公开(公告)号：US07055777B2

公开(公告)日：2006-06-06

申请号：US10178345

申请日：2002-06-25

Applicant: Hokan S. Colting

Inventor： Hokan S. Colting

IPC: B64B1/02 ,  B64B1/24

CPC classification number: B64B1/34 ,  B64B1/02 ,  B64B1/32 ,  B64C21/02 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  Y02T50/166

Abstract: An airship has a generally spherical shape and has an internal envelope for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system that permits it to be flown to a desired loitering location, and to be maintained in that location for a period of time. In one embodiment the airship may achieve neutral buoyancy when the internal envelope is as little as 7% full of lifting gas, and may have a service ceiling of about 60,000 ft. The airship has an equipment module that can include either communications equipment, or monitoring equipment, or both. The airship can be remotely controlled from a ground station. The airship has a solar cell array and electric motors of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit that can be used to drive the electric motors. The airship can have a pusher propeller that assists in driving the airship and also moves the point of flow separation of the spherical airship further aft. In one embodiment the airship can be refuelled at altitude to permit extended loitering.

Abstract translation: 飞艇具有大致球形并且具有用于容纳诸如氦气或氢气的提升气体的内部信封。 飞艇有一个推进和控制系统，允许飞行到所需的游荡地点，并在该地点保持一段时间。 在一个实施例中，当内部信封充满提升气体的时间少至7％时，飞艇可以达到中性浮力，并且可以具有大约6万英尺的服务天花板。飞艇具有可以包括通信设备或监视的设备模块 设备，或两者兼而有之。 飞艇可以从地面站遥控。 飞艇具有太阳能电池阵列，推进和控制系统的电动机由阵列获得的功率驱动。 飞艇还具有可用于驱动电动机的辅助动力单元。 飞艇可以有一个推动螺旋桨，有助于驾驶飞艇，还可以使球形飞艇进一步向后流动。 在一个实施例中，飞艇可以在高度加油以允许延长的游荡。

公开(公告)号：US20060074557A1

公开(公告)日：2006-04-06

申请号：US11011001

申请日：2004-12-13

Applicant: Anthony Mulligan ,  Christopher Troudt ,  Jason Michael Douglas

Inventor： Anthony Mulligan ,  Christopher Troudt ,  Jason Michael Douglas

IPC: G01C21/26

CPC classification number: G05D1/0094 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/205 ,  B64C2201/208

Abstract: Methods and apparatuses provide surveillance of a convoy. At least one unmanned aerial vehicle (UAV) obtains images around the convoy's position to provide information about potential hostile activity while the UAV follows a generally curvilinear path around the convoy as instructed by one of the convoy vehicles. Path planner algorithm software is executed by the controlling convoy vehicle in which position and velocity information regarding the unmanned aerial vehicle and the convoy are processed to determine values of control variables. The determined values are sent to the unmanned aerial vehicle over a wireless communications channel. The path of the surveillance vehicle may be changed in order to provide evasive measures to avoid an attack on the surveillance vehicle by an adversary.

Abstract translation: 方法和设备对车队进行监视。 至少一架无人驾驶飞行器（UAV）获取围绕车队位置的图像，以提供关于潜在敌对行为的信息，而无人机按照车队车辆指示的方式沿着车队周围的大致曲线路径。 路径规划器算法软件由控制车队车辆执行，其中处理关于无人机和车队的位置和速度信息以确定控制变量的值。 所确定的值通过无线通信信道发送到无人驾驶飞行器。 监视车辆的路径可能会改变，以便提供回避措施，以避免对手对监控车辆的攻击。

公开(公告)号：US06959895B2

公开(公告)日：2005-11-01

申请号：US10774653

申请日：2004-02-04

Applicant: David A. Cylinder

Inventor： David A. Cylinder

IPC: B64C33/02 ,  B64C39/02 ,  B64C39/08

CPC classification number: B64C39/08 ,  B64C33/02 ,  B64C39/024 ,  B64C2201/025 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146

Abstract: A vehicle for flying and having a forward portion and a rearward portion opposite the forward. The vehicle includes a first pair of wings arranged at the forward portion of the vehicle, a second pair of wings arranged at the rearward portion of the vehicle, and a support structure. The support structure is connected to the forward pair of wings and connected to the rearward pair of wings, the support structure being arranged to drive the forward pair of wings alternately toward each other and apart and drives the second pair of wings alternately toward each other and apart.

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：US20050178895A1

公开(公告)日：2005-08-18

申请号：US10808725

申请日：2004-03-24

Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

IPC: B64C3/56 ,  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：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。

公开(公告)号：US20050151009A1

公开(公告)日：2005-07-14

申请号：US10760150

申请日：2004-01-16

Applicant: Cory Roeseler ,  Andreas von Flotow

Inventor： Cory Roeseler ,  Andreas von Flotow

IPC: B64C39/02 ,  B64F1/04 ,  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 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。

公开(公告)号：US20050133665A1

公开(公告)日：2005-06-23

申请号：US10759545

申请日：2004-01-16

Applicant: Brian Dennis ,  Brian McGeer ,  Cory Roeseler

Inventor： Brian Dennis ,  Brian McGeer ,  Cory Roeseler

IPC: B64C25/68 ,  B64C39/02 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  B64C25/00

CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for capturing and constraining motion of unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. A trigger mechanism coupled to the recovery line can actuate a hoist device to reduce slack in the recovery line. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft on the recovery line.

Abstract translation: 描述了用于捕获和约束无人驾驶飞机和其他飞行装置或射弹的运动的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 联接到回收管线的触发机构可以启动提升装置以减少回收管线中的松弛。 耦合到回收管线的张紧装置可以吸收与飞机在回收管线上的冲击相关联的力。

公开(公告)号：US06840477B2

公开(公告)日：2005-01-11

申请号：US10085181

申请日：2002-02-27

Applicant: Masaki Hamamoto ,  Yoshiji Ohta ,  Keita Hara

Inventor： Masaki Hamamoto ,  Yoshiji Ohta ,  Keita Hara

IPC: B25J5/00 ,  B64C33/02 ,  B64C39/02 ,  H02N2/00 ,  B64C33/00

CPC classification number: B64C33/02 ,  B64C39/028 ,  B64C2201/025 ,  B64C2201/044 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146

Abstract: On a main body portion of a fluttering apparatus, a wing (left wing) is formed which has a front wing shaft, a rear wing shaft and a wing film provided spreading over the front and rear wing shafts. Further, on the main body portion, a rotary actuator for driving the front wing shaft and a rotary actuator for driving the rear wing shaft are mounted. The front (rear) wing shafts reciprocate in a plane orthogonally crossing an axis of rotation with the actuator serving as the fulcrum. Thus, a moving apparatus is obtained which has superior maneuverability and can move not hindered by any obstacle or geometry both indoors and outdoors.

Abstract translation: 在飘动装置的主体部分上，形成有一个翼翼（左翼），其具有前翼轴，后翼轴和设置在前翼和后翼轴上的翼片。 此外，在主体部上安装有用于驱动前翼轴的旋转致动器和用于驱动后翼轴的旋转致动器。 前（后）翼轴在与作为支点的致动器正交的旋转轴线的平面中往复运动。 因此，获得具有优异的机动性并且可以在室内和室外不受任何障碍物或几何形状阻碍的移动装置。

公开(公告)号：US06685140B2

公开(公告)日：2004-02-03

申请号：US10255185

申请日：2002-09-26

Applicant: Ernest A. Carroll

Inventor： Ernest A. Carroll

IPC: B64C2556

CPC classification number: B64C39/028 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64D17/80 ,  F02B75/34 ,  F02D35/0069 ,  F02D41/2406 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  G05D1/101

Abstract: A miniature, unmanned aircraft having a parachute which deploys automatically under certain conditions. The aircraft has a flight control system based on remotely generated signals, potentially achieves relatively high altitude flight for a remotely controlled aircraft, and can thus operate well beyond line-of-sight control. For safety, an automatically deployed parachute system is provided. The parachute deployment system includes a folded parachute and a propulsion system for expelling the parachute from the aircraft. Preferably, a microprocessor for flight management sends intermittent inhibitory signals to prevent unintended deployment. A deployment signal is generated, illustratively, when the microprocessor fails, when engine RPM fall below a predetermined threshold, and when the aircraft strays from predetermined altitude and course.

Abstract translation: 具有降落伞的微型无人机在某些条件下自动部署。 该飞机具有基于远程产生的信号的飞行控制系统，可能为远程控制的飞机实现相对高的高度飞行，并且因此可以远远超出视线控制。 为了安全起见，提供了自动部署的降落伞系统。 降落伞部署系统包括折叠的降落伞和用于从降落伞排出飞机的推进系统。 优选地，用于飞行管理的微处理器发送间歇性抑制信号以防止意外部署。 例如，当微处理器发生故障时，当发动机转速低于预定阈值时，以及当飞行器从预定高度和当然时间偏离时，产生部署信号。