公开(公告)号：US20090026309A1

公开(公告)日：2009-01-29

申请号：US12056463

申请日：2008-03-27

Applicant: Michael SCHWARZ

Inventor： Michael SCHWARZ

IPC: B64C1/00

CPC classification number: B64D27/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048

Abstract: The invention relates to an aircraft having a first propulsion unit with an air inlet above the fuselage of the aircraft and a second propulsion unit with an air inlet below the fuselage of the aircraft, the fuselage of the aircraft having recesses for receiving the propulsion units which are arranged such that the first and the second propulsion unit are arranged above one another in the plane set by the longitudinal and vertical axis of the aircraft. The propulsion unit comprises an engine, a housing having an air inlet, devices for the releasable fastening of the propulsion unit to the fuselage of the aircraft as well as devices for establishing a releasable connection of electric supply and data lines as well as fuel lines between the propulsion unit and the fuselage of an aircraft.

Abstract translation: 本发明涉及一种具有第一推进单元的飞机，该第一推进单元具有在飞行器的机身上方的空气入口，以及具有在飞行器的机身下方具有空气入口的第二推进单元，飞行器的机身具有用于接收推进单元的凹部 被布置成使得第一和第二推进单元在由飞行器的纵向和纵向轴线设置的平面中彼此上下布置。 推进单元包括发动机，具有空气入口的壳体，用于将推进单元可释放地紧固到飞行器的机身的装置以及用于建立电力供应和数据线的可释放连接的装置以及在 推进单元和机身的机身。

公开(公告)号：US20060231675A1

公开(公告)日：2006-10-19

申请号：US11384167

申请日：2006-03-17

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C29/00

CPC classification number: B64C3/385 ,  B64C17/06 ,  B64C27/20 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/14

Abstract: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

公开(公告)号：US20060214051A1

公开(公告)日：2006-09-28

申请号：US11189623

申请日：2005-07-26

Applicant: Michael Dammar

Inventor： Michael Dammar

IPC: 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：US07097136B2

公开(公告)日：2006-08-29

申请号：US10823434

申请日：2004-04-13

Applicant: Robert A. Ruszkowski, Jr.

Inventor： Robert A. Ruszkowski, Jr.

IPC: B64C35/00

CPC classification number: B64C1/062 ,  B63G8/28 ,  B63G8/30 ,  B63G13/00 ,  B64C35/00 ,  B64C37/00 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/205 ,  F41F3/07 ,  F42B15/20

Abstract: A sea-launched and recovered unmanned aircraft is disclosed. The aircraft is jet-powered and has features and systems to maintain watertight integrity such that it may be released from a submerged submarine or dropped into a body of water by a ship or an aircraft. The aircraft is buoyant and remains at or near the water surface before its rockets are ignited. The rockets propel the air vehicle out of the sea and accelerate it to flying speed at which time a jet engine is started and the rockets are jettisoned. The air vehicle performs its mission independently or in conjunction with other ones of the air vehicles. The air vehicle then returns to an assigned splashdown point at sea via, for example, an engine-off “whip-stall” maneuver. A submarine or ship may retrieve the air vehicle and readies it for another mission.

Abstract translation: 披露了一架海上发射和回收的无人机。 飞机是喷气式动力的，并具有保持水密完整性的特征和系统，使得其可以从潜水艇释放或由船或飞机落入水体。 这架飞机是浮力的，并且在其火箭点火之前保持在水面或附近。 火箭将空中车辆推出海面，并将其加速到飞行速度，此时起飞喷气发动机，火箭被抛弃。 机动车辆独立地或与其他机动车辆一起执行任务。 然后，空中飞行器通过例如发动机关闭“鞭炮”操纵返回到海上指定的飞溅点。 潜艇或船只可以检索空中飞行器并准备进行另一个飞行任务。

公开(公告)号：US07090166B2

公开(公告)日：2006-08-15

申请号：US10758948

申请日：2004-01-16

Applicant: Brian D. Dennis ,  Andreas H. von Flotow

Inventor： Brian D. Dennis ,  Andreas H. von Flotow

IPC: B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  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 includes an extendable boom. A launch carriage is positioned on a launch guide structure of the boom and carries the aircraft during takeoff. An energy reservoir is configured to provide energy to the launch carriage during takeoff of the aircraft, and can absorb energy from the launch carriage to decelerate the launch carriage after takeoff. The apparatus can further include a transmission that smoothly and rapidly accelerates and/or decelerates the launch carriage.

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，飞行器可以从包括可扩展起重臂的装置发射。 发射架位于起重臂的发射导向结构上，并在起飞时承载飞机。 能量储存器构造成在飞行器起飞期间向发射台提供能量，并且可以从起飞台吸收能量，以在起飞后减速发射台。 该装置还可以包括使发射台平滑且快速地加速和/或减速的变速器。

公开(公告)号：US07059931B2

公开(公告)日：2006-06-13

申请号：US10855275

申请日：2004-05-26

Applicant: Michael A. Dammar

Inventor： Michael A. Dammar

IPC: A63H27/00

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：US07059564B2

公开(公告)日：2006-06-13

申请号：US10758940

申请日：2004-01-16

Applicant: Brian D. Dennis

Inventor： Brian D. Dennis

IPC: B64F1/02

CPC classification number: B64F1/06 ,  B63B27/26 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured by a recovery line in flight, a process that can be aided by a line capture device having a retainer with two portions spaced apart by a distance great enough to receive the recovery line, e.g., to capture the recovery line with increased security. The line capture device can be operatively mounted on a lifting surface of the aircraft.

Abstract translation: 描述了用于捕获和恢复无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由飞行中的恢复线捕获，该过程可以由具有保持器的线捕获装置辅助，该保持器具有两个间隔开足够大的距离以接收恢复线，例如捕获 恢复线增加了安全性。 线捕获装置可以可操作地安装在飞行器的提升表面上。

公开(公告)号：US20060032971A1

公开(公告)日：2006-02-16

申请号：US11042666

申请日：2005-01-24

Applicant: G. Baldwin

Inventor： G. Baldwin

IPC: B64C27/22

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：US20050230536A1

公开(公告)日：2005-10-20

申请号：US10758943

申请日：2004-01-16

Applicant: Brian Dennis ,  Clifford Jackson ,  Brian McGeer

Inventor： Brian Dennis ,  Clifford Jackson ,  Brian McGeer

IPC: B64C39/02 ,  B64F1/02 ,  B64F1/06

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 capturing, recovering, disassembling, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the boom can be extended to deploy a recovery line to capture the aircraft in flight, a process that can be aided by a line capture device having retainers in accordance with further aspects of the invention. The aircraft can then be returned to its launch platform, disassembled, and stored, again with little or no direct manual contact between the operator and the aircraft, for example, by capturing a first wing of the aircraft and securing a second wing before releasing the first.

Abstract translation: 描述了用于捕获，恢复，拆卸和存储无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，吊杆可以被延伸以部署回收线以在飞行中捕获飞行器，这是根据本发明的其它方面能够由具有保持器的线捕获装置辅助的过程。 然后，飞机然后可以返回到其发射平台，拆卸和存储，再次与操作者和飞机之间的很少或没有直接的手动接触，例如通过捕获飞行器的第一翼并且在释放之前固定第二翼 第一。

公开(公告)号：US06923404B1

公开(公告)日：2005-08-02

申请号：US10339908

申请日：2003-01-10

Applicant: Danny D. Liu ,  Ping-Chih Chen ,  Darius Sarhaddi

Inventor： Danny D. Liu ,  Ping-Chih Chen ,  Darius Sarhaddi

IPC: B64C1/00 ,  B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C9/00 ,  B64C30/00 ,  B64C39/02 ,  B64C39/08 ,  B64F1/04 ,  F42B10/14 ,  F42B10/64

CPC classification number: B64F1/04 ,  B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C30/00 ,  B64C39/024 ,  B64C39/028 ,  B64C39/08 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/125 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  F42B10/14 ,  F42B10/64 ,  Y02T50/14

Abstract: An unmanned air vehicle (“UAV”) apparatus is configured to have a body and a body-conformal wing. The body-conformal wing is configured to variably sweep from a closed position to a fully deployed position. In the closed position, the body-conformal wing span is aligned with the body axis and in the fully deployed position the body-conformal wing span is perpendicular to the axial direction of the body. Delivery of the UAV comprises the steps of: positioning the span of a body conformal wing in alignment with the axis of the body of the UAV; initiating the flight of the UAV; and adjusting the sweep angle of the body-conformal wing as a function of the current speed, altitude, or attack angle of the UAV, with the adjustment starting at a 0 degree position and varying between a closed position and a fully deployed position. The UAV also has a control mechanism configured to variably adjust the sweep of the body-conformal wing to achieve a high lift over drag ratio through out the flight path of the UAV.

Abstract translation: 无人驾驶飞行器（“UAV”）装置被配置为具有主体和主体保形翼。 身体适形翼被配置为从关闭位置可变地扫掠到完全展开位置。 在关闭位置，身体共形翅膀跨度与身体轴线对齐，并且在完全展开位置，身体共形翅膀跨度垂直于身体的轴向。 无人机的交付包括以下步骤：将身体保形翼的跨度定位成与UAV的身体的轴线对准; 启动无人机的飞行; 并且根据UAV的当前速度，高度或攻角来调节身体保形翼的扫掠角度，调整从0度位置开始，并且在关闭位置和完全展开位置之间变化。 无人机还具有控制机构，其配置为可变地调整身体保形翼的扫掠，以通过无人机的飞行路径实现高的牵引比。