公开(公告)号：US08408489B2

公开(公告)日：2013-04-02

申请号：US13466327

申请日：2012-05-08

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.

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：US08308106B2

公开(公告)日：2012-11-13

申请号：US13200466

申请日：2011-09-23

Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

IPC: B64D27/24 ,  B64D27/00

CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, 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 includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere.

Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。

公开(公告)号：US20110062278A1

公开(公告)日：2011-03-17

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: B64C3/38

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：US20110006151A1

公开(公告)日：2011-01-13

申请号：US12487907

申请日：2009-06-19

Applicant: Randal W. Beard

Inventor： Randal W. Beard

IPC: B64D3/00 ,  B64D17/00 ,  B64F1/02

CPC classification number: B64D3/00 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/182

Abstract: A method, apparatus, system, and computer system to facilitate aerial recovery of an air vehicle are disclosed. In various embodiments, a drogue is established in a drogue recovery orbit and an air vehicle is recovered with the drogue. Establishment of the drogue in a drogue recovery orbit may include establishment of a mothership in a mothership recovery orbit or actuating control surfaces on the drogue. Recovering the air vehicle may include maneuvering the drogue and the air vehicle in a cooperative manner to facilitate recovery of the air vehicle or utilizing a homing device on the drogue to guide the air vehicle. The various techniques disclosed may be modified to compensate for wind.

Abstract translation: 公开了一种促进空中交通工具空中恢复的方法，装置，系统和计算机系统。 在各种实施方案中，在锥套回收轨道中建立锥套，并且用锥套回收空气载体。 在潜艇恢复轨道上设置潜水员可能包括在母舰恢复轨道上建立母舰或在水手上启动控制面。 恢复飞行器车辆可以包括以合作的方式操纵锥套和空中飞行器，以便于空中交通工具的恢复，或利用锥套上的归位装置引导空中交通工具。 可以修改所公开的各种技术以补偿风。

公开(公告)号：US07841559B1

公开(公告)日：2010-11-30

申请号：US11707088

申请日：2007-02-16

Applicant: Hank O'Shea

Inventor： Hank O'Shea

IPC: B64C3/40

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

Abstract: Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.

公开(公告)号：US07798445B2

公开(公告)日：2010-09-21

申请号：US12020131

申请日：2008-01-25

Applicant: Stephen B. Heppe ,  Jaime Mack

Inventor： Stephen B. Heppe ,  Jaime Mack

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C2201/028 ,  B64C2201/182

Abstract: Systems and methods for recovering unmanned aircraft and controlling post-recovery motion of the aircraft are disclosed herein. An aircraft recovery system for recovering an unmanned aircraft in flight in accordance with one embodiment of the disclosure, for example, can include an inflatable aircraft recovery system having an inflatable portion with a generally vertical orientation. The inflatable portion can also include a landing pocket extending at least partially therethrough. The landing pocket is sized to receive at least a portion of a fuselage of the aircraft. The aircraft recovery system can also include a guidance system at least proximate to the landing pocket and positioned to guide the aircraft toward the landing pocket.

Abstract translation: 本文公开了用于恢复无人飞机并控制飞行器的恢复后运动的系统和方法。 例如，根据本公开的一个实施例，用于在飞行中恢复无人飞行器的飞行器恢复系统可以包括具有大致垂直取向的可充气部分的可充气飞行器回收系统。 可充气部分还可以包括至少部分地延伸穿过其中的着陆口袋。 登陆口袋的大小可以接收飞机的机身的至少一部分。 飞机恢复系统还可以包括至少靠近着陆口袋并定位成引导飞行器朝着着陆口袋的引导系统。

公开(公告)号：US20100123047A1

公开(公告)日：2010-05-20

申请号：US12271556

申请日：2008-11-14

Applicant: Jeffrey L. Williams

Inventor： Jeffrey L. Williams

IPC: B64C3/10 ,  B64C3/14

CPC classification number: B64C3/10 ,  A63H27/02 ,  A63H30/04 ,  B64C3/16 ,  B64C39/024 ,  B64C39/028 ,  B64C2039/105 ,  B64C2201/028

Abstract: A Blended Wing Body SUAV and MUAV is disclosed having a novel airfoil profile, wing configuration, rigging and tractor pull propeller placement that provide improved stability and safety characteristics over prior art SUAVs and MUAVs of comparable size and weight. This unique blended wing design includes wing twist on the outboard wing and an inverted “W” shaped planform to provide lateral and longitudinal stability, and smooth, even flight characteristics throughout the range of the expected flight envelope. These flight characteristics are crucial to providing a stable reconnaissance platform with favorable stall speeds, an increased payload and the ability to hand launch without the danger of exposing ones hands or wrist to a propeller.

Abstract translation: 混合翼体SUAV和MUAV被公开具有新颖的机翼轮廓，机翼构造，索具和拖拉机拉拔螺旋桨放置，其提供相当于相当尺寸和重量的现有技术的SUAV和MUAV的改进的稳定性和安全性。 这种独特的混合翼设计包括在外侧机翼上的机翼扭转和倒置的“W”形平台，以提供横向和纵向的稳定性，以及在预期飞行包线的整个范围内的平滑，均匀的飞行特性。 这些飞行特性对于提供稳定的侦察平台，具有良好的失速速度，增加的有效载荷和手动发射的能力，而不会将一只手或手腕暴露于螺旋桨的危险至关重要。

公开(公告)号：US07712702B2

公开(公告)日：2010-05-11

申请号：US11603810

申请日：2006-11-21

Applicant: Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

IPC: B64F1/06

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

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 includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

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，飞行器可以从包括沿发射导向装置移动的发射台的装置发射。 当滑架和/或发射引导件的部分相对于彼此移动时，托架可以加速。 由发射托架携带的夹具可以具有至少一个与飞行器接触的抓握部分，同时发射托架沿着发射轴加速。 当发射架减速时，至少一个把手部分可以与飞行器脱离接触，释放飞机起飞。 制动器可以在发射后阻止夹具的运动。

公开(公告)号：US20100025543A1

公开(公告)日：2010-02-04

申请号：US12262747

申请日：2008-10-31

Applicant: LLOYD E. KINSEY ,  Patrick Kranking

Inventor： LLOYD E. KINSEY ,  Patrick Kranking

IPC: B64C27/24

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

Abstract translation: 根据本发明的各个方面的用于变换航空器的方法和装置可以与被配置为围绕其纵向轴线旋转飞行器的发射系统一起操作。 枢转地连接到飞行器的提升表面可以被定位成使得飞行器的旋转导致提升表面在飞行器上产生提升力。 该升降机使得飞行器在提升表面旋转到第二位置之前陀螺地升高，使得飞行器从陀螺仪模式转换为固定翼型飞行器。 然后可以再次旋转提升表面，以允许飞行器作为自动陀螺仪着陆。

公开(公告)号：US20090218447A1

公开(公告)日：2009-09-03

申请号：US12390301

申请日：2009-02-20

Applicant: Andreas Hubertus von Flotow ,  Tyler Patrick Horton

Inventor： Andreas Hubertus von Flotow ,  Tyler Patrick Horton

IPC: B64C1/00

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。