公开(公告)号：US20140312169A1

公开(公告)日：2014-10-23

申请号：US14184542

申请日：2014-02-19

Applicant: AeroVironment, Inc.

Inventor： Christopher Eugene Fisher ,  Steven Bradley Chambers ,  Pavil Belik ,  Austin Craig Gunder ,  John Peter Zwaan

IPC: B64C5/02 ,  B64C39/00 ,  B64C9/00 ,  B64C3/10 ,  B64C39/12 ,  B64C5/06

CPC classification number: B64C5/02 ,  B64C3/10 ,  B64C5/06 ,  B64C9/00 ,  B64C39/00 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/22

Abstract: An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.

Abstract translation: 公开了一种具有机身悬臂的飞机装置，其具有近端和远端，联接到机身吊臂的近端的翼和连接到机身吊杆的远端的至少一个透明稳定器。

公开(公告)号：US20140203141A1

公开(公告)日：2014-07-24

申请号：US14247883

申请日：2014-04-08

Applicant: Aerovel Corporation

Inventor： Brian T. McGeer ,  Andreas H. von Flowtow ,  Corydon C. Roeseler

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/182 ,  B64F1/04 ,  B64F5/00

Abstract: For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy.

公开(公告)号：US08746620B1

公开(公告)日：2014-06-10

申请号：US13747626

申请日：2013-01-23

Applicant: Sunlight Photonics Inc.

Inventor： John Peter Moussouris ,  Sergey V. Frolov ,  Michael Cyrus

IPC: B64C3/30 ,  B64C1/34

CPC classification number: B64C1/34 ,  B64C3/30 ,  B64C3/46 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/105 ,  B64C2201/122 ,  B64D2211/00 ,  H01L31/0543 ,  H02S10/40 ,  H02S20/32 ,  Y02E10/52 ,  Y02T50/14

Abstract: Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes a solar PV system having at least one solar tracking system and being able to follow the sun position in order to increase sunlight collection and power output; and an expandable body having an aerodynamic cross-section that minimizes parasitic air drag at any given thickness of the body, further being at least partially transparent to sunlight, further enclosing the solar PV system, and further being able to change its shape in response to changes in the positions of the solar PV system.

Abstract translation: 本文提供了适用于太阳能机身的方法和装置。 在一些实施例中，适应性太阳能机身包括具有至少一个太阳能跟踪系统并且能够跟随太阳位置以增加阳光收集和功率输出的太阳能PV系统; 以及具有空气动力学横截面的可膨胀体，该空气动力学横截面最小化在本体的任何给定厚度的寄生空气阻力，进一步包围太阳能光伏系统，并进一步包围太阳能光伏系统，并且还能够响应于 太阳能光伏系统的位置变化。

公开(公告)号：US20140151508A1

公开(公告)日：2014-06-05

申请号：US13689853

申请日：2012-11-30

Applicant: WB Electronics S.A.

Inventor： WOJCIECH SZUMINSKI ,  Ryszard Jurecki ,  Grzegorz Krupa ,  Adam Bartosiewicz ,  Piotr Wojciechowski

IPC: B64D1/08

CPC classification number: B64D1/08 ,  B60V1/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/185 ,  B64C2201/187

Abstract: The mode of landing of an unmanned aerial vehicle driven by an electric engine, containing main power supply batteries, control systems of the surveillance head, transmitting and receiving systems, a flight control system, and a container equipped with a surveillance head with a looking down lens, placed in a recess situated in the lower part of the fuselage by which the vehicle is lightened at the last stage of flight shortly before landing, which means the container placed in the recess is detached, then moved outside the vehicle's body and descended by means of a parachute into a desired location, and the lightened vehicle lands in some other place. The recess in the fuselage contains an electrically controlled lock which fixes detachably the container equipped with at least one parachute placed at the bottom section of the container, on the side of the surveillance head.

Abstract translation: 由电动发动机驱动的无人驾驶飞机的模式，包含主电源电池，监视头的控制系统，发射和接收系统，飞行控制系统和装备有俯视监视头的集装箱 透镜放置在位于机身下部的凹部中，车辆在着陆前不久的最后阶段减轻，这意味着放置在凹槽中的容器被分离，然后移动到车身的外部并且下降 降落伞进入所需位置的方式，轻型车辆落在其他地方。 机身中的凹槽包含一个电控锁，其可拆卸地固定装备有至少一个放置在容器底部的降落伞的容器，在监视头的一侧。

公开(公告)号：US20140077028A1

公开(公告)日：2014-03-20

申请号：US13900191

申请日：2013-05-22

Applicant: Aerovel Corporation

Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Corydon C. Roeseler

IPC: B64F1/02 ,  B64F1/04 ,  B64F5/00

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/182 ,  B64F1/04 ,  B64F5/00

Abstract: For retrieval of a hovering aircraft, a cable bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separatod supports. The aircraft slowly flies into this fixture, which then sides along the aircraft in a direction approximately parallel with the aircraft's thrust. line.. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy.

Abstract translation: 为了检索悬停的飞行器，电缆杆或类似的固定装置在两个井分离支架之间跨越取回区域以大致水平的方向悬挂。 飞机慢慢地飞入这个固定装置，然后沿着飞机的方向与飞机的推力大致平行。 这导致飞机通过拦截器或飞机捕获器被固定到固定装置上，在替代实施例中，该拦截器或飞机捕获器分别在飞机或夹具上，或两者兼而有之。 然后减小推力，飞机从固定装置上休息，以便随后拆卸。 因此，采用简单经济的装置，飞机上的轻微不引人注意的元素，低损害风险，只有适度的驾驶准确性来实现检索。

公开(公告)号：US08672264B1

公开(公告)日：2014-03-18

申请号：US13717147

申请日：2012-12-17

Applicant: Aerovel Corporation

Inventor： Brian T. McGeer ,  Andreas H. Von Flotow ,  Corydon C. Roeseler

IPC: B64F1/02 ,  B64F1/04

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/182 ,  B64F1/04 ,  B64F5/00

Abstract: For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy.

Abstract translation: 为了检索悬停的飞行器，电缆，杆或类似的固定装置悬挂在两个分离好的支撑件之间的取回区域的大致水平的方向上。 飞机慢慢地飞入这个固定装置，然后沿着与飞机的推力线大致平行的方向沿飞机滑动。 这导致飞行器通过拦截器或飞行器捕获器被固定到固定装置上，在替代实施例中飞行器或飞机捕获器分别在飞行器或固定装置上或两者上。 然后减小推力，飞机从固定装置上休息，以便随后拆卸。 因此，在飞机上使用简单经济的装置，轻便和不引人注意的元件来实现检索，损坏风险低，而且只有适度的驾驶准确性。

公开(公告)号：US08662441B2

公开(公告)日：2014-03-04

申请号：US13367494

申请日：2012-02-07

Applicant: David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

Inventor： David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

IPC: B64F1/10

CPC classification number: B64C39/024 ,  B63G8/30 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/205

Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

Abstract translation: 用于发射无人机（UAV）有效载荷的系统包括发射管，液体火箭和发射控制组件。 火箭定位在发射管中，并包含无人机的有效载荷。 增压组件可以包括部分地填充有液体的罐。 气瓶内充满压缩气体。 液体被气体预加压或在发射前与气体混合，使得在发射时，液体和气体推进阶段将火箭发射到阈值高度。 无人机有效载荷在达到阈值高度后部署。 可选的稳定管可以连接到发射管，其可以浮动用于水基操作。 可选的系绳可以连接到液体火箭，以在达到远地点之前停止其飞行。 无人机有效载荷不直接由气/液混合发射。 还公开了一种启动无人机有效载荷的方法。

公开(公告)号：US20140054415A1

公开(公告)日：2014-02-27

申请号：US14034097

申请日：2013-09-23

Applicant: Aerovel Corporation

Inventor： Brian Theodore McGeer ,  Robert Joseph Heavey, III ,  Damon Lucas McMillan ,  John William Stafford

IPC: B64F1/02 ,  B64F5/00 ,  B64D37/00 ,  B64C39/02

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/182 ,  B64D37/00 ,  B64F5/00

Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched. In one embodiment, for retrieval, the aircraft drops a tether and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured b an end effector. The tether length is adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch, the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with a simple, economical apparatus. It can be used with low risk of damage and requires moderate accuracy in manual or automatic flight control.

Abstract translation: 可以自动检索，维修和启动能够推力飞行的飞机。 在一个实施例中，为了检索，飞行器降低系绳并且以相对较低的速度将系绳拉动以与水平引导件接触。 将系绳拉过引导件，直到引导件被捕获为末端执行器。 系绳长度根据需要进行调整，飞机在导轨上摆动，悬挂在倒立的位置。 沿着导轨翻转系绳，然后将飞机带到对接车厢，飞机停在其中，以便维修。 对于发射，托架正直摆动，末端执行器从引导件释放，飞机起飞进入自由飞行。 因此，可以使用简单，经济的装置自动完成完整的地面处理循环。 它可以在低风险的情况下使用，并且在手动或自动飞行控制中要求中等精度。

公开(公告)号：US20140021288A1

公开(公告)日：2014-01-23

申请号：US13569360

申请日：2012-08-08

Applicant: Andrew Charles ELSON ,  Peter Davison

Inventor： Andrew Charles ELSON ,  Peter Davison

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187 ,  B64D2211/00

Abstract: A method of launching a powered unmanned aerial vehicle at an altitude of at least 13,000 m, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

Abstract translation: 一种在至少13000米的高度上发射供电的无人驾驶飞行器的方法，该方法包括通过将空载承载装置从基本上地平面的位置附近提升到升高的高度，使得车辆 当车辆相对于承载件的速度基本上为零时，车辆离开载体，然后车辆随着其高度减小到能够防止任何进一步下降并且可以开始独立的持续飞行的速度。

公开(公告)号：US08584984B2

公开(公告)日：2013-11-19

申请号：US13620249

申请日：2012-09-14

Applicant: Robert Parks ,  Adam Woodworth ,  Peter Lively ,  Thomas Vaneck ,  Kimberly Kohlhepp ,  Justin McClellan

Inventor： Robert Parks ,  Adam Woodworth ,  Peter Lively ,  Thomas Vaneck ,  Kimberly Kohlhepp ,  Justin McClellan

IPC: B64C3/30

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/127

Abstract: A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

Abstract translation: 公开了一种可用于能够在85,000英尺或以上的高度操作的高空飞机的折叠翼。 可折叠翼可以采用螺旋折叠展开，其中可折叠翼的每个片段之间的铰链稍微偏离垂直线。 连续定位的翼片彼此折叠。 或者，铰链基本上垂直，使得每个相应的翼段相对于下一个翼段线性地折叠。 具有可充气臂的充气肋可以被充气以提供抵抗两个相邻臂的力，从而将翼段展开完整的180度旋转。