公开(公告)号：US20140046589A1

公开(公告)日：2014-02-13

申请号：US14002657

申请日：2012-04-13

Applicant: Bernhard Metzler ,  Knut Siercks

Inventor： Bernhard Metzler ,  Knut Siercks

IPC: G01B21/04 ,  G05D1/00

CPC classification number: G01B21/04 ,  B64C2201/123 ,  B64C2201/141 ,  G05D1/0094

Abstract: A measuring system for determining 3D coordinates of measurement points on an object surface which has a scanning apparatus for measuring the measurement points on the object surface and for determining inner measurement point coordinates in an inner scanning coordinate system. Furthermore, a referencing arrangement for producing referencing information for referencing the inner measurement point coordinates in the outer object coordinate system and an evaluation unit for determining the 3D coordinates of the measurement points in the outer object coordinate system on the basis of the inner measurement point coordinates and the referencing information are provided such that the inner measurement point coordinates are in the form of 3D coordinates in the outer object coordinate system. The scanning apparatus is in this case carried in an unmanned, controllable, automotive air vehicle.

Abstract translation: 一种用于确定物体表面上的测量点的3D坐标的测量系统，其具有用于测量物体表面上的测量点并用于确定内部扫描坐标系中的内部测量点坐标的扫描装置。 此外，用于产生用于参考外部对象坐标系中的内部测量点坐标的参考信息的参考装置和用于基于内部测量点坐标来确定外部对象坐标系中的测量点的3D坐标的评估单元 并且提供参考信息，使得内部测量点坐标是外部对象坐标系中的3D坐标的形式。 在这种情况下，扫描装置是携带在无人驾驶的，可控的汽车中的。

公开(公告)号：US08434920B2

公开(公告)日：2013-05-07

申请号：US13211483

申请日：2011-08-17

Applicant: Kenneth R Jones

Inventor： Kenneth R Jones

IPC: F21V1/20

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  F42B12/42 ,  G05D1/0094

Abstract: An aerially deployed illumination system is provided which may be remotely operated or preprogrammed to illuminate a designated target, such as a geographic area, vehicle, or personnel. In particular, a remotely controlled UAV having an illumination system disposed thereon is provided, the illumination system comprised of a concentrated light source and light movement apparatus operable to rapidly scan the target with the light source, thereby providing an illusion of a large area of illumination. Preferably, a line is created from the light source, the line being rapidly moved over the target in specific patterns and at specific frequencies. The system may further include a plurality of UAV's capable of ad hoc networking, so as to illuminate both large areas, as well as stationary and moving targets. In addition, the UAV's having an illumination system disposed thereon may be disposed within a projectile, the projectile tube or gun launched, and the UAV ejected from the projectile over a designated target, thereby enabling quick delivery of the UAV to an area of interest.

Abstract translation: 提供了一种空中部署的照明系统，其可以被远程操作或预编程以照亮指定的目标，例如地理区域，车辆或人员。 特别地，提供了一种具有设置在其上的照明系统的远程控制的UAV，该照明系统由集中的光源和光运动装置组成，可操作以用光源快速扫描目标，从而提供大面积照明的错觉 。 优选地，从光源产生线，线以特定模式和特定频率快速移动到目标上。 该系统还可以包括能够进行自组织联网的多个UAV，以便照亮大面积以及固定和移动的目标。 此外，具有设置在其上的照明系统的UAV可以设置在射弹内，射弹管或枪发射，并且无人机从射弹弹出指定的目标，从而能够将UAV快速传送到感兴趣的区域。

公开(公告)号：US20120044710A1

公开(公告)日：2012-02-23

申请号：US13211483

申请日：2011-08-17

Applicant: Kenneth R. Jones

Inventor： Kenneth R. Jones

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  F42B12/42 ,  G05D1/0094

Abstract: An aerially deployed illumination system is provided which may be remotely operated or preprogrammed to illuminate a designated target, such as a geographic area, vehicle, or personnel. In particular, a remotely controlled UAV having an illumination system disposed thereon is provided, the illumination system comprised of a concentrated light source and light movement apparatus operable to rapidly scan the target with the light source, thereby providing an illusion of a large area of illumination. Preferably, a line is created from the light source, the line being rapidly moved over the target in specific patterns and at specific frequencies. The system may further include a plurality of UAV's capable of ad hoc networking, so as to illuminate both large areas, as well as stationary and moving targets. In addition, the UAV's having an illumination system disposed thereon may be disposed within a projectile, the projectile tube or gun launched, and the UAV ejected from the projectile over a designated target, thereby enabling quick delivery of the UAV to an area of interest.

Abstract translation: 提供了一种空中部署的照明系统，其可以被远程操作或预编程以照亮指定的目标，例如地理区域，车辆或人员。 特别地，提供了一种具有设置在其上的照明系统的远程控制的UAV，该照明系统由集中的光源和光运动装置组成，可操作以用光源快速扫描目标，从而提供大面积照明的错觉 。 优选地，从光源产生线，线以特定模式和特定频率快速移动到目标上。 该系统还可以包括能够进行自组织联网的多个UAV，以便照亮大面积以及固定和移动的目标。 此外，具有设置在其上的照明系统的UAV可以设置在射弹内，射弹管或枪发射，并且无人机从射弹弹出指定的目标，从而能够将UAV快速传送到感兴趣的区域。

公开(公告)号：US20090216394A1

公开(公告)日：2009-08-27

申请号：US11932545

申请日：2007-10-31

Applicant: Stephen B. Heppe ,  Andreas H. von Flotow ,  Aram Soghikian

Inventor： Stephen B. Heppe ,  Andreas H. von Flotow ,  Aram Soghikian

IPC: G06F19/00 ,  B64D7/00

CPC classification number: B64D7/00 ,  B64C39/024 ,  B64C2201/123 ,  B64C2201/127 ,  B64D47/08

Abstract: Turret assemblies for small aerial platforms, including unmanned aircraft, and associated methods are disclosed herein. In one embodiment, an aircraft system can include a turret assembly having a payload with a line of sight to a target and a gimbal system carrying the payload. The gimbal system can include (a) a first support coupled to a first actuator to rotate about a first axis, and (b) a second support carried by the first support and coupled to a second actuator to rotate about a second axis generally transverse to the first axis. The payload can be carried by the second support. A housing at least partially surrounds the payload and the gimbal system. The turret assembly can also include a controller configured to direct movement of at least one of the first actuator and the second actuator such that the line of sight is pointed away from a point of impact before the turret assembly contacts the ground or another external structure during landing or capture operations.

Abstract translation: 本文公开了包括无人驾驶飞机在内的小型高空作业台的转塔组件和相关方法。 在一个实施例中，飞行器系统可以包括具有具有到目标的视线的有效载荷的转台组件和承载有效载荷的万向节系统。 万向节系统可以包括（a）联接到第一致动器以围绕第一轴线旋转的第一支撑件，以及（b）由第一支撑件承载并联接到第二致动器的第二支撑件，以绕第二轴线大致横向于 第一轴。 有效载荷可以由第二支撑承载。 壳体至少部分地围绕有效载荷和万向节系统。 转塔组件还可以包括控制器，其被配置为引导第一致动器和第二致动器中的至少一个的运动，使得在转塔组件接触地面或另一外部结构之前，视线被指向远离冲击点 着陆或捕获操作。

公开(公告)号：US07360741B2

公开(公告)日：2008-04-22

申请号：US11603815

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与飞行器接触的至少一个抓握部分，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：US20070084971A1

公开(公告)日：2007-04-19

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：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：US20060284005A1

公开(公告)日：2006-12-21

申请号：US11510013

申请日：2006-08-25

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

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

IPC: B64C3/56 ,  B64C3/00

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：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：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。