公开(公告)号：US07377470B2

公开(公告)日：2008-05-27

申请号：US11252185

申请日：2005-10-18

Applicant: Haru Miyake

Inventor： Haru Miyake

IPC: B64C13/20

CPC classification number: B64C13/20 ,  A63H27/007 ,  A63H27/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

Abstract translation: 无线控制飞机包括飞行单元和地面控制器，其通过通信部分连接到飞行单元并飞行飞行单元。 飞行单元包括主体，安装在主体上的驱动部分，当由驱动部驱动时产生推进力的推进装置，包括多个翼元件的主翼，其安装成能够与 相对于彼此相对的改变主翼的有效面积而改变翼元件的相对位置的开闭机构，以及选择性地保持和降低载荷的下落装置。 通过改变主翼的有效面积，可以改变飞行速度，因此可以减小用于旋转推进装置的驱动部的容量和尺寸。

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：US07331546B2

公开(公告)日：2008-02-19

申请号：US11510013

申请日：2006-08-25

Applicant: Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn J. Mitryk ,  Frank J. Boria ,  Mujahid Abdulrahim

Inventor： Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn J. Mitryk ,  Frank J. Boria ,  Mujahid Abdulrahim

IPC: B64C3/56

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过从管中简单地释放微型飞行器而从管展开。

公开(公告)号：US20080006743A1

公开(公告)日：2008-01-10

申请号：US11428706

申请日：2006-07-05

Applicant: Gerald D. Miller ,  Wesley Moore ,  Adrian Viisoreanu ,  Russell W. Morris ,  Ronald W. Davidson ,  Shailesh Atreya ,  Albert D. Olsen ,  William Bigbee-Hansen

Inventor： Gerald D. Miller ,  Wesley Moore ,  Adrian Viisoreanu ,  Russell W. Morris ,  Ronald W. Davidson ,  Shailesh Atreya ,  Albert D. Olsen ,  William Bigbee-Hansen

IPC: B64D33/00

CPC classification number: B64D37/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/127 ,  B64C2201/165 ,  Y02T10/16 ,  Y02T50/44 ,  Y02T90/44

Abstract: Hydrogen powered air vehicles that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 60,000 ft carrying payloads of up to 2,000 pounds. Embodiments may include features such as large wingspan relative to fuselage and an all composite or partial composite structure for light weight and strength. The aircraft of the invention use one or more internal combustion engines adapted for hydrogen combustion, each engine driving propellers. The hydrogen fuel is stored on board in containers, located within the fuselage, as a cryogenic liquid, and is vaporized in a heat exchanger before delivery to the internal combustion engine.

Abstract translation: 在一些实施例中的氢动力空中飞行器可以在高达60,000英尺的高度上以非常长的耐久性（10或更多天）飞行，承载高达2,000磅的有效载荷。 实施例可以包括相对于机身的大翼展以及用于轻量化和强度的全复合或部分复合结构的特征。 本发明的飞机使用一个或多个适于氢燃烧的内燃机，每个发动机都驱动螺旋桨。 氢燃料被储存在位于机身内的容器中，作为低温液体，并且在输送到内燃机之前在热交换器中蒸发。

公开(公告)号：US20070108345A1

公开(公告)日：2007-05-17

申请号：US11510920

申请日：2006-08-28

Applicant: William McDonnell

Inventor： William McDonnell

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将无人机（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

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.

公开(公告)号：US20070063096A1

公开(公告)日：2007-03-22

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: B64C39/02

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，其锥形形状变窄为其前端具有遮光角度的叶片尖端，具有无风翼型的空气动力学表面的飞翼型，低侧面 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：US07182297B2

公开(公告)日：2007-02-27

申请号：US10758294

申请日：2004-01-15

Applicant: Clifford Jackson

Inventor： Clifford Jackson

IPC: B64C13/28

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165

Abstract: Methods and apparatuses for supporting aircraft components, including actuators are disclosed. An apparatus in accordance with one embodiment of the invention includes an actuator housing having an actuator receptacle that securely yet releasably receives an actuator. The actuator receptacle can include conformal walls that conform at least in part to the shape of the actuator and can accordingly squeeze the actuator and properly align the actuator. At least one of the actuator walls can further include a projection that is releasably received in a corresponding recess of the actuator. One of both of these features can releasably secure the actuator relative to the aircraft, reducing and/or eliminating the likelihood that the actuator will be misaligned and/or mispositioned relative to the aircraft during installation and/or replacement.

Abstract translation: 公开了用于支持飞机部件（包括致动器）的方法和装置。 根据本发明的一个实施例的装置包括具有可靠地可释放地接收致动器的致动器插座的致动器壳体。 致动器容器可以包括至少部分地符合致动器的形状的适形壁，并且可以相应地挤压致动器并且正确对准致动器。 致动器壁中的至少一个还可以包括可释放地容纳在致动器的相应凹部中的突起。 这两个特征之一可以相对于飞行器可释放地固定致动器，减少和/或消除在安装和/或更换期间致动器相对于飞行器不对准和/或错位的可能性。

公开(公告)号：US07128294B2

公开(公告)日：2006-10-31

申请号：US10760150

申请日：2004-01-16

Applicant: Cory Roeseler ,  Andreas H. von Flotow

Inventor： Cory Roeseler ,  Andreas H. von Flotow

IPC: B64C3/56

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。