公开(公告)号：US20130062457A1

公开(公告)日：2013-03-14

申请号：US13636583

申请日：2011-03-22

Applicant: Nicholas James Deakin

Inventor： Nicholas James Deakin

IPC: B64B1/62 ,  H01L31/0232 ,  H01Q1/28 ,  B64B1/20

CPC classification number: B64B1/02 ,  B64B1/08 ,  B64B1/10 ,  B64B1/12 ,  B64B1/14 ,  B64B1/20 ,  B64B1/38 ,  B64B1/64 ,  B64B2201/00 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  H01Q1/36 ,  H01Q9/27

Abstract: An aerial vehicle is described which comprises: a first compartment for holding a lighter than air gas; a second compartment for holding atmospheric air and having an inlet and an outlet; a solar panel for converting sunlight into electricity; a compressor for pumping atmospheric air through the inlet into the second compartment; control means for controlling the pitch and yaw of the vehicle; and a controller for controlling the buoyancy of the vehicle via the compressor and the outlet such that the vehicle is either lighter than the surrounding air and rising or heavier than the surrounding air and falling, and for controlling the control means such that the rising and falling motion includes a horizontal component. In another embodiment the solar panel is replaced by an engine and a fuel tank for storing fuel for the engine is also provided.The aerial vehicle can remain airborne for extended periods by using buoyancy propulsion.In the embodiments including a solar panel, a system including a light transmission station may be provided to supply energy to the solar panel from the light transmission station rather than relying on the incident sunlight alone.A method of flight using buoyancy propulsion is also described.

Abstract translation: 描述了一种飞行器，其包括：用于保持比空气气体轻的第一隔室; 用于容纳大气并具有入口和出口的第二隔室; 用于将阳光转化为电的太阳能电池板; 用于将大气通过所述入口泵送到所述第二隔室中的压缩机; 用于控制车辆的俯仰和偏航的控制装置; 以及用于经由压缩机和出口控制车辆的浮力的控制器，使得车辆比周围空气要轻，并且比周围空气上升或者重，并且下降，并且用于控制控制装置使得上升和下降 运动包括水平分量。 在另一个实施例中，太阳能电池板被发动机代替，并且还提供了用于储存用于发动机的燃料的燃料箱。 航空器可以通过使用浮力推进长时间保持空中。 在包括太阳能电池板的实施例中，可以提供包括光传输站的系统，以从光传输站向太阳能电池板提供能量，而不是仅依赖于入射的太阳光。 还描述了使用浮力推进的飞行方法。

公开(公告)号：US20100308161A1

公开(公告)日：2010-12-09

申请号：US12804988

申请日：2010-08-02

Applicant: Greg T. Kendall ,  Derek L. Lisoski ,  Walter R. Morgan ,  John A. Griecci

Inventor： Greg T. Kendall ,  Derek L. Lisoski ,  Walter R. Morgan ,  John A. Griecci

IPC: B64C3/38

CPC classification number: B64C3/38 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C17/00 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55

Abstract: A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.

公开(公告)号：US07281681B2

公开(公告)日：2007-10-16

申请号：US10600258

申请日：2003-06-20

Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

IPC: B64D27/00

CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

公开(公告)号：US06931247B2

公开(公告)日：2005-08-16

申请号：US09789450

申请日：2001-02-20

Applicant: Earl C. Cox ,  Kyle D. Swanson

Inventor： Earl C. Cox ,  Kyle D. Swanson

IPC: B64C39/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  G05D1/00 ,  H04B7/185 ,  H04Q7/20

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Traveling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft includes hinges and actuators capable of providing an adjustable dihedral for the wing. The actuators can be motors or control surfaces. Alternately, the actuators can be movable masses within the wing, which may be capable of deforming the wing to alter the aerodynamics of the wing, and thereby actuate the hinges. Because of wing dihedral, the aircraft includes motors both above and below the center of drag, and the aircraft uses differential thrust to control aircraft pitch. The aircraft has a wide variety of applications, which include serving as a long term high altitude platform that serves to link a ground station using radio wave signals and a satellite using optical signals.

Abstract translation: 本公开提供了一种太阳能可再充电飞机，其生产便宜，是可操纵的，并且几乎可以无限期地保持空中飞行。 首选飞机是一个装有跨距的飞翼，没有机身或方向舵。 以相对较慢的速度行驶，并且拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差动推力来转动。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。 飞机包括铰链和致动器，能够为机翼提供可调节的二面体。 执行器可以是电机或控制面。 或者，致动器可以是机翼内的可移动质量块，其可以使机翼变形以改变机翼的空气动力学，从而致动铰链。 由于机翼二面体，飞机包括在阻力中心上方和下方的电机，飞机使用差速推力来控制飞机俯仰。 该飞机具有广泛的应用，其中包括作为长期高空平台，用于使用无线电波信号连接地面站和使用光信号的卫星。

公开(公告)号：US20030025034A1

公开(公告)日：2003-02-06

申请号：US10189796

申请日：2002-07-03

Inventor： Yutaka Akahori

IPC: B64B001/02 ,  B64B001/06

CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

Abstract translation: 根据本发明的飞艇系统具有飞艇（110），基站（120）和至少三个测量点。 飞艇（110）在接收到来自基站（120）的指令时发射超声波。 测量点单元（S1-S3）接收超声波，从而测量从飞艇（110）到相应测量点的距离。 并入基站（120）的MPU计算飞艇（110）的位置。 基站（120）通过向飞艇（110）发送飞行指令，基于计算出的位置来控制飞艇（110）的路线。 以这种方式，可以提供一种飞艇系统，使得飞行员不需要飞行飞艇，并且可以减少飞艇的负载重量和功率消耗。

公开(公告)号：WO2019105857A1

公开(公告)日：2019-06-06

申请号：PCT/EP2018/082351

申请日：2018-11-23

Applicant: BRITISH TELECOMMUNICATIONS PUBLIC LIMITED COMPANY

Inventor： GHOSH, Ayan

IPC: B64C39/02 ,  H04B7/185

CPC classification number: B64C39/022 ,  B64C2201/027 ,  B64C2201/06 ,  B64C2201/122 ,  B64C2201/148 ,  H04B7/18504

Abstract: An unmanned aircraft such as a tethered drone has an electrical power connection (10) for receiving electrical power from a remote source, and a power delivery system for delivering electrical power to onboard applications equipment (14) such as radio transmitters (5, 6). To ensure that ground staff are not exposed to high levels of radiation from the transmitters, power is only delivered to the communications equipment after the aircraft has left the ground. A sensor (13) associated with the aircraft's undercarriage may be used to detect when the aircraft is airborne. The applications equipment (14) is powered from an accumulator which is only charged up from the power supply (10) after launch. In the event of a failure of the power supply (10) when airborne, the output of the accumulator is diverted to control propulsion and flight control systems (17), which are normally powered directly from the power supply (10), to allow a controlled descent, and thus shutting off the applications equipment (14) before the aircraft returns to proximity to personnel on the ground.

公开(公告)号：WO2018226412A1

公开(公告)日：2018-12-13

申请号：PCT/US2018/034203

申请日：2018-05-23

Applicant: SET POINT SOLUTIONS, LLC

Inventor： BROWN, Joseph Harrington Matanane

IPC: F42B12/36 ,  F42B5/02 ,  F42B10/56 ,  F42B12/02 ,  F42B12/62 ,  F42B15/00

CPC classification number: H04B7/18502 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/122 ,  B64D17/76 ,  F42B12/365 ,  F42B15/08

Abstract: The present disclosure describes a signal relay node that is physically displaceable by a delivery system to move the signal relay node to a different location, to enable the signal relay node to overcome physical obstructions to signal propagation. A delivery system, such as a launching system, can launch the signal relay node encased within a housing unit, such as a projectile cap. Upon launch into the air, an additional aloft package may provide an aerostat, parachute, and/or a propeller and motor system to keep the signal relay node aloft in the air for a longer period of time.

公开(公告)号：WO2017130137A1

公开(公告)日：2017-08-03

申请号：PCT/IB2017/050422

申请日：2017-01-26

Applicant: OPENSTRATOSPHERE SA

Inventor： BROWN, Dave ,  JOHNSON, Simon ,  TISCHHAUSER, Frederick

IPC: B64C39/02 ,  B64D27/24

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2211/00 ,  B64D27/24 ,  B64D2211/00 ,  Y02T50/44 ,  Y02T50/62

Abstract: A stratospheric drone able to operate at an altitude between 17 km and 23 km(ISA), said stratospheric drone comprising: one fuselage; at least two wings; at least one tail;at least two motors and two corresponding propellers; at least one accumulator in each of said wings, so as to partly compensate the lift force on said wings with the weight of the accumulators in said wings; a payload pod at the front of the fuselage, for housing a removable payload,wherein the structure of the drone is designed and optimized for transporting a payload having a maximal mass between 20 and 50 kg.

Abstract translation: 平流层无人机能够在17公里和23公里之间的高度运行（ISA），所述平流层无人机包括：一个机身; 至少两个翅膀; 至少一个尾部;至少两个电机和两个相应的螺旋桨; 在每个所述机翼中至少有一个蓄能器，以便利用所述机翼中蓄能器的重量部分地补偿所述机翼上的升力; 机身前部的有效载荷舱，用于容纳可移动的有效载荷，其中无人驾驶飞机的结构被设计和优化用于运输最大质量在20和50kg之间的有效载荷。

公开(公告)号：WO2017105657A1

公开(公告)日：2017-06-22

申请号：PCT/US2016/060146

申请日：2016-11-02

Applicant: SKYCOM CORPORATION

Inventor： MICHAELIS IV, Max, G. ,  BENNETT, John, H. H.

IPC: B64B1/00 ,  B64B1/02 ,  B64B1/40 ,  B64B1/44 ,  B64B1/58 ,  B64B1/62

CPC classification number: H02S20/32 ,  B64B1/12 ,  B64B1/30 ,  B64B1/58 ,  B64B1/62 ,  B64C2201/022 ,  B64C2201/122 ,  B64C2201/208 ,  H02S10/40 ,  H02S30/20

Abstract: Techniques are disclosed relating lighter-than-air aircraft. Such aircraft may be used for various purposes, such as providing network connectivity to areas that would otherwise lack such connectivity. For example, in some embodiments, a lighter-than-air aircraft according to this disclosure may include various types of antennas (directional or non-directional) for communicating with ground-based electronics or with other lighter-than-air aircraft.

Abstract translation: 所公开的技术涉及轻于空气的飞机。 这种飞机可以用于各种目的，例如提供网络连接到本来缺乏这种连接的地区。 例如，在一些实施例中，根据本公开内容的比空中轻的飞机可以包括用于与地面电子设备或与其他轻于空气的飞行器通信的各种类型的天线（定向或非定向的）。 p>

公开(公告)号：WO2017080600A1

公开(公告)日：2017-05-18

申请号：PCT/EP2015/076415

申请日：2015-11-12

Applicant: SONY MOBILE COMMUNICATIONS INC. ,  LJUNG, Rickard

Inventor： LJUNG, Rickard ,  YING, Zhinong ,  TRANG, Linh ,  KARLSSON, Peter C. ,  PERSSON, Magnus

IPC: H04W16/26

CPC classification number: H04W16/18 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/122 ,  H04B7/18504 ,  H04W16/24 ,  H04W16/26 ,  H04W24/02 ,  H04W36/22 ,  H04W36/32 ,  H04W84/005

Abstract: Apparatus (200), systems, and methods are disclosed for determining dynamic positioning of mobile cells (200). Dynamic positioning provides for navigating a mobile cell (200), such as an unmanned aerial vehicle or the like, to a location suitable for offloading current network traffic, such that the suitable location maximizes offloading capabilities. The methodology described takes into account both the current traffic load on the network and the location of the highest system capacity-intensive mobile terminals (218) in determining an initial position for deploying the mobile cell (200). Additionally, the location of the deployed mobile cell (200) is optimized, over time, based on tracking the direction of movement (222) of the highest capacity-intensive mobile terminals (218), and, in some embodiments, service quality indicators provided by the mobile terminals and/or contextual information captured by the mobile cell apparatus (200).

Abstract translation: 公开了用于确定移动小区（200）的动态定位的设备（200），系统和方法。 动态定位提供将诸如无人驾驶飞行器等的移动小区（200）导航到适于卸载当前网络业务的位置，使得合适的位置最大化卸载能力。 所描述的方法在确定用于部署移动小区（200）的初始位置时考虑了网络上的当前业务负载以及最高系统容量密集型移动终端（218）的位置。 此外，基于跟踪最高容量密集型移动终端（218）的移动方向（222），随着时间的推移优化部署的移动小区（200）的位置，并且在一些实施例中，提供的服务质量指示符 通过移动终端和/或由移动小区设备（200）捕获的上下文信息。