WO2024142309A1 - 飛行体 - Google Patents

飛行体 Download PDF

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Publication number
WO2024142309A1
WO2024142309A1 PCT/JP2022/048353 JP2022048353W WO2024142309A1 WO 2024142309 A1 WO2024142309 A1 WO 2024142309A1 JP 2022048353 W JP2022048353 W JP 2022048353W WO 2024142309 A1 WO2024142309 A1 WO 2024142309A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
relay
motor
center
lift
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2022/048353
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
藤原徹也
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Kubota Corp
Ishikawa Energy Research Co Ltd
Original Assignee
Kubota Corp
Ishikawa Energy Research Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Kubota Corp, Ishikawa Energy Research Co Ltd filed Critical Kubota Corp
Priority to JP2024567085A priority Critical patent/JPWO2024142309A1/ja
Priority to PCT/JP2022/048353 priority patent/WO2024142309A1/ja
Publication of WO2024142309A1 publication Critical patent/WO2024142309A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U80/00—Transport or storage specially adapted for UAVs
    • B64U80/80—Transport or storage specially adapted for UAVs by vehicles
    • B64U80/82—Airborne vehicles

Definitions

  • the present invention relates to an aircraft that flies with a load suspended from it.
  • An aircraft can fly while holding a suspended load (item) such as luggage.
  • a suspended load such as luggage.
  • the aircraft (unmanned aircraft) disclosed in the patent document suspends the load from a support member (wire).
  • the present invention aims to reduce the effects that hinder precise control of an aircraft.
  • an aircraft that flies with a load suspended therefrom, and includes a main body, an arm that protrudes outward from the main body in a planar view, a lift generating unit that is provided on the arm and generates lift that is used for flight, a number of support members that support the load, and an attachment unit to which the support members are attached, and the attachment unit is located in an area of the main body that is outside the midpoint of a line that connects the center of gravity of the main body and the center of the lift generating unit in a planar view.
  • the aircraft has mounting parts in the outer area of the aircraft for attaching the support members to the aircraft.
  • the payload suspended from the aircraft is suspended below the central area of the aircraft by multiple support members suspended from the outside of the aircraft.
  • This configuration allows the lift force to be adjusted more efficiently according to the stress on the support member.
  • the lift generating section may have a main lift generating section that generates the lift to propel the aircraft, and a secondary lift generating section that generates the lift to control the attitude of the aircraft, and the attachment section may be positioned so as to overlap with the secondary lift generating section in a plan view.
  • This configuration allows the secondary lift generating section to more efficiently control the attitude of the aircraft in response to stress on the mounting section. As a result, the stability of the payload and the aircraft can be improved, and the flying object can be controlled with greater precision.
  • This configuration allows the length of the support member to be adjusted to adjust the attitude of the load, improving the stability of the suspended load. As a result, the flying object can be controlled with precision.
  • the attachment portion may also be provided on the arm portion.
  • the attachment section By providing an attachment section on the arm section that supports the lift generating section, the attachment section can be positioned significantly outside the central area of the main body section. This makes it easier to stabilize the payload and allows for more precise control of the flying object.
  • the mounting parts are placed on the main body, which is easier to strengthen, so the load can be supported more firmly.
  • the lift generating part may also be a rotor.
  • the attitude of the load 8 can be stabilized, the stability of the airframe can be improved, and the flying object can be controlled with high precision.
  • the relay section 17 is a pulley that supports the wire 5, the length of which is changed, in a state where friction is reduced.
  • the motor 18 is operated by the power generated by the generator 12 or the power stored in the battery 13.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Transportation (AREA)
  • Catching Or Destruction (AREA)
  • Load-Engaging Elements For Cranes (AREA)
PCT/JP2022/048353 2022-12-27 2022-12-27 飛行体 Ceased WO2024142309A1 (ja)

Priority Applications (2)

Application Number Priority Date Filing Date Title
JP2024567085A JPWO2024142309A1 (https=) 2022-12-27 2022-12-27
PCT/JP2022/048353 WO2024142309A1 (ja) 2022-12-27 2022-12-27 飛行体

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2022/048353 WO2024142309A1 (ja) 2022-12-27 2022-12-27 飛行体

Publications (1)

Publication Number Publication Date
WO2024142309A1 true WO2024142309A1 (ja) 2024-07-04

Family

ID=91716781

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2022/048353 Ceased WO2024142309A1 (ja) 2022-12-27 2022-12-27 飛行体

Country Status (2)

Country Link
JP (1) JPWO2024142309A1 (https=)
WO (1) WO2024142309A1 (https=)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3934847A (en) * 1974-10-04 1976-01-27 Bentivegna Pasquale P Rescue capsule for use with a helicopter
JP2010280251A (ja) * 2009-06-02 2010-12-16 Bin Mamdooh Bin Abdul Aziz Al Saud Naief ヘリコプターに取り付けられる消火救難ユニット
KR101650525B1 (ko) * 2016-02-18 2016-08-24 아이씨티웨이주식회사 지아이에스 기반 신규데이터에 따른 영상 업데이트 도화시스템
JP2017104365A (ja) * 2015-12-11 2017-06-15 株式会社ディスコ 有人ドローン
CN107054653A (zh) * 2017-05-05 2017-08-18 西安工业大学 基于绳牵引的飞行载物机器人及方法
CN210149563U (zh) * 2019-06-20 2020-03-17 郑州鑫雅图安科技有限公司 一种航空救援挂载装置

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3934847A (en) * 1974-10-04 1976-01-27 Bentivegna Pasquale P Rescue capsule for use with a helicopter
JP2010280251A (ja) * 2009-06-02 2010-12-16 Bin Mamdooh Bin Abdul Aziz Al Saud Naief ヘリコプターに取り付けられる消火救難ユニット
JP2017104365A (ja) * 2015-12-11 2017-06-15 株式会社ディスコ 有人ドローン
KR101650525B1 (ko) * 2016-02-18 2016-08-24 아이씨티웨이주식회사 지아이에스 기반 신규데이터에 따른 영상 업데이트 도화시스템
CN107054653A (zh) * 2017-05-05 2017-08-18 西安工业大学 基于绳牵引的飞行载物机器人及方法
CN210149563U (zh) * 2019-06-20 2020-03-17 郑州鑫雅图安科技有限公司 一种航空救援挂载装置

Also Published As

Publication number Publication date
JPWO2024142309A1 (https=) 2024-07-04

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