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：US20050153812A1

公开(公告)日：2005-07-14

申请号：US10756031

申请日：2004-01-12

Applicant: J. Box ,  Jules Kish

Inventor： J. Box ,  Jules Kish

IPC: B64C39/02 ,  B64D35/00 ,  F16H1/20 ,  F16H1/22 ,  F16H1/28 ,  F16H13/04 ,  F16H3/74

CPC classification number: B64C39/024 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/00 ,  F16H1/20 ,  F16H1/227 ,  F16H13/04

Abstract: A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The transmission system includes a traction drive stage that provides a reduction ratio preferably having a value of at least 7, and most preferably greater than 9. The transmission system is of small-size preferably having a maximum diameter less than twelve inches. Preferably, the input stage of the transmission system is self-equilibrating such that first shaft can be supported without bearings and is operably coupled to the output shaft of the microturbine engine by an outside diameter piloted spline coupling mechanism. For vertical lift applications, a single traction stage along with a bevel gear assembly or other shaft transmission mechanism can be used to provide the necessary RPM reduction.

Abstract translation: 与微型涡轮发动机结合使用的用于推进飞机机体（例如基于螺旋桨的固定翼飞行器或基于转子的垂直升降飞机）或用于各种其它应用的传动系统。 微型涡轮发动机的输出轴优选地在72,000RPM和150,000RPM之间的转速下工作，输出功率在150HP和5HP之间（最优选地在50,000RPM和200,000RPM之间的扩展范围内工作，并且输出 功率在200 HP和5 HP之间）。 传动系统包括牵引驱动台，其优选地具有至少7的值，最优选地大于9的减速比。传动系统的尺寸最小，最好具有小于12英寸的最大直径。 优选地，传动系统的输入级是自平衡的，使得第一轴可以被支撑而没有轴承，并且通过外径引导的花键联接机构可操作地联接到微型涡轮发动机的输出轴。 对于垂直升降应用，可以使用单个牵引台以及锥齿轮组件或其他轴传动机构来提供必要的RPM减小。

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：US06874729B1

公开(公告)日：2005-04-05

申请号：US10031925

申请日：2000-07-24

Applicant: William R. McDonnell

Inventor： William R. McDonnell

IPC: B64C25/68 ,  B64C39/02 ,  B64D3/00 ,  B64F1/02 ,  B64F1/04 ,  B64F1/10

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

公开(公告)号：US20050029400A1

公开(公告)日：2005-02-10

申请号：US10600400

申请日：2003-06-20

Applicant: Richard Ouellette ,  Aaron Kutzmann

Inventor： Richard Ouellette ,  Aaron Kutzmann

IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64D7/00

CPC classification number: B64C1/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/187 ,  B64D7/00

Abstract: A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.

Abstract translation: 模块化组件组可配置成形成多个具有飞行能力的平台。 多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。 主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。 多个任务专用面板各自可拆卸地连接到相对的壁之一。 至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。

公开(公告)号：US20050017129A1

公开(公告)日：2005-01-27

申请号：US10754251

申请日：2004-01-09

Applicant: William McDonnell

Inventor： William McDonnell

IPC: B64C25/68 ,  B64C39/02 ,  B64D3/00 ,  B64F1/02 ,  B64F1/04 ,  B64F1/10

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将UAV（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

公开(公告)号：US20040075018A1

公开(公告)日：2004-04-22

申请号：US10679984

申请日：2003-10-06

Applicant: Fuji Jukogyo Kabushiki Kaisha

Inventor： Akihiro Yamane

IPC: B64C011/34 ,  B64C011/44 ,  B64C027/54

CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  G05D1/0669 ,  G05D1/0676

Abstract: An unmanned helicopter 20 includes altitude control device for giving a command of a collective pitch rudder angle based on an altitude change rate command, etc., and performing altitude control of an airframe and takeoff device, upon reception of a takeoff start command from the ground, for causing the airframe to take off and climbing the airframe to a first altitude while increasing the collective pitch rudder angle without performing the altitude control of the altitude control device and then causing the altitude control device to start the altitude control. The unmanned helicopter further includes descending device for causing the airframe to descend to a second altitude while changing descent rate command of the altitude control device and giving a descent rate command smaller than the descent rate command to the second altitude to the altitude control device for causing the airframe to descend from the second altitude to the ground.

Abstract translation: 无人直升机20包括高度控制装置，用于基于高度变化率命令等给出集体俯仰舵角的命令，并且在从地面接收到起飞开始命令时执行机体和起飞装置的高度控制 用于使机身在不进行高度控制装置的高度控制的同时增加集体桨距方向舵角度使机身起飞并爬升到第一高度，然后使高度控制装置开始高度控制。 无人直升机进一步包括下降装置，用于使机身下降到第二高度，同时改变高度控制装置的下降速率指令，并将低于下降速率指令的下降率指令提供给第二高度，以向高度控制装置引起 机身从第二高度下降到地面。

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。