公开(公告)号：WO2013052178A2

公开(公告)日：2013-04-11

申请号：PCT/US2012/041782

申请日：2012-06-09

Applicant: LASERMOTIVE, INC. ,  NUGENT, Tom ,  BASHFORD, David ,  KARE, Jordin, T.

Inventor： NUGENT, Tom ,  BASHFORD, David ,  KARE, Jordin, T.

IPC: H04J14/06

CPC classification number: H02J50/30 ,  B64B1/50 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/148 ,  B64F3/00 ,  B64F3/02 ,  H02J7/025 ,  H02J17/00 ,  H02J50/40 ,  H04B10/807

Abstract: An aerial platform receives power in the form of light, for example laser light, transmitted via an optical fiber from a remote optical power source. The platform comprises a receiver which converts at least a portion of the light to a different form of power, for example electric power. The platform also comprises a propulsion element which consumes the different form of power to generate propulsive thrust. Supplying power to the aerial platform from a remote source enables the platform to remain aloft longer than a battery or fuel tank carried by the platform would allow. Transmitting the power in the form of light is preferable in many cases to transmitting electric power, because electrical conductors are generally heavier than optical fibers, and are hazardous in the presence of lightning or a high-voltage power line.

Abstract translation: 空中平台通过光纤从远程光功率源接收以光的形式（例如激光）的功率。 平台包括将至少一部分光转换成不同形式的功率（例如电力）的接收器。 该平台还包括消耗不同形式的动力以产生推进推力的推进元件。 从远程电源向空中平台供电可使平台比平台承载的电池或燃料箱更长时间保持高度。 由于电导体通常比光纤重，所以在许多情况下以光的形式发射功率在传输电力方面是优选的，并且在存在雷电或高压电力线的情况下是危险的。

公开(公告)号：WO2012118731A2

公开(公告)日：2012-09-07

申请号：PCT/US2012/026716

申请日：2012-02-27

Applicant: CIAMPA, John, A.

Inventor： CIAMPA, John, A.

IPC: B64B1/58

CPC classification number: B64C39/024 ,  B64B1/62 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/127 ,  B64C2201/146 ,  B64D47/08

Abstract: Lighter-than-air systems, methods, and kits for obtaining aerial images are described. For example, various methods for determining planned ascent, drift, and/ or descent of a lighter-than-air system are described. In addition, various structural arrangements of lighter-than-air systems for accomplishing planned ascent, drift, and/or descent and obtaining aerial images are described.

Abstract translation: 描述了用于获取航拍图像的比空中轻的系统，方法和套件。 例如，描述了用于确定轻于空气系统的计划上升，漂移和/或下降的各种方法。 另外，描述了用于完成计划上升，漂移和/或下降以及获得航拍图像的轻于空气系统的各种结构布置。

公开(公告)号：WO2009029367A2

公开(公告)日：2009-03-05

申请号：PCT/US2008071231

申请日：2008-07-25

Applicant: NEAR SPACE SYSTEMS INC ,  CHU ADAM N

Inventor： CHU ADAM N

IPC: B64B1/02

CPC classification number: B64D17/025 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/185

Abstract: An orientation system is disclosed for a lighter-than-air aircraft having a lower stage suspended from an envelope. The orientation system includes a swivel and a plurality of thrust generators. The swivel is affixed between the envelope and the lower stage. The swivel is oriented for allowing the lower stage to rotate with respect to the envelope. The plurality of thrust generators are affixed to the lower stage. At least some of the trust generators generating differential thrust produces a change in rotation of the lower stage with respect to the envelope.

Abstract translation: 公开了一种具有从信封悬挂的较低级的轻型飞机的定向系统。 定向系统包括旋转件和多个推力发生器。 旋转体固定在信封和下层之间。 旋转件被定向成允许下阶段相对于外壳旋转。 多个推力发生器固定在下阶段。 产生差分推力的信任发生器中的至少一些相对于包络产生下阶段的旋转变化。

公开(公告)号：WO2004100289A8

公开(公告)日：2005-11-10

申请号：PCT/US2004013895

申请日：2004-05-05

Applicant: ION AMERICA CORP ,  MCELROY JAMES FREDERICK ,  SRIDHAR K R

Inventor： MCELROY JAMES FREDERICK ,  SRIDHAR K R

IPC: B64B1/62 ,  B64C39/02 ,  B64D27/24 ,  H01M20060101 ,  H01M8/04 ,  H01M8/12 ,  H01M8/18

CPC classification number: H01M8/186 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/101 ,  B64C2201/127 ,  B64C2201/148 ,  B64C2201/165 ,  B64D27/24 ,  B64D2041/005 ,  B64D2211/00 ,  H01M8/04007 ,  H01M8/2475 ,  H01M2250/20 ,  Y02E60/528 ,  Y02T50/44 ,  Y02T50/62 ,  Y02T50/69 ,  Y02T90/32 ,  Y02T90/36 ,  Y10S429/901

Abstract: A neutral buoyant airship, such as a blimp, contains a lifting body which allows the airship to remain neutrally buoyant in air and fuel cell located in the airship. A method of generating power in the neutrally buoyant airship, comprising providing a fuel and a oxidizer to a solid oxide fuel cell to generate power, and providing heat from the fuel cell to a remotely located lifting body, wherein the lifting body allows the airship to remain neutrally buoyant in air.

Abstract translation: 一个中性浮力的飞艇，如飞艇，包含一个提升体，允许飞艇在位于飞艇的空气和燃料电池中保持中性浮力。 一种在中性浮力飞艇中产生动力的方法，包括向固体氧化物燃料电池提供燃料和氧化剂以产生动力，并将热量从燃料电池提供到位于远处的提升体，其中提升体允许飞艇 在空气中保持中性浮力。

公开(公告)号：WO2004000642A1

公开(公告)日：2003-12-31

申请号：PCT/CA2003/000945

申请日：2003-06-25

Applicant: 21ST CENTURY AIRSHIPS INC. ,  COLTING, Hokan

Inventor： COLTING, Hokan

IPC: B64B1/00

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 (20) has a generally spherical shape and has an internal envelope (24) for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system (36, 38) 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 (180) 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 (44, 46) of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit (52) 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（20）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封壳（24）。 飞艇有一个推进和控制系统（36,38），允许飞行到期望的游荡地点，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7％时，飞艇可以实现中性浮力，并且可以具有约6万英尺的服务天花板。飞艇具有可以包括通信设备 ，或监控设备，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机（44,46）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（52）。 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：US20230227157A1

公开(公告)日：2023-07-20

申请号：US17852101

申请日：2022-06-28

Applicant: Hyundai Motor Company ,  Kia Corporation

Inventor： Jung Hun CHOI ,  Dong Hyun Ha ,  Jae Wung Jung

IPC: B64C39/02 ,  F03D9/32 ,  B64B1/62 ,  B64C3/56 ,  B64D27/24 ,  B64D47/00 ,  B64C13/28 ,  B64C11/18 ,  H02K7/18

CPC classification number: B64C39/024 ,  F03D9/32 ,  B64B1/62 ,  B64C3/56 ,  B64D27/24 ,  B64D47/00 ,  B64C13/28 ,  B64C11/18 ,  H02K7/183 ,  F05B2220/706 ,  B64C2201/042 ,  B64C2201/022

Abstract: An aero wind power generation apparatus includes: a drone unit including drone wings configured to make the aero wind power generation apparatus move and hover and a sensor unit configured to detect information for controlling the aero wind power generation apparatus; a buoyancy generation unit connected to the drone unit and including a side cover configured to open or close and a balloon provided inside the side cover, wherein the buoyancy generation unit is configured to enable injection of gas into or release of the gas from the balloon; and a power generation unit connected to the buoyancy generation unit and including a rotating unit with a plurality of blades, a blade control unit of adjusting the state of the blades, and a motor unit of converting kinetic energy transferred from the rotating unit into electrical energy.

公开(公告)号：US20190210725A1

公开(公告)日：2019-07-11

申请号：US16352694

申请日：2019-03-13

Applicant: Walmart Apollo, LLC

Inventor： Robert L. Cantrell ,  John P. Thompson ,  David C. Winkle ,  Michael D. Atchley ,  Donald R. High ,  Todd D. Mattingly ,  John J. O'Brien ,  John F. Simon

IPC: B64C39/02 ,  B64C33/02 ,  B64C3/56 ,  B64C3/42

CPC classification number: B64C39/024 ,  B64C3/42 ,  B64C3/56 ,  B64C33/02 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/025 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/14 ,  B64C2201/162

Abstract: Systems, apparatuses, and methods are provided herein for unmanned flight optimization. A system for unmanned flight comprises a set of motors configured to provide locomotion to an unmanned aerial vehicle, a set of wings coupled to a body of the unmanned aerial vehicle via an actuator and configured to move relative to the body of the unmanned aerial vehicle, a sensor system on the unmanned aerial vehicle, and a control circuit. The control circuit being configured to: control the unmanned aerial vehicle, cause the set of motors to lift the unmanned aerial vehicle, detect condition parameters based on the sensor system, determine a position for the set of wings based on the condition parameters, and cause the actuator to move the set of wings to the wing position while the unmanned aerial vehicle is in flight.

公开(公告)号：US20190210723A1

公开(公告)日：2019-07-11

申请号：US15863018

申请日：2018-01-05

Applicant: Raytheon Company

Inventor： Gregory W. Heinen

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64B1/34 ,  B64B1/44 ,  B64B1/54 ,  B64B1/70 ,  B64B2201/00 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/12 ,  G01S7/4004 ,  G01S7/4052 ,  G01S2007/4082 ,  H01Q1/082 ,  H01Q1/2291 ,  H01Q1/28 ,  H01Q1/34

Abstract: A flight vehicle includes a drone with a pair of shaped protrusions mechanically coupled to the drone. One of the shapes is a hollow lift-producing shape, such as being a balloon filed with a lighter-than-air gas, and the other of the shapes is below the drone. The shape below the drone may be a hollow shape that does not produce lift, for example being a balloon filled with air. The shapes may be similar in size and shape, so as to provide similar drag characteristics. The shapes may be opposite ends of a support, such as a stick, rod, or other (relatively) slender structure. The vehicle includes a payload, such as radar calibration equipment or an antenna. The drone may be used to counteract wind forces on the flight vehicle, and/or to otherwise position the flight vehicle.

公开(公告)号：US20180327070A1

公开(公告)日：2018-11-15

申请号：US15774246

申请日：2016-03-24

Applicant: Hossein RAHNAMA

Inventor： Hossein RAHNAMA

IPC: B64B1/40 ,  G05D1/00 ,  B64C39/02 ,  G06F3/147 ,  H04B1/3888

CPC classification number: B64B1/40 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  G05D1/0094 ,  G06F3/147 ,  H04B1/3888 ,  H04M1/72527

Abstract: According to embodiments described in the specification, a hover attachment includes a housing operable to receive a mobile device having a processor, a memory, and a display, at least one sensor operable to detect a position parameter of the mobile device relative to an object under tracking, and a regulator operable to maintain, responsive to the detecting, the mobile device in a hover relation to the object under tracking, wherein the display of the mobile device is a situational display. An exemplary method includes providing a situational display interface on a display of a mobile device mounted in a hover attachment, detecting a movement of an object under tracking in hover relation to the mobile device, and when the detected movement is associated with a position change function, controlling the hover attachment to maintain the hover relation between the mobile device and the object under tracking.

公开(公告)号：US20180319477A1

公开(公告)日：2018-11-08

申请号：US15972087

申请日：2018-05-04

Applicant: Andrew X. Yakub

Inventor： Andrew X. Yakub

IPC: B64B1/58 ,  B64B1/70 ,  H01M8/18 ,  B64C39/00 ,  B64D27/24

CPC classification number: B64B1/58 ,  B64B1/70 ,  B64C39/001 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/066 ,  B64D27/24 ,  B64D2027/026 ,  B64D2041/005 ,  B64D2211/00 ,  H01M8/186 ,  H01M2250/20

Abstract: The zero carbon emission vehicle as disclosed herein may include a condenser for extracting fluid water from the atmosphere, an electrolyzer for generating hydrogen from the fluid water, and one or more deformable fluid-retaining chambers that couple thereto for selectively adjusting the buoyancy and altitude of the zero carbon emission vehicle in real-time, to maintain the air vehicle in flight substantially without needing to land and refuel the air vehicle. Solar panels provide the energy for the described systems, and the energy from the solar panels can be stored in the form of hydrogen gas which gives buoyancy to the air vehicle.