公开(公告)号：US06676084B2

公开(公告)日：2004-01-13

申请号：US10168588

申请日：2002-06-24

Applicant: Jean Asseline ,  George De Noni

Inventor： Jean Asseline ,  George De Noni

IPC: B64D1734

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: A small radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, the device being capable of short take-off and landing and flying at maximum speed of 35 Km/h. The device includes a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6). The base is a welded one-piece element that includes the engine, the airscrew, a tank and the radio control. The apex is a welded one-piece element. The lower plane and the two lateral planes include spars (11, 12) assembled at the base and as the apex. The lower plane includes at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires. The wings (13) are a caisson-type supple parachute and are connected to the pod in an adjustable fashion by two front slings (17), two braking slings (18) acting on the two flaps/ailerons.

Abstract translation: 由具有推进式螺旋桨（19）的热力发动机（20）推进的用于遥感的小型无线电控制飞行装置，该装置能够以35Km / h的最大速度短时起飞和着陆并飞行。 该装置包括荚和翼，荚（1）是刚性三轮车，可通过基本上棱锥形的夹具与后基部（2）和前顶点（7），下平面（3），两个侧平面（4， 5）和上平面（6）。 底座是焊接的单件元件，包括发动机，螺旋桨，油箱和无线电控制。 顶点是焊接的单件元件。 下平面和两个横向平面包括组装在基部和顶点的翼梁（11,12）。 下平面在其三个端角处包括两个后轮（8）和前轮（9），前轮设置成朝向顶点的前部突出，并且轮是低压轮胎。 机翼（13）是沉箱式柔软的降落伞，并且通过两个前吊索（17）和作用在两个翼片/副翼上的两个制动吊索（18）以可调节的方式连接到吊舱。

公开(公告)号：US20030141409A1

公开(公告)日：2003-07-31

申请号：US10310415

申请日：2002-12-05

Inventor： Derek L. Lisoski ,  Greg T. Kendall

IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.

Abstract translation: 太阳能可再充电，长时间，跨度的飞翼，没有机身或方向舵。 拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差速推力来转弯，俯仰和偏航。 机翼构造成在飞行载荷下变形以定位螺旋桨，使得可以实现控制。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。

公开(公告)号：US20030066932A1

公开(公告)日：2003-04-10

申请号：US10255186

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: B64C001/00

CPC classification number: B64C39/028 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  F02D2200/703

Abstract: A miniature, unmanned aircraft having interchangeable data handling modules, such as sensors for obtaining digital aerial imagery and other data, and radio transmitters and receivers for relaying data. The aircraft has a microprocessor for managing flight, remote control guidance system, and electrical supply system. The data handling modules have an aerodynamic housing and manual fasteners enabling ready installation and removal. One or more data acquiring sensors or data transferring apparatus and support equipment such as batteries and communications and power cables are contained within the module. A plurality of different modules are preferably provided. Each module, when attached in a preferred location below the wing, does not significantly alter the center of gravity of the airframe. Preferably, each module contains the supervisory microprocessor so that the microprocessor need not be part of the airframe.

Abstract translation: 具有可互换数据处理模块的微型无人飞机，例如用于获得数字航空图像和其他数据的传感器，以及用于中继数据的无线电发射机和接收机。 飞机有一个用于管理飞行，遥控引导系统和电力供应系统的微处理器。 数据处理模块具有空气动力学外壳和手动紧固件，可以实现安装和拆卸。 模块内包含一个或多个数据采集传感器或数据传输设备以及诸如电池和通信和电力电缆的支持设备。 优选地提供多个不同的模块。 当每个模块安装在机翼下方的首选位置时，不会显着改变机身的重心。 优选地，每个模块包含管理微处理器，使得微处理器不需要是机身的一部分。

公开(公告)号：US20030060944A1

公开(公告)日：2003-03-27

申请号：US10255187

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: G06F017/00

CPC classification number: F02D41/2406 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  F02B75/34 ,  F02D35/0069 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  G05D1/101

Abstract: A power and communications connection arrangement for a miniature, unmanned aircraft having data handling capability. The aircraft has a microprocessor for managing flight control, a GPS receiver, a communications radio frequency transceiver, and data handling apparatus. The latter may be any of a sensor for gathering environmental data, sensing aircraft altitude or attitude, a data relay station, or any combination of these. The data handling apparatus is part of a removable module mounted to and detachable from the aircraft. The connection arrangement includes stationary power and communications terminals fixed to the module, and corresponding free power and data cables completing respective power circuits and communications links within the aircraft. In the preferred embodiment, the microprocessor, at least one sensor, and a battery pack are located in the module, and a radio transceiver, a GPS receiver, controls such as rudder and elevator, and other sensors are located in the airframe.

公开(公告)号：US20030057325A1

公开(公告)日：2003-03-27

申请号：US10255182

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: B64C001/00

CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  F02B75/34

Abstract: A method of shipping a disassembled miniature, unmanned aircraft capable of handling data, the aircraft having remote guidance, an onboard microprocessor for managing flight, wing area of at least eight hundred square inches, a wingspan of at least eight feet, and weighing under fifty-five pounds. The aircraft includes a data handling module. The aircraft is disassembled into separate components including at a minimum the wing, the fuselage, and the data handling module. The fuselage and possibly other lesser components are packed in a first shipping container. The wing is packed in a second shipping container. The data handling module is packed in a third shipping container. The first and second containers are shipped by overnight courier, while the third container is either shipped the same way or alternatively travels as unchecked luggage aboard a commercial airliner.

Abstract translation: 运送能够处理数据的分解的微型无人飞机，具有远程引导的飞行器，用于管理飞行的机载微处理器，至少八百平方英寸的机翼面积，至少八英尺的翼展，并且重量在五十 - 英镑 飞机包括一个数据处理模块。 飞机被拆卸成单独的部件，包括至少机翼，机身和数据处理模块。 机身和可能的其他较小的部件被包装在第一运输容器中。 机翼包装在第二个运输集装箱。 数据处理模块包装在第三个运输容器中。 第一个和第二个集装箱是通过隔夜快递运送的，而第三个集装箱运输方式相同，或者作为一个商业客机上的未检查行李。

公开(公告)号：US06431494B1

公开(公告)日：2002-08-13

申请号：US09907006

申请日：2001-07-17

Applicant: W. Douglas Kinkead ,  Mark W. Scott

Inventor： W. Douglas Kinkead ,  Mark W. Scott

IPC: B64C1316

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/165

Abstract: A flight control system includes a blending algorithm which evaluates the current flight regime and determines the effectiveness of the flight controls to effect the rotational moment of a hybrid vehicle about the roll axis. Gain schedules for both roll cyclic and aileron control provide a quantitative measure of control effectiveness. Based on the respective gain schedules, the algorithm determines how much of the control commands should be sent to each control surface. The result is that for a given control command, the same amount of roll moment will be generated regardless of flight regime. This simplifies the underlying flight control law since the commands it generates are correct regardless of flight regime.

Abstract translation: 飞行控制系统包括混合算法，其评估当前飞行状态并且确定飞行控制器实现混合动力车辆围绕滚动轴线的旋转力矩的有效性。 滚动循环和副翼控制的增益计划提供了控制有效性的定量测量。 基于相应的增益计划，该算法确定应将多少控制命令发送到每个控制表面。 结果是对于给定的控制命令，不管飞行情况如何，将产生相同的滚动时刻。 这简化了潜在的飞行控制规则，因为它产生的命令是正确的，无论飞行情况如何。

公开(公告)号：US5918832A

公开(公告)日：1999-07-06

申请号：US818582

申请日：1997-03-14

Applicant: Siegfried Hermann Zerweckh

Inventor： Siegfried Hermann Zerweckh

IPC: B64C3/38 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C3/38 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  Y02T50/145

Abstract: An air vehicle defining a plane of symmetry includes a pair of outboard panels which are rotatably mounted on the lifting body of the vehicle and respectively extend in opposite directions from the plane of symmetry. A control system collectively rotates the outboard panels to selectively contribute forces from the panels to the lift on the air vehicle. The control system also differentially rotates the outboard panels to control roll of the air vehicle. A pair of empennage panels are also rotatably mounted on the lifting body to establish a dihedral angle centered on the plane of symmetry. The control system collectively rotates these empennage panels to control pitch, and differentially rotates the empennage panels to control yaw, of the air vehicle. In a high speed flight regime the lifting body alone is sufficient and the outboard panels are collectively rotated to reduce drag and contribute substantially zero lift. In a slow speed flight regime, the outboard panels are collectively rotated to contribute to the lift on the air vehicle.

Abstract translation: 限定对称平面的空中车辆包括一对舷外面板，其可旋转地安装在车辆的提升体上并且分别沿着对称平面的相反方向延伸。 控制系统共同地旋转外侧面板，以选择性地贡献从面板到机动车辆上的电梯的力。 控制系统还将外侧面板差分地旋转以控制空中车辆的滚动。 一对尾翼也可旋转地安装在提升体上，以建立以对称平面为中心的二面角。 控制系统将这些尾翼面板共同旋转以控制俯仰，并差速旋转尾翼面板以控制飞行器的偏航。 在高速飞行状态下，单独的提升体就足够了，并且外侧面板共同旋转以减少阻力并大体上提供零升力。 在慢速飞行状态下，外侧面板被集体旋转以对飞行器上的电梯做出贡献。

公开(公告)号：US5340057A

公开(公告)日：1994-08-23

申请号：US850913

申请日：1992-03-13

Applicant: Hugh Schmittle

Inventor： Hugh Schmittle

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C29/02 ,  B64C3/385 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

Abstract: The VTOL aircraft includes a free wing having wings on opposite sides of the fuselage connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators, rudder and the differential pitch settings of the wings, respectively. At launch, the elevator pitches the fuselage nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing freely rotates relative to the fuselage into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and tile aircraft may be gently recovered in or on a resilient surface such as a net.

Abstract translation: 垂直起落架飞机包括一个自由翼，在机身的相对两侧具有彼此连接的翼，用于联合自由旋转，并在飞行员，计算机或遥控器下进行差距俯仰设置。 在垂直发射时，俯仰，偏航和侧倾控制分别由电梯，方向舵和翼的差距俯仰设置来实现。 在发射时，升降机将机身鼻部向下倾斜以改变推力矢量并向飞行器提供水平速度，由此自由翼相对于机身自由旋转成大致水平的方向以在水平飞行期间提供升力。 从水平飞行到垂直飞行的过渡是通过相反的过程实现的，瓦片飞机可以在诸如网络的弹性表面中或其上轻轻地回收。

公开(公告)号：US4730793A

公开(公告)日：1988-03-15

申请号：US566163

申请日：1984-01-26

Applicant: Charles H. Thurber, Jr. ,  Frederick A. Behrens ,  John H. Hunton

Inventor： Charles H. Thurber, Jr. ,  Frederick A. Behrens ,  John H. Hunton

IPC: B64C39/02 ,  B64F1/10 ,  F41G7/00 ,  F41G7/22 ,  F42B15/053

CPC classification number: B64C39/024 ,  B64F1/10 ,  F41G7/007 ,  F41G7/22 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208

Abstract: A method and system for delivery ordnance to a target via a remotely piloted or programmable aircraft including a yaw-to-turn guidance system, a deployment and launching system and packaging for the aircraft are disclosed.

Abstract translation: 公开了一种用于通过远程驾驶或可编程的飞行器对目标进行运送的方法和系统，包括偏航转向引导系统，用于飞机的部署和发射系统以及包装。

公开(公告)号：US20230192290A1

公开(公告)日：2023-06-22

申请号：US17554371

申请日：2021-12-17

Applicant: WING Aviation LLC

Inventor： Adam Woodworth ,  Giulia B. Pantalone ,  Luis Prado ,  Michelle Suen

IPC: B64C39/02 ,  B64C27/26 ,  B64C27/32 ,  B64C11/00 ,  B64C27/30 ,  B64C27/80 ,  G05D1/10

CPC classification number: B64C39/024 ,  B64C27/26 ,  B64C27/325 ,  B64C11/00 ,  B64C27/30 ,  B64C27/80 ,  G05D1/102 ,  B64C2201/02 ,  B64C2201/108 ,  B64C2201/104 ,  B64C2201/165

Abstract: An unmanned aerial vehicle (UAV) includes lift rotors and control rotors. The lift rotors are mounted to the UAV and oriented to provide a first vertical thrust to the UAV. The control rotors are mounted to the UAV outboard of the lift rotors and oriented to provide a second vertical thrust to the UAV. The control rotors are each smaller than any of the lift rotors.