公开(公告)号：US07665691B2

公开(公告)日：2010-02-23

申请号：US11679365

申请日：2007-02-27

Applicant: Patrick T. Hanzlick ,  Joshua J. Lange

Inventor： Patrick T. Hanzlick ,  Joshua J. Lange

IPC: B64F1/10

CPC classification number: B64F1/10 ,  B64C2201/084 ,  B64C2201/208

Abstract: An aerial vehicle launching system includes a launch platform and a restraint system coupled to the launch platform. The restraint system has at least one passive restraint suitably adapted to indirectly restrain an aerial vehicle. The restraint system is configured to coordinate the uniform retention and release of the passive restraint in order to launch the aerial vehicle.

Abstract translation: 飞行器发射系统包括发射平台和耦合到发射平台的约束系统。 约束系统具有至少一个适当地适应于间接限制飞行器的被动约束。 约束系统被配置为协调被动约束的均匀保持和释放以便发射飞行器。

公开(公告)号：US20100025543A1

公开(公告)日：2010-02-04

申请号：US12262747

申请日：2008-10-31

Applicant: LLOYD E. KINSEY ,  Patrick Kranking

Inventor： LLOYD E. KINSEY ,  Patrick Kranking

IPC: B64C27/24

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

Abstract translation: 根据本发明的各个方面的用于变换航空器的方法和装置可以与被配置为围绕其纵向轴线旋转飞行器的发射系统一起操作。 枢转地连接到飞行器的提升表面可以被定位成使得飞行器的旋转导致提升表面在飞行器上产生提升力。 该升降机使得飞行器在提升表面旋转到第二位置之前陀螺地升高，使得飞行器从陀螺仪模式转换为固定翼型飞行器。 然后可以再次旋转提升表面，以允许飞行器作为自动陀螺仪着陆。

公开(公告)号：US07472866B2

公开(公告)日：2009-01-06

申请号：US11602436

申请日：2006-11-15

Applicant: Jeremy R. Heaston ,  David E. Toth

Inventor： Jeremy R. Heaston ,  David E. Toth

IPC: B64F1/04 ,  F41F3/00 ,  F41F3/04

CPC classification number: B64F1/04 ,  B63G8/28 ,  B64C2201/084 ,  B64C2201/205 ,  F41F3/07

Abstract: A launch system in which an unmanned aerial vehicle is secured to a platform in a watertight tube adapted to be launched from a submerged platform. Once launched, side panels on the tube are jettisoned and a flotation device is deployed to bring the tube to the surface. The flotation device maintains the tube in a vertical position when rising to and at the surface. After surfacing, a top-sealing cap of the tube is opened. A lifting mechanism within the tube raises the vertically oriented platform assembly up within the tube. Guide rails maintain the vertical orientation of the assembly during lifting. At the topmost point of travel, the assembly is raised clear of the tube and is disengaged from the guide rails, allowing the assembly to pivot about its attachment to the lifting mechanism and assume an orientation favorable for launching the UAV.

Abstract translation: 一种发射系统，其中无人驾驶飞行器固定在适于从淹没平台发射的水密管中的平台上。 一旦启动，管上的侧面板被抛弃，并且布置浮选装置以将管带到表面。 当上升到表面时，浮选装置将管保持在垂直位置。 表面处理后，打开管子的顶盖。 管内的提升机构使垂直定向的平台组件向上升起。 导轨在升降过程中保持组件的垂直方向。 在最高点行程时，组件从管上升起并与导轨分离，允许组件围绕其附接件枢转到提升机构，并采取有利于发射无人机的方向。

公开(公告)号：US20080125920A1

公开(公告)日：2008-05-29

申请号：US11576590

申请日：2005-10-11

Applicant: Philip John Miles ,  Richard Thomas Partner ,  Kenneth Ronald Keeler ,  Terence James McConnell

Inventor： Philip John Miles ,  Richard Thomas Partner ,  Kenneth Ronald Keeler ,  Terence James McConnell

IPC: G05D1/04 ,  G01C23/00 ,  G01V3/165 ,  B64C39/02 ,  G01V3/40 ,  G06F19/00

CPC classification number: B64C39/024 ,  B64C2201/084 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/182 ,  B64C2201/208 ,  G01V3/165

Abstract: An un-manned airborne vehicle (UAV), for acquiring aeromagnetic data for geophysical surveying at low altitude on land or over water, comprising an extended fuselage that is adapted to hold and maintain magnetometer and a magnetic compensation magnetometer at a minimum distance from the avionics and propulsion systems of the UAV. The magnetometer measures magnetic anomalies and the magnetic compensation magnetometer measures magnetic responses corresponding to the pitch, yaw and roll of the UAV. A data acquisition system stores and removes the magnetic response measurements from the magnetic anomaly measurements. The data acquisition system also stores a survey flight plan and transmits the same to the avionics system. The generator of the UAV is shielded and the propulsion system is stabilized to reduce magnetic and vibrational noises that can interfere with the operation of the magnetometer.

Abstract translation: 一种无人载客空中飞行器（UAV），用于获取陆上或水上低空地球物理测量的航空数据，包括一个延伸的机身，适用于将磁力计和一个磁性补偿磁力计保持在离飞行距离最远的距离 和无人机的推进系统。 磁力计测量磁异常，磁补偿磁力计测量对应于无人机的俯仰，偏航和滚动的磁响应。 数据采集​​系统从磁异常测量中存储和去除磁响应测量。 数据采集​​系统还存储一个调查飞行计划，并将其传送到航空电子系统。 无人机的发电机被屏蔽并且推进系统被稳定以减少可能干扰磁力计操作的磁和振动噪声。

公开(公告)号：US20080111021A1

公开(公告)日：2008-05-15

申请号：US11602436

申请日：2006-11-15

Applicant: David E. Toth ,  Jeremy R. Heaston

Inventor： David E. Toth ,  Jeremy R. Heaston

IPC: B64F1/08

CPC classification number: B64F1/04 ,  B63G8/28 ,  B64C2201/084 ,  B64C2201/205 ,  F41F3/07

Abstract: A launch system is provided in which an unmanned aerial vehicle is secured to a platform in a watertight tube adapted to be launched from a submerged platform. Once launched, side panels on the tube are jettisoned and a flotation device is deployed to bring the tube to the surface. The flotation device maintains the tube in a vertical position when rising to and at the surface. After surfacing, a top-sealing cap of the tube is opened. A lifting mechanism within the tube raises the vertically oriented platform assembly up within the tube. Guide rails maintain the vertical orientation of the assembly during lifting. At the topmost point of travel, the assembly is raised clear of the tube and is disengaged from the guide rails, allowing the assembly to pivot about its attachment to the lifting mechanism and assume an orientation favorable for launching the UAV.

Abstract translation: 提供了一种发射系统，其中无人驾驶飞行器固定在适于从浸没式平台发射的水密管中的平台上。 一旦启动，管上的侧面板被抛弃，并且布置浮选装置以将管带到表面。 当上升到表面时，浮选装置将管保持在垂直位置。 表面处理后，打开管子的顶盖。 管内的提升机构使垂直定向的平台组件向上升起。 导轨在升降过程中保持组件的垂直方向。 在最高点行程时，组件从管子上升起并与导轨分离，允许组件围绕其附接件枢转到提升机构，并采取有利于发射无人机的方向。

公开(公告)号：US20070108345A1

公开(公告)日：2007-05-17

申请号：US11510920

申请日：2006-08-28

Applicant: William McDonnell

Inventor： William McDonnell

IPC: B64F1/02

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无人机（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：US20070075185A1

公开(公告)日：2007-04-05

申请号：US11603810

申请日：2006-11-21

Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

IPC: B64F1/04

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.

公开(公告)号：US20070025809A1

公开(公告)日：2007-02-01

申请号：US11191094

申请日：2005-07-27

Applicant: Kang Lee ,  Thomas Forrester ,  Tomasz Jannson ,  Andrew Kostrzewski ,  Gajendra Savant

Inventor： Kang Lee ,  Thomas Forrester ,  Tomasz Jannson ,  Andrew Kostrzewski ,  Gajendra Savant

IPC: F16C11/00

CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/182 ,  H01R13/005 ,  H01R13/2421 ,  H01R35/04 ,  H01R39/64 ,  Y10T403/32606

Abstract: Two embodiments of a connector that can be mated without regard for its orientation are disclosed. One embodiment is mated and demated autonomously as part of a system for recovering, docking with, recharging and re-launching unmanned aerial vehicles. Another embodiment is employed on the decks of vessels to facilitate mating and demating of various equipment providing different functions to reconfigure the vessel. Because both embodiments are configured for connection irrespective of angular orientation over 360°, they are especially suited for harsh environments including autonomous operation, rough seas, darkness and the like.

Abstract translation: 公开了可以不考虑其取向而配合的连接器的两个实施例。 作为用于恢复，对接，再充电和重新发射无人驾驶飞行器的系统的一部分，一个实施例被自动地配合和排列。 在容器的甲板上采用另一个实施例，以便于提供不同功能的各种设备的配合和排气以重新配置容器。 由于两个实施例都被配置为连接，而不管角度取向超过360°，它们特别适用于恶劣的环境，包括自主操作，粗糙的海洋，黑暗等。

公开(公告)号：US07128294B2

公开(公告)日：2006-10-31

申请号：US10760150

申请日：2004-01-16

Applicant: Cory Roeseler ,  Andreas H. von Flotow

Inventor： Cory Roeseler ,  Andreas H. von Flotow

IPC: B64C3/56

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：US07059566B2

公开(公告)日：2006-06-13

申请号：US10856360

申请日：2004-05-27

Applicant: David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

Inventor： David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

IPC: B64C1/00

CPC classification number: B64C1/068 ,  B64C1/061 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/105 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D5/00

Abstract: A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

Abstract translation: 中空的椭圆柱形船体适合地容纳中空矩形棱柱舱，由此四个纵向平行的外边缘与前者的内表面接触。 完全构造的飞机（非动力或动力）包括一体的船体加舱结构以及与其结合的鼻，尾和翼型结构。 机舱适合容纳用于货物存储的中空矩形模块。 当鼻部和/或尾部结构与整体的船体 - 舱室结构脱离时，模块被插入到舱室中，舱室被密封。 飞机被提升（例如，通过飞机，直升机，火箭或气球）到特定的高度并被释放，于是两翼完全出现，并且飞机实现控制的飞行直到到达其目的地。 在着陆后，鼻部和/或尾部结构与整体式的船体 - 舱室结构脱离，舱室被开封，模块从舱室中取出。