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。

公开(公告)号：US07357352B2

公开(公告)日：2008-04-15

申请号：US11270342

申请日：2005-11-09

Applicant: Thomas E. Speer ,  Richard D. Jones

Inventor： Thomas E. Speer ,  Richard D. Jones

IPC: B64C37/02 ,  B64D5/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2201/165 ,  B64D5/00

Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

Abstract translation: 提供了一种用于发射空中车辆组件的机动车组件和相应的方法，以及相应的控制系统和方法。 空中车辆组件可以包括在飞行的一部分期间例如在起飞和着陆期间可释放地彼此连接的多个空中飞行器。 通过可释放地彼此接合，例如在起飞和着陆期间，空中车辆可以在垂直起飞和着陆期间依靠和协助彼此，同时被设计成在过渡到 同时保持与其他空中客车分离的距离或距离。 通过考虑其他机动车辆的状态，控制系统和方法还允许机动车组件的空中车辆协作。

公开(公告)号：US20070228212A1

公开(公告)日：2007-10-04

申请号：US11394018

申请日：2006-03-30

Applicant: Peter Ifju ,  Bret Stanford ,  Roberto Albertani

Inventor： Peter Ifju ,  Bret Stanford ,  Roberto Albertani

IPC: B64C3/14

CPC classification number: B64C3/18 ,  B64C3/42 ,  B64C3/44 ,  B64C3/52 ,  B64C39/028 ,  B64C2201/028 ,  Y02T50/14

Abstract: An airfoil for a micro air vehicle that includes components enabling the airfoil to adjust the angle of attack (AOA) of the airfoil in response to wind gusts, thereby enabling the airfoil to provide smooth flight. The airfoil may include a first compliant region positioned between an inboard section and a first outboard section and may include a second compliant region between a second outboard section and the inboard section. The compliant regions enable the first and second outboard sections to bend about a leading edge section and move relative to an inboard section. This action creates smoother flight due to numerous aerodynamic advantages such as a change in the angle of attack and improved wind gust rejection due to adaptive washout as a result of the airfoil flexing, twisting and decambering.

Abstract translation: 一种用于微型飞行器的翼型件，其包括能够使翼型件响应于阵风而调节翼型的迎角（AOA）的部件，从而使翼型件能够提供平稳的飞行。 翼型件可以包括位于内侧部分和第一外侧部分之间的第一顺应性区域，并且可以包括第二外侧部分和内侧部分之间的第二顺应区域。 顺从区域使得第一和第二外侧部分能够围绕前缘部分弯曲并相对于内侧部分移动。 由于翼型的弯曲，扭转和回旋的结果，由于许多空气动力学优点，例如迎角的变化和改善的阵风排除，由于适应性冲洗，这种动作产生更平滑的飞行。

公开(公告)号：US20070102565A1

公开(公告)日：2007-05-10

申请号：US11270342

申请日：2005-11-09

Applicant: Thomas Speer ,  Richard Jones

Inventor： Thomas Speer ,  Richard Jones

IPC: B64C29/00 ,  B64C37/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2201/165 ,  B64D5/00

Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

Abstract translation: 提供了一种用于发射空中车辆组件的机动车组件和相应的方法，以及相应的控制系统和方法。 空中车辆组件可以包括在飞行的一部分期间例如在起飞和着陆期间可释放地彼此连接的多个空中飞行器。 通过可释放地彼此接合，例如在起飞和着陆期间，空中车辆可以在垂直起飞和着陆期间依靠和协助彼此，同时被设计成在过渡到 同时保持与其他空中客车分离的距离或距离。 通过考虑其他机动车辆的状态，控制系统和方法还允许机动车组件的空中车辆协作。

公开(公告)号：US20070075185A1

公开(公告)日：2007-04-05

申请号：US11603810

申请日：2006-11-21

Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

IPC: B64F1/04

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.