公开(公告)号：US07165745B2

公开(公告)日：2007-01-23

申请号：US10808725

申请日：2004-03-24

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：US07101246B1

公开(公告)日：2006-09-05

申请号：US11189623

申请日：2005-07-26

Applicant: Michael A. Dammar

Inventor： Michael A. Dammar

IPC: A63H27/12

CPC classification number: B64C39/00 ,  B64C27/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/22

Abstract: A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.

公开(公告)号：US20060121818A1

公开(公告)日：2006-06-08

申请号：US10595022

申请日：2004-06-21

Applicant: Chang Lee ,  Nam Song

Inventor： Chang Lee ,  Nam Song

IPC: A63H27/127

CPC classification number: B64C39/028 ,  A63H27/12 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/165

Abstract: The purpose of this invention is to provide an ultra-miniature aircraft which is able to perform ‘Vertical Take-off and Landing (VTOL)’ and maintaining altitude when the vehicle is moving or when the horizontal velocity of a vehicle is at 0 by getting life only from a single rotor's rotation, and without using separate stabilizers such as a tail-rotor or a gyro. To fulfill the above purpose, this invention comprises: several blades in airfoil shape that are places in calculated angle and space; hubs that connect the blade to with a body of a vehicle; a rotor which gives lifting force with its spin; a spin-able axle which its vertical hem is bound to the hubs; a rotor drive that is needed to spin the rotor; a vehicle body that is placed right under the rotor in order to fly from the lift that is obtained by revolutions of the rotor; fixed-wings that are placed in certain angle and space around the outside of the vehicle body in order to reduce a reaction torque, which affects the body to turn the opposite direction of the rotor, from the rotor's movement; and a reaction-torque-counter-balancing-system on each of the above fixed-wings that offsets the reaction torque aggressively.

Abstract translation: 本发明的目的是提供一种超小型飞机，其能够执行“垂直起飞和着陆（VTOL）”，并且当车辆移动时保持高度，或者当车辆的水平速度为0时，通过获得 只有从单个转子旋转，并且不使用单独的稳定器，例如尾转子或陀螺仪。 为了实现上述目的，本发明包括：以计算的角度和空间位置的翼型形状的几个叶片; 将刀片连接到车身的轮毂; 一个转子，其旋转提供提升力; 一个可旋转轴，其垂直下摆与轮毂相连; 需要旋转转子的转子驱动器; 车体正好位于转子正下方，以便从通过转子旋转获得的电梯飞行; 固定翼，其被设置在车体外部的一定角度和空间中，以便减小影响车身转动反转方向的反作用转矩与转子的运动; 以及在每个上述固定翼上的反作用力 - 反平衡系统，其积极地抵消了反作用力矩。

公开(公告)号：US20050258304A1

公开(公告)日：2005-11-24

申请号：US11189605

申请日：2005-07-26

Applicant: Michael Dammar

Inventor： Michael Dammar

IPC: B64C27/00 ,  B64C39/00 ,  B64C39/02 ,  B64C27/22

CPC classification number: B64C39/00 ,  B64C27/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/22

Abstract: A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.

Abstract translation: 旋转飞机（旋翼飞机），其中整个飞机在其飞行时绕其质心旋转，并且其中质心位于由飞机的单翼和两个螺旋桨形成的大致三角形区域中的飞机外部。 当飞机飞行时，两个螺旋桨提供关于质心的扭矩，并旋转机翼，为飞机提供升降机。 飞机可以通过固定的无线电发射机进行控制，该发射机发出俯仰，滚转，偏航和高度的指令。 飞机中的接收机使用传输的信号来结合发送的命令来建立飞机的瞬时定向，以产生驱动影响飞机姿态的螺旋桨马达的控制信号。 俯仰和倾斜是通过螺旋桨电机电压的脉宽调制来控制的，以便影响飞机旋转周期特定部分的推力。

公开(公告)号：US20050224657A1

公开(公告)日：2005-10-13

申请号：US10782253

申请日：2004-02-19

Applicant: John Bolling

Inventor： John Bolling

IPC: B64C1/00 ,  B64C39/02 ,  B64D39/00

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104

Abstract: An in-flight refueling system for an unmanned aircraft is responsive to sensed forces acting on a refueling receptacle of the aircraft by a separate refueling probe, to control movements of the aircraft as it is being refueled to reduce the magnitude of the sensed forces and thereby maintain the coupling of the aircraft with the refueling probe.

Abstract translation: 用于无人驾驶飞机的飞行中加油系统响应于通过单独的加油探针作用在飞机的加油容器上的感测力，以控制飞机在被加油时的运动，以减小感测力的大小，从而 保持飞机与加油探头的耦合。

公开(公告)号：US06845939B1

公开(公告)日：2005-01-25

申请号：US10693800

申请日：2003-10-24

Applicant: G. Douglas Baldwin

Inventor： G. Douglas Baldwin

IPC: B64C29/00 ,  B64C39/02 ,  B64C27/28

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

Abstract translation: 公开的飞行技术包括具有第一端和第二端的悬挂结构，升降单元和有效载荷单元。 提升单元包括机舱和尾巴，并且枢转地联接到悬架结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂，并且使得抵抗来自提升单元的降洗的阻力最小化。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。

公开(公告)号：US06845937B2

公开(公告)日：2005-01-25

申请号：US10453777

申请日：2003-06-03

Applicant: Henry August

Inventor： Henry August

IPC: B64C5/12 ,  B64C39/02 ,  B64C39/06 ,  B64C39/12 ,  B64D1/06 ,  F42B10/16 ,  F42B10/62 ,  F42B12/58 ,  F42B12/62 ,  F42B15/00 ,  B64C37/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/104 ,  B64C2201/121 ,  F42B10/16 ,  F42B10/62 ,  F42B12/58 ,  F42B12/62 ,  F42B15/00

Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

Abstract translation: 可重复使用的马赫速度移动平台通过垂直发射，无力滑翔，武器释放和着陆操作阶段提供武器有效载荷。 平台包括具有尾部和前端的大致管状的主体和有效载荷部分。 一个弓翼由身体后端支撑。 拱翼具有通过两个弯曲端板在远端连接的上翼和下翼。 前端组件在前端连接，具有向上定向的固定迎角，以产生前端提升。 安装在车体下方的散热瓦片和下部翼片下侧辐射/消散在高角度攻角平台折返期间产生的热量。 使用雷达吸收或雷达半透明材料。 该平台优选地从尾端排出有效载荷以进行安全分离。 起落架延伸到着陆阶段。

公开(公告)号：US20050011990A1

公开(公告)日：2005-01-20

申请号：US10620793

申请日：2003-07-16

Applicant: Yuriy Gmirya

Inventor： Yuriy Gmirya

IPC: B64C29/00 ,  B64C39/02 ,  B64D35/04 ,  B64D27/00

CPC classification number: F16H1/22 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/04

Abstract: A powerplant system for a vehicle such as a hybrid UAV includes a miniature gas turbine engine and a gearbox assembly. The engine is mounted to the gearbox assembly through a support structure which provides for pivotal movement of the engine relative thereto. The input gear is engaged with two gears such that the pivoted engine arrangement permits the input gear to float until gear loads between the input gear and the first and second gear are balanced. Regardless of the gear teeth errors or gearbox shaft misalignments the input gear will float and split the torque between the two gears.

Abstract translation: 用于诸如混合UAV的车辆的动力装置系统包括微型燃气涡轮发动机和齿轮箱组件。 发动机通过支撑结构安装到齿轮箱组件，该支撑结构提供发动机相对于其的枢转运动。 输入齿轮与两个齿轮接合，使得枢转的发动机装置允许输入齿轮浮动，直到输入齿轮与第一和第二齿轮之间的齿轮负载平衡。 齿轮齿轮误差或齿轮箱轴不对准，输入齿轮将浮动并分离两个齿轮之间的转矩。

公开(公告)号：US20040248496A1

公开(公告)日：2004-12-09

申请号：US10768741

申请日：2004-02-02

Inventor： William B. Harvey

IPC: A63H027/00

CPC classification number: B64C39/024 ,  A63H27/02 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

Abstract: An unmanned, remote-controlled, long-range or long-flight duration airplane is designed to efficiently carry a large amount of fuel and payload for long duration flights. Structural wing design comprises an integral structure of recessed and interconnected geometric shapes, such as hexagonal cells. Wings are formed together as a single unit, with each wing formed in an arc design as it extends from the fuselage.

Abstract translation: 无人驾驶，远程控制，长距离飞行或长时间飞行的飞机旨在有效携带大量的燃油和有效载荷以进行长时间飞行。 结构翼设计包括凹陷和互连的几何形状的整体结构，例如六边形单元。 翅膀一起形成为单个单元，每个翼片从机身延伸形成弧形设计。

公开(公告)号：US06672538B2

公开(公告)日：2004-01-06

申请号：US10153970

申请日：2002-05-23

Applicant: Vincent Francis Millea ,  Anthony George Chory ,  Michelle Consolini ,  Ralph D. Costanzo ,  Jules G. Kish

Inventor： Vincent Francis Millea ,  Anthony George Chory ,  Michelle Consolini ,  Ralph D. Costanzo ,  Jules G. Kish

IPC: B64C2730

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/06

Abstract: A transmission system for a hybrid aircraft is driven by a plurality of driveshafts and drives a translational propulsion system. Each driveshaft is mounted to a pinion gear which mesh with an upper and lower counter-rotating gear. The upper and lower counter-rotating gears drive a respective upper and lower rotor shaft which powers a counter-rotating rotor system. A first angle is defined between a first and a second driveshaft while a second angle is defined between the second and a third driveshaft. The angle between the driveshafts are a whole number multiple of the formula: &thgr;=(CP/R)*(180/&pgr;). By so angularly locating the driveshafts, proper meshing of the pinion gears and the upper and lower counter-rotating gears is assured and tolerances are less stringent as the support structure is effective designed around optimal location of the driveshafts for gear meshing rather than vice versa.

Abstract translation: 用于混合飞机的传动系统由多个驱动轴驱动并驱动平移推进系统。 每个驱动轴安装在与上下反转齿轮啮合的小齿轮上。 上下反转齿轮驱动相应的上下转子轴，其对反向旋转的转子系统供电。 在第一和第二驱动轴之间限定第一角度，而在第二和第三驱动轴之间限定第二角度。 驱动轴之间的角度是以下公式的整数倍：θ=（CP / R）*（180 / pi）。 通过如此角度地定位传动轴，确保小齿轮和上下相对转动齿轮的适当啮合，并且由于支撑结构有效地围绕用于齿轮啮合的驱动轴的最佳位置设计而不是反之亦然，公差不太严格。