公开(公告)号：US06857601B2

公开(公告)日：2005-02-22

申请号：US10189796

申请日：2002-07-03

Applicant: Yutaka Akahori

Inventor： Yutaka Akahori

IPC: B64B1/06 ,  B64C39/02 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/02 ,  G08G5/00 ,  B64B1/00

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：US20040232285A1

公开(公告)日：2004-11-25

申请号：US10877082

申请日：2004-06-25

Inventor： Yutaka Akahori

IPC: F41J009/08

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，并且可以降低飞艇的负载重量和功率消耗。

公开(公告)号：US20030234320A1

公开(公告)日：2003-12-25

申请号：US10178345

申请日：2002-06-25

Applicant: 21st Century Airships Inc.

Inventor： Hokan S. Colting

IPC: B64B001/02 ,  B64B001/06

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 has a generally spherical shape and has an internal envelope for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system 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% fall of lifting gas, and may have a service ceiling of about 60,000 ft. The airship has an equipment module 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 of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit 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信封。 飞艇有一个推进和控制系统，允许飞行到所需的游荡地点，并在该地点保持一段时间。 在一个实施例中，当内部信封低至7％的提升气体下降时，飞艇可以实现中性浮力，并且可以具有约60,000ft的服务天花板。飞艇具有可以包括通信设备或监视的设备模块 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动机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。 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.

公开(公告)号：US20180229828A1

公开(公告)日：2018-08-16

申请号：US15753162

申请日：2015-08-19

Applicant: (X-CONTROL SYSTEM CO., LTD.)

Inventor： Fan YANG

IPC: B64B1/06 ,  G09F19/18 ,  G09F21/06 ,  B64C39/02 ,  G03B29/00

CPC classification number: B64B1/06 ,  B64B1/26 ,  B64B1/34 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/12 ,  B64C2201/127 ,  G03B21/10 ,  G03B29/00 ,  G03B37/04 ,  G09F19/18 ,  G09F21/06

Abstract: The present invention provides a flying robot (10) with projector, including a movable end (100) and a fixed end (200). A distributed working mode is used on the movable end (100) and the fixed end (200). The movable end (100) includes a top (110), a main body (120) and a bottom (130). The top (110) includes a lift system (112) and one or more proximity sensors (114); the main body (120) is a sealed hollow spherical body or spheroid body made of a film material capable of being used as a rear projection screen, and is filled with a gas of which the density is less than that of the air. The bottom (130) includes one or more rear projectors (131), a wireless communication module (132), a microcontroller (133), a battery (134), a direction and steering controlling device (135), a camera device (136), a sound capturing and reproduction device (137), a height sensor (138) and other sensors, etc. The fixed end (200) includes a wireless communication module (220), a control apparatus (240), a charging port (260), and other data interfaces, etc. The flying robot (10) with projector according to the present invention facilitates human-machine interaction and is suitable for being used in both indoor and outdoor environments.

公开(公告)号：US20180088592A1

公开(公告)日：2018-03-29

申请号：US15714693

申请日：2017-09-25

Applicant: CALIFORNIA INSTITUTE OF TECHNOLOGY ,  CHEVRON U.S.A. INC.

Inventor： Matthew GILDNER ,  Donald F. RUFFATTO ,  Sophia MITCHELL ,  Oktay ARSLAN ,  Joshua Vander HOOK ,  Jolly JAMES ,  Robert Kwan Meng SEAH ,  Nick MARKOV

IPC: G05D1/04 ,  G05D1/02 ,  B64B1/06 ,  B64B1/70

CPC classification number: G05D1/042 ,  B64B1/06 ,  B64B1/70 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64D47/04 ,  B64D2203/00 ,  G01N21/8803 ,  G01N21/9515 ,  G01N21/954 ,  G05D1/0022 ,  G05D1/0202 ,  G05D2201/0207 ,  Y10S901/01 ,  Y10S901/44

Abstract: Designing intrinsically safe robotic inspection systems used for unmanned navigation and inspection of large tanks with hazardous and explosive atmosphere is challenging. The disclosed methods and devices provide solutions to overcome such challenge. Intrinsically safe devices and methods using a combination of a lighter-than-air blimp with various intrinsically safe subsystems attached to the blimp are presented.