公开(公告)号：US11840358B2

公开(公告)日：2023-12-12

申请号：US17689960

申请日：2022-03-08

申请人： Brian Zima ,  Kristof Jebens ,  Agalya Jebens

发明人： Brian Zima ,  Kristof Jebens ,  Agalya Jebens

IPC分类号： B64D47/08 ,  B64B1/40 ,  B64B1/62 ,  B64D47/02 ,  B64U10/30 ,  B64U50/13 ,  B64U101/30

CPC分类号： B64D47/08 ,  B64B1/40 ,  B64B1/62 ,  B64D47/02 ,  B64D2211/00 ,  B64U10/30 ,  B64U50/13 ,  B64U2101/30 ,  B64U2201/20

摘要： A remote controlled lighter-than-air drone assembly that is capable of prolonged flight. The drone assembly utilizes a balloon structure. Separately, a reservoir is provided for holding a smaller second volume of gas. A propulsion system and a control unit are carried by the balloon structure. The control unit selectively transfers the gas from the reservoir to the balloon structure, and selectively vents the gas as needed. A receiver is used to receive command signals from an external source. The command signals are utilized to operate the propulsion system. An electronics suite is provided that can be altered depending upon duties. The electronics suite is used to scan or otherwise monitor an area below the drone assembly. In flight, the balloon structure is translucent and internally illuminated. A projector can be provided for projecting images onto the interior of the balloon structure.

公开(公告)号：US20230356839A1

公开(公告)日：2023-11-09

申请号：US18144653

申请日：2023-05-08

申请人： Pete Bitar

发明人： Pete Bitar

IPC分类号： B64D27/24 ,  B64C31/024

CPC分类号： B64C31/024 ,  B64D27/24 ,  B64D2211/00

摘要： An improved system of electrical, battery operated propulsion for use by an individual when engaging in paragliding, powered paragliding, paramotoring, hang gliding, and other similar sporting activities. The system includes a lightweight frame; at least one electrical driven, ducted turbine system made of at least one turbine, a shroud with a cut protector, and an electric motor; a seat assembly; a seat belt, and a pair of shoulder straps to hold user to the seat; a power system with a set of rechargeable batteries, battery boxes, a wiring harness from batteries to motors; and a servo-throttle for powering a motor of the system.

公开(公告)号：US20230352608A1

公开(公告)日：2023-11-02

申请号：US18140747

申请日：2023-04-28

申请人： Encarnacion Gonzalez

发明人： Encarnacion Gonzalez

IPC分类号： H01L31/05 ,  B64G1/44 ,  B64D41/00 ,  B60L8/00 ,  H02S30/10

CPC分类号： H01L31/05 ,  B64G1/443 ,  B64D41/00 ,  B60L8/003 ,  H02S30/10 ,  B64D2211/00

摘要： As it is scientifically known all or nearly all celestial bodies have magnetic fields to varying degrees including Earth. Many celestial bodies also have a gaseous atmosphere. The present invention utilizes said magnetic fields and or gaseous atmospheres in conjunction with a plurality of electric grids, coils, or super conducting slats to which varying levels of positive voltage are applied to produce electric power. A plurality of electric grids, coils, or super conducting slats may be installed on automobiles, aircraft, spacecraft, and onto the blades of a wind powered electrical generating system to produce electric power when the blades are in motion.

公开(公告)号：US20230333573A1

公开(公告)日：2023-10-19

申请号：US18337412

申请日：2023-06-19

申请人： HAPSMobile Inc.

发明人： Koji FUJIMOTO

IPC分类号： G05D1/10 ,  H02S50/00 ,  H02S10/40 ,  B64D41/00 ,  B64D47/08

CPC分类号： G05D1/106 ,  H02S50/00 ,  H02S10/40 ,  B64D41/00 ,  B64D47/08 ,  B64D2211/00

摘要： Provided is a control device that controls a power supply flight vehicle, the control device including a control unit which controls the power supply flight vehicle so as to cause a light irradiation unit to radiate light toward a solar cell panel while flying following flight of a power supply target flight vehicle on which the solar cell panel is mounted. Provided is a control method to control a power supply flight vehicle, which is executed by a computer, the control method including controlling the power supply flight vehicle so as to cause a light irradiation unit to radiate light toward a solar cell panel while flying following flight of a power supply target flight vehicle on which the solar cell panel is mounted.

公开(公告)号：US20180155005A1

公开(公告)日：2018-06-07

申请号：US15706807

申请日：2017-09-18

申请人： AeroVironment, Inc.

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

IPC分类号： B64C3/38 ,  H04B7/185 ,  B64C17/00 ,  B64D31/06 ,  B64C39/10 ,  B64C15/02 ,  B64C3/52 ,  B64D27/24 ,  B64C39/02 ,  B64C3/42

CPC分类号： 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

摘要： 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：US20180134381A1

公开(公告)日：2018-05-17

申请号：US15816319

申请日：2017-11-17

申请人： DETROIT AIRCRAFT CORPORATION

发明人： Jon Rimanelli ,  Lai YIZHANG

IPC分类号： B64C29/00 ,  B64D47/08 ,  B64D9/00 ,  B64C25/34 ,  B64C39/02

CPC分类号： B64C29/0033 ,  B64C25/34 ,  B64C25/405 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162 ,  B64D9/00 ,  B64D47/08 ,  B64D2211/00 ,  Y02T50/55

摘要： An unmanned air vehicle is provided. The unmanned air vehicle includes a frame having a center portion connecting two substantially parallel transversely spaced apart ele-wings. The ele-wings may store batteries and rotate along a forward axis to provide lift during a transition from vertical flight to linear flight. The landing gear may be connected to the ele-wings and configured to change pitch of the ele-wing to ensure stable flight during flight mode transition. A plurality of propellers, each having propeller drive motors, are attached to the frame and able to rotate from parallel position, relative to the center portion, for vertical flight to a perpendicular position, relative to the center portion, for linear flight. The propeller drives rotate on its axis and may be configured to propel the vehicle in a ground and flight mode.

公开(公告)号：US20170217587A1

公开(公告)日：2017-08-03

申请号：US15417175

申请日：2017-01-26

申请人： JG Entrepreneurial Enterprises LLC

发明人： John Goelet

IPC分类号： B64C39/02 ,  A01G15/00 ,  G05D1/00 ,  B64D1/18 ,  B64D1/02 ,  B64D39/06

CPC分类号： B64C39/02 ,  A01G15/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/12 ,  B64C2201/125 ,  B64C2201/146 ,  B64C2201/206 ,  B64D1/02 ,  B64D1/18 ,  B64D39/06 ,  B64D2211/00 ,  G05D1/0022

摘要： A weather modification system that includes both systems and vehicles capable of modifying the weather. The systems may include devices capable of utilizing compositions to create dispersants that can modify weather. The system is capable of autonomous weather modification where the vehicles may operate for long periods of time in the air and may be directed by a control station. The vehicles may include an airplane, a UAV, a balloon, a satellite, an airship, such as a lenticular airship, a helicopter or a lighter than air vehicle. The vehicles are capable of multiple functions including weather modification, weather monitoring, and coordination between different vehicles.

公开(公告)号：US09691926B2

公开(公告)日：2017-06-27

申请号：US14505357

申请日：2014-10-02

申请人： Google Inc.

发明人： Clinton L. Whetsel ,  Matthew A. Nubbe

IPC分类号： B64C3/26 ,  H01L31/052 ,  B64D41/00

CPC分类号： H01L31/052 ,  B64C3/26 ,  B64D41/00 ,  B64D2041/002 ,  B64D2211/00 ,  H01L31/044 ,  Y02E10/50

摘要： A solar panel includes a plurality of solar cells, a bypass diode unit, and a heat spreader. The bypass diode unit includes a bypass diode coupled in an electrical shunting configuration across at least a first solar cell of the plurality of solar cells to bypass current around at least the first solar cell in an event of failure of the first solar cell. The heat spreader is disposed over a portion of one or more of the solar cells. The bypass diode unit is disposed on a first side of the heat spreader with the bypass diode in thermal contact with the heat spreader. A second side of the heat spreader is mounted in thermal contact with the one or more of the solar cells to dissipate heat generated in the bypass diode to the one or more of the solar cells.

公开(公告)号：US20170029111A1

公开(公告)日：2017-02-02

申请号：US15264487

申请日：2016-09-13

申请人： Astigan Limited

发明人： Andrew Charles ELSON

IPC分类号： B64D5/00 ,  B64C39/02 ,  B64B1/40

CPC分类号： 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

摘要： An embodiment of an unmanned aerial vehicle, which may be connected to a lighter-than-air carrier, may have a ratio of a lifting force of the carrier to a weight of the vehicle from 1.1:1 to 3:1. The vehicle, excluding payload, may have a mass of from 30 kg to 150 kg. The vehicle may have a wingspan of from 20 m to 60 m.

摘要翻译： 可以连接到轻型承载人的无人驾驶飞行器的实施例可以具有从1.1:1到3:1的载体的提升力与车辆重量之比。 车辆（不包括有效载荷）的质量可能为30公斤至150公斤。 车辆可能具有20米至60米的翼展。

公开(公告)号：US20160318618A1

公开(公告)日：2016-11-03

申请号：US14880278

申请日：2015-10-12

申请人： The Boeing Company

发明人： Robert Erik Grip ,  Blaine Knight Rawdon

IPC分类号： B64D27/24 ,  B64C3/18 ,  B64C3/26 ,  B64C3/22

CPC分类号： B64D27/24 ,  B64C3/18 ,  B64C3/182 ,  B64C3/185 ,  B64C3/187 ,  B64C3/22 ,  B64C3/26 ,  B64D2211/00 ,  Y02T50/44 ,  Y02T50/62 ,  Y02T50/64 ,  Y10T156/10

摘要： An aircraft wing has a plurality of wing segments mounted on a wing spar by joints that allow relative movement between the spar and the wing segments. Tuning of coefficients of thermal expansion is employed to reduce induced stresses from changes in temperature.