公开(公告)号：US20130261914A1

公开(公告)日：2013-10-03

申请号：US13538107

申请日：2012-06-29

Applicant: Benjamin T. INGRAM ,  Robert Ussery ,  William M. Yates, III

Inventor： Benjamin T. INGRAM ,  Robert Ussery ,  William M. Yates, III

IPC: G01C21/34 ,  B60W40/04 ,  B60W40/06 ,  B60W10/18

CPC classification number: B64D33/00 ,  B60W20/12 ,  B60W30/143 ,  B60W30/146 ,  B60W30/188 ,  B60W2050/0089 ,  B60W2520/10 ,  B60W2550/12 ,  B60W2550/20 ,  B60W2550/402 ,  B60W2710/083 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/187 ,  B64D27/24 ,  G01C21/3469

Abstract: A control system that makes adjustments, such as limiting the maximum speed or maximum torque in a vehicle, is provided. These adjustments can be based on knowledge about the vehicle and trip, and on the estimated energy remaining. The control system is applicable to a wide range of vehicles, including ground, air, water, and sea vehicles, as well as vehicles powered by battery, electricity, compressed natural gas, or even liquid fuel propulsion systems. The control system may be used to adjust vehicle operation in route to assure the vehicle reaches a destination and to inform or counteract a human vehicle operator. Control system can also be used in racing applications to calculate the fastest-possible race speed and drive torque for a given race length; or alternatively, in endurance racing or delivery applications to optimize the vehicle speed and/or drive torque for a given race length or route.

Abstract translation: 提供了进行调节的控制系统，例如限制车辆中的最大速度或最大扭矩。 这些调整可以基于关于车辆和行程的知识以及剩余的估计能量。 控制系统适用于各种车辆，包括地面，空气，水和海上车辆，以及由电池，电力，压缩天然气或甚至液体燃料推进系统供电的车辆。 控制系统可用于在路线中调整车辆操作，以确保车辆到达目的地并通知或抵消人类车辆操作者。 控制系统也可以用于赛车应用中，以计算给定的赛道长度的最快的赛车速度和驱动扭矩; 或者替代地，在耐力赛车或交付应用中，以针对给定的赛跑长度或路线优化车辆速度和/或驱动扭矩。

公开(公告)号：US08459591B2

公开(公告)日：2013-06-11

申请号：US13465220

申请日：2012-05-07

Applicant: Kevin Reed Lutke ,  Aaron J. Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron J. Kutzmann

IPC: B64F1/04

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/206

Abstract: Methods and systems are provided which may allow a first vehicle to recover a second air vehicle while both are moving. The first vehicle and the second air vehicle may be traveling at different velocities. An attachment member of the second air vehicle may attach to a recovery member of the first vehicle while the first vehicle and the second air vehicle are traveling at different velocities. The recovery member attached to the second air vehicle may move relative to and along an exterior surface of the first vehicle in a direction substantially parallel to a direction of travel of the first vehicle.

Abstract translation: 提供了方法和系统，其可以允许第一车辆在移动时都恢复第二空中车辆。 第一车辆和第二空中车辆可以以不同的速度行驶。 当第一车辆和第二空中车辆以不同的速度行驶时，第二空中车辆的附接构件可以附接到第一车辆的回收构件。 附接到第二空气车辆的回收构件可以在与第一车辆的行进方向基本平行的方向上相对于第一车辆的外表面移动并沿其移动。

公开(公告)号：US20130104966A1

公开(公告)日：2013-05-02

申请号：US13286202

申请日：2011-10-31

Applicant: Robert Erik Grip ,  Blaine Knight Rawdon ,  Tab Hunter Crooks ,  Michael F. Stola

Inventor： Robert Erik Grip ,  Blaine Knight Rawdon ,  Tab Hunter Crooks ,  Michael F. Stola

IPC: H01L31/048 ,  H01L31/18

CPC classification number: H01L31/0422 ,  B64C2201/021 ,  B64C2201/042 ,  B64D2211/00 ,  H01L31/042 ,  H02S10/40 ,  H02S20/00 ,  Y02B10/20 ,  Y02E10/50

Abstract: In an embodiment of the disclosure, there is provided a strain isolation layer assembly. The assembly has a rigid solar layer; a strain isolation layer having a discontinuous configuration, a vertical rigidity, and a horizontal shear flexibility; and an underlying substrate layer. The strain isolation layer is coupled between the rigid solar layer and the underlying substrate layer to form a strain isolation layer assembly, such that the strain isolation layer isolates the rigid solar layer to reduce one or more strains induced on the rigid solar layer.

Abstract translation: 在本公开的一个实施例中，提供了应变隔离层组件。 该组件具有刚性的太阳能层; 具有不连续构型，垂直刚性和水平剪切挠度的应变隔离层; 和底层基底层。 应变隔离层耦合在刚性太阳能层和下面的基底层之间以形成应变隔离层组件，使得应变隔离层隔离刚性太阳能层以减少在刚性太阳能层上诱发的一种或多种应变。

公开(公告)号：US20130018532A1

公开(公告)日：2013-01-17

申请号：US13182065

申请日：2011-07-13

Applicant: Matthew Jonathan Segal ,  Kevin Andrew Wise

Inventor： Matthew Jonathan Segal ,  Kevin Andrew Wise

IPC: G06F19/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/141 ,  B64D27/24 ,  B64D2211/00 ,  G05D1/0005 ,  Y02T50/62

Abstract: A method and apparatus for managing solar power collection. A position of the sun is identified relative to an aerospace vehicle while the aerospace vehicle is moving along a flight path. A level of power generation is identified by a solar power generation system while the aerospace vehicle moves along the flight path using a threat management module and equivalent radar signature data. The threat management module uses the equivalent radar signature data to identify the level of power generation by the aerospace vehicle from different positions of the sun relative to the aerospace vehicle, and the equivalent radar signature data is based on solar power generation signature data identifying the level of power generation for the different positions of the sun relative to the aerospace vehicle. A change in the flight path that results in a desired level of power generation is identified by the solar power generation system.

Abstract translation: 一种用于管理太阳能集热的方法和装置。 当航空航天器沿着飞行路径移动时，相对于航空航天车辆识别太阳的位置。 太阳能发电系统确定发电水平，而航空航天飞行器使用威胁管理模块和等效雷达签名数据沿飞行路线移动。 威胁管理模块使用等效雷达签名数据来识别航空航天器从太阳相对于航空航天车辆的不同位置的发电水平，等效雷达签名数据基于识别水平的太阳能发电签名数据 的太阳相对于航空航天车辆的不同位置的发电。 由太阳能发电系统识别导致所需发电水平的飞行路径的变化。

公开(公告)号：US20120325965A1

公开(公告)日：2012-12-27

申请号：US13516453

申请日：2010-12-17

Applicant: Alfram V. Bright ,  Richard Wlezien

Inventor： Alfram V. Bright ,  Richard Wlezien

IPC: B64C3/30 ,  B64C3/56

CPC classification number: B64C3/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/127 ,  D06M10/001 ,  D06M10/10 ,  D06M15/327 ,  E04H12/00 ,  F03D13/20 ,  H05G2/00 ,  Y02E10/728

Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements which find use in rapidly deploying and supporting the wing of an aerial vehicle.

Abstract translation: 本发明提供了新颖的可膨胀和可固化的支撑元件，及其制造和使用方法。 特别地，本发明提供了充气和可固化的支撑元件，其可用于快速展开和支撑飞行器的机翼。

公开(公告)号：US08333348B1

公开(公告)日：2012-12-18

申请号：US12705691

申请日：2010-02-15

Applicant: Gerald D. Miller

Inventor： Gerald D. Miller

IPC: B64C23/00

CPC classification number: B64C13/16 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/44

Abstract: The disclosure provides in one embodiment a wing tip device for a wing of an air vehicle. The device comprises a tip tail element, a boom element attaching the tip tail element to a wing tip, a hinge element connecting the tip tail element to the boom element, and an actuator element connected to the hinge element. One or more wing load sensors sense wing loads, and a flight control system controls the actuator element. A load alleviation method and system for an air vehicle are also provided.

Abstract translation: 本公开在一个实施例中提供了用于机动车辆的机翼的翼尖装置。 该装置包括尖端尾部元件，将尖端尾部元件附接到翼尖的吊杆元件，将末端尾部元件连接到吊杆元件的铰链元件以及连接到铰链元件的致动器元件。 一个或多个机翼负载传感器感测机翼负载，飞行控制系统控制致动器元件。 还提供了一种用于空中交通工具的负载减轻方法和系统。

公开(公告)号：US08322650B2

公开(公告)日：2012-12-04

申请号：US12847004

申请日：2010-07-30

Applicant: Christopher Charles Kelleher

Inventor： Christopher Charles Kelleher

IPC: B64C39/12

CPC classification number: B64C39/024 ,  B64C23/069 ,  B64C23/076 ,  B64C2201/021 ,  B64C2201/126 ,  Y02T50/164

Abstract: An aircraft, particularly a solar powered, high altitude, long endurance, unmanned aerial vehicle, is equipped with a combination of canted down, raked back wing tips and trailing “tip tails” carried on booms from the tip regions of the mainplane. Each tip tail is positioned to be subject to the upwash field of the respective wing tip vortex, at least in the cruise condition of the aircraft. The wing tip form can achieve a reduction in induced drag and help to relieve wing root bending moment while the tip tails can act through their connections to the mainplane to provide torsional relief to the latter, particularly under lower incidence/higher speed conditions. In the higher incidence/lower speed cruise condition, however, the presence of the tip tails in the upwash fields of the wing tip vortices means that they can generate lift with a component in the forward direction of flight and hence contribute to the thrust requirements of the aircraft.

Abstract translation: 飞机，特别是太阳能，高空，长寿命，无人驾驶飞行器，配备有从主板的尖端区域承载在悬臂上的倾斜下倾斜后翼翼尖和尾尖尾的组合。 至少在飞行器的巡航条件下，每个末梢尾部定位成受到相应的翼尖涡流的上洗液场的影响。 翼尖形式可以实现诱导阻力的减小，并且有助于减轻翼根弯曲力矩，同时尖端尾部可以通过它们与主平面的连接而起作用，以向后者提供扭转释放，特别是在较低的入射/更高速度条件下。 然而，在较高的发生率/较低速度的巡航条件下，翼尖涡流的上冲流场中尖端尾部的存在意味着它们可以在飞行方向上产生具有部件的升力，因此有助于推力要求 飞机。

公开(公告)号：US20120138727A1

公开(公告)日：2012-06-07

申请号：US13097394

申请日：2011-04-29

Applicant: Jeremy F. Fisher

Inventor： Jeremy F. Fisher

IPC: F42B15/01 ,  B64D1/02 ,  B64C3/56 ,  F42B10/14

CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。

公开(公告)号：US20120048990A1

公开(公告)日：2012-03-01

申请号：US13154796

申请日：2011-06-07

Applicant: Geoffrey S. SOMMER

Inventor： Geoffrey S. SOMMER

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

Abstract: Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

Abstract translation: 提供了用于形成具有高纵横比翼平台的多关节飞行系统（天基）的系统和/或方法，其可操作以在高海拔地区的感兴趣区域上游荡。 在某些示例性实施例中，自主模块化飞行器以翼尖到翼尖的方式连接在一起。 这样的模块化飞行器可以从日晒中获得其功率。 自主传单可以包括单独操作的传感器，或者在形成天空基础之后集体运行。 天空基优选地可以按照主要条件的要求进行聚合，分解和/或再聚集。 因此，可能提供“永远在车”的飞机。

公开(公告)号：US20110168838A1

公开(公告)日：2011-07-14

申请号：US12799297

申请日：2010-04-21

Applicant: William Hornback ,  Michael Holly

Inventor： William Hornback ,  Michael Holly

IPC: B64F1/04

CPC classification number: B64C39/028 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  F41A23/42 ,  F41B7/00 ,  F41B11/62 ,  F41F3/042 ,  F41F3/052 ,  F41F7/00 ,  F42B10/16 ,  F42B15/08

Abstract: An unmanned aerial surveillance and reconnaissance system are disclosed wherein an unmanned aerial vehicle is launchable from a launch tube, for instance, the bore of an existing weapons system mounted on a mobile vehicle, such as a weapon barrel of a tank or armored combat vehicle and which the launch may be remotely initiated from the protected armored compartment of the mobile vehicle.

Abstract translation: 公开了一种无人驾驶的空中监视和侦察系统，其中无人驾驶飞行器可从发射管发射，例如安装在诸如坦克或装甲战斗车辆的武器枪的移动车辆上的现有武器系统的钻孔， 该发射可以从移动车辆的受保护的装甲舱远程地发起。