120104169A1

公开(公告)日：2012-05-03

申请号：US13347624

申请日：2012-01-10

Applicant: Andreas Hubertus von Flotow ,  Tyler Patrick Horton

Inventor： Andreas Hubertus von Flotow ,  Tyler Patrick Horton

IPC: B64C1/00 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/165

Abstract: Vibration isolation devices and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first fuselage section. The aircraft can also include at least one vibration isolation device coupling the first fuselage section to the second fuselage section. The vibration isolation device is translationally stiffer along a longitudinal axis than it is along a lateral and a vertical axis, and rotationally stiffer about a pitch and a yaw axis than it is about a roll axis.

Abstract translation: 本文公开了隔振装置及相关系统和方法。 在一个实施例中，例如，无人飞行器可以包括具有第一机身部分的机身和与第一机身部分相邻并且至少大致纵向对齐的第二机身部分。 飞机还可以包括将第一机身部分连接到第二机身部分的至少一个隔振装置。 振动隔离装置沿着纵向轴线比沿着横向轴线和垂直轴线平移地更硬，并且围绕俯仰轴线和偏转轴线相对于绕轴线旋转更硬。

公开(公告)号：US08123160B2

公开(公告)日：2012-02-28

申请号：US10573570

申请日：2004-07-22

Applicant: Michael Shepshelovich ,  Mario Sletean ,  Moshe Steinbuch ,  David Eli Levy

Inventor： Michael Shepshelovich ,  Mario Sletean ,  Moshe Steinbuch ,  David Eli Levy

IPC: B64C39/12

CPC classification number: B64D15/163 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/165

Abstract: An aircraft arrangement for Mini or Micro UAV comprising a fore wing (14) and an aft wing (12) in tandem closed-coupled arrangement. The aft wing (12) has side panels (18) and control surfaces (19), and tapered planform with positive sweep, while the fore wing (14) has non-positive trailing edge sweep. The fore wing (14) and the aft wing (12) are disposed at different height, and the aircraft arrangement has no other wings or tail arrangements.

Abstract translation: 一种用于迷你或微型无人机的飞行器装置，其包括串联闭合联接装置的前翼（14）和后翼（12）。 后翼（12）具有侧板（18）和控制表面（19），并且具有正扫掠的锥形平面，而前翼（14）具有非正的后缘扫掠。 前翼（14）和后翼（12）设置在不同的高度，并且飞行器装置没有其他翼或尾翼装置。

公开(公告)号：US07980510B2

公开(公告)日：2011-07-19

申请号：US10569653

申请日：2004-05-12

Applicant: Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

Inventor： Yasutada Tanabe ,  Chiharu Totsuka ,  Takeshi Akasaka ,  Masato Okamoto

IPC: B64C11/46 ,  B64D27/00 ,  B64D33/00

CPC classification number: A63H27/02 ,  B64C39/028 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  Y10S244/903

Abstract: A small unmanned airplane includes; a main wing having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers placed at blade tips of left and right of the main wing; and two propellers installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

Abstract translation: 一架小型无人机包括 主翼具有下表面近似平坦的弧形翼型，其锥形形状变窄到其前端具有遮光角度的叶片尖端，其具有无风翼型的空气动力学表面的飞翼型，并且是低方位 比; 在主翼的左右两侧的后缘部分中大致极宽的可动翼片至少在水平飞行中具有二面角; 放置在主翼左右叶片尖端的垂直稳定器; 并安装在主翼顶面的两个螺旋桨。 这可以实现小型化和轻量化的小型无人驾驶飞机的个人承载能力和适合性，例如用手抛出。

公开(公告)号：US20100252690A1

公开(公告)日：2010-10-07

申请号：US12740005

申请日：2008-11-20

Applicant: Inderpal Singh Hothi ,  Jon Robert Stoackley ,  Steven John Stoackley

Inventor： Inderpal Singh Hothi ,  Jon Robert Stoackley ,  Steven John Stoackley

IPC: B64C29/02 ,  B64C19/00

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088

Abstract: An unmanned aerial vehicle (UAV) in the form of a “tail sitter” flying wing adapted for vertical take off and landing and transitions between flight as a helicopter and wing-borne flight. The vehicle is electrically powered from onboard batteries and equipped with rotors on miniature helicopter rotor heads at the tips of the wing for both lift, during take off and landing, and forward thrust. In planform the wing comprises, to each side of its longitudinal axis, an inner section with swept back leading and trailing edges, and an outer section with a leading edge more perpendicular to the longitudinal axis, being only mildly swept back or substantially unswept, and a swept forward trailing edge.

Abstract translation: 一种无人机（UAV），以“尾巴”飞翼的形式适用于垂直起飞和着陆，并且作为直升机和机翼飞行之间的飞行之间的过渡。 车辆由车载电池供电，并在机翼顶部的微型直升机转子头上配备转子，用于升降机，起飞和着陆期间以及向前推力。 在平面图中，翼片在其纵向轴线的每一侧包括具有扫掠的前缘和后缘的内部部分，并且具有更垂直于纵向轴线的前缘的外部部分仅被轻度地扫掠或基本上不被刮除，以及 前沿后缘。

公开(公告)号：US20090134273A1

公开(公告)日：2009-05-28

申请号：US11064287

申请日：2005-02-22

Applicant: Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

Inventor： Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

IPC: B64C1/00 ,  B28B5/00 ,  B64F1/04

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/165 ,  B64C2201/201

Abstract: An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container. In a second configuration, a launch assembly is provided, that includes an elastic tether connecting a UAV to an accelerated mass for gentle acceleration to flight speed under a stable tow.

Abstract translation: 提供无人驾驶飞行器（UAV），使用和制造具有成本效益，并且包括低数量的部件，允许任务规划人员以一次性方式使用无人机。 无人机包括具有中心体的机身和从中心体延伸的翼，限定内腔。 机身包括一个上部和下部壳体，每个都由整体塑料构成。 上壳体和下壳体之间具有限定了堆叠构造的燃料箱和有效载荷的壁。 机身还可以包括配置成包围有效载荷舱并有助于机身的中心体的有效载荷盖。 还提供发射组件。 在第一配置中，提供了一种发射组件，其包括用于容纳多个UAV的容器和启动无人机从容器的快速喷射的展开机构。 在第二构造中，提供了一种发射组件，其包括将UAV连接到加速质量块的弹性系绳，以在稳定的丝束下平缓加速到飞行速度。

公开(公告)号：US20090032648A1

公开(公告)日：2009-02-05

申请号：US12058520

申请日：2008-03-28

Applicant: Jerome Pearson

Inventor： Jerome Pearson

IPC: B64D27/02

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102

Abstract: A long endurance powered aircraft includes a fuselage, a propeller coupled to the fuselage, a wing coupled to the fuselage, and an energy storage system disposed within the fuselage. The wing includes an adjustable surface area including solar cells configured to collect incident solar energy and convert the collected incident solar energy to electrical energy for powering the aircraft during daylight flight. The energy storage system is configured to convert excess electrical energy converted from collected incident solar energy to chemical energy, store the chemical energy, and convert the stored chemical energy to electrical energy for powering the aircraft during night flight.

Abstract translation: 长寿命动力飞机包括机身，与机身相连的螺旋桨，与机身相连的机翼，以及设置在机身内的能量存储系统。 机翼包括可调节的表面区域，包括被配置为收集入射的太阳能并且将收集的入射太阳能转换成电能的太阳能电池，以在日间飞行期间为飞机供电。 能量存储系统被配置为将从收集的入射太阳能转换的过量电能转换成化学能，存储化学能，并将存储的化学能转换成电能，以在夜间飞行期间为飞行器供电。