WO2019142014A1 - Agencement de type planeur/drone électrique - Google Patents

Agencement de type planeur/drone électrique Download PDF

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Publication number
WO2019142014A1
WO2019142014A1 PCT/IB2018/050313 IB2018050313W WO2019142014A1 WO 2019142014 A1 WO2019142014 A1 WO 2019142014A1 IB 2018050313 W IB2018050313 W IB 2018050313W WO 2019142014 A1 WO2019142014 A1 WO 2019142014A1
Authority
WO
WIPO (PCT)
Prior art keywords
glider
drone
rope
cable
electric
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/IB2018/050313
Other languages
English (en)
Inventor
Jānis PUTRĀMS
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.)
Aerones Sia
Original Assignee
Aerones Sia
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 Aerones Sia filed Critical Aerones Sia
Priority to PCT/IB2018/050313 priority Critical patent/WO2019142014A1/fr
Publication of WO2019142014A1 publication Critical patent/WO2019142014A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/02—Gliders, e.g. sailplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/50—Glider-type UAVs, e.g. with parachute, parasail or kite
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/24—Coaxial rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/293—Foldable or collapsible rotors or rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/34—In-flight charging
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/80—Vertical take-off or landing, e.g. using rockets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/80—Vertical take-off or landing, e.g. using rockets
    • B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/31—Supply or distribution of electrical power generated by photovoltaics

Definitions

  • the invention relates to electric drones and gliders.
  • Vertical take-off and landing vehicles such as rotorcrafts, are typically more efficient during take-off and landing, than during horizontal flight. While fixed-wing aircrafts are more energy efficient during horizontal flight using moving air to gain and maintain height as well as glide.
  • stages 2 and 4 Glider needs horizontal air flow to reach beyond stall speed and gain lifting power. Transition stages requires both air flows that do not match.
  • the known solutions create compromises by using some part of the device area for vertical air flow and some for horizontal. As a result, vertical lifting efficiency is low because of relatively small available propeller disk area and stall speed of the winged aircraft is high also because of relatively small wing size and worsened aerodynamics affected by vortices created between both air flows.
  • the invention provides a manned or unmanned electrically powered flying arrangement with capabilities of vertical take-off or landing (VTOL) and efficient horizontal flight.
  • VTOL vertical take-off or landing
  • the invention improves efficiency of the known devices by creating interactive dynamic system that allows to increase relative propeller disk area, separate air flows during transition stages between vertical and horizontal flight stages and optimize overall aerodynamics.
  • the electric drone glider arrangement comprising: a heavy-lift multi-rotor drone with batteries; a manned or unmanned glider; a high voltage generator (preferably, located on the ground); an electric cable and rope connecting the drone and the glider (said cable and rope having adjustable length); an electric cable and rope connecting the glider and the generator.
  • the cable and rope connecting the glider and the generator being detachably attached to the glider, such that the cable and the rope can be disconnected from the glider once the glider is raised to the sufficient height.
  • the cable and rope connecting the glider and the drone at both ends is preferably connected to the center of gravity of the drone and the glider.
  • Fig. 1 shows a schematic view of the electric drone glider arrangement in take-off stage of the flight
  • Fig. 2 - a schematic view of the electric drone glider arrangement in transition flight stage between vertical and fully horizontal flight stages;
  • Fig. 3 - a schematic view of the electric drone glider arrangement in horizontal (forward) flight stage.
  • the electric drone glider arrangement comprising:
  • the cable and rope 4 is provided with mechanism (e.g. winch) adapted to allow controllable adjustment of length of the cable and rope 4 during the flight of the drone glider arrangement; - a cable and rope 5 connecting the glider 2 and generator 3; the cable and rope 5 being removably attached to the glider 2.
  • mechanism e.g. winch
  • the detachable end of the cable and rope 5 connected to the glider 2 is preferably provided with a parachute designed to be deployed after the detachable end of the cable and rope 5 is disconnected from the glider 2 and falls down.
  • the electric drone glider 2 arrangement further optionally comprises solar panels mounted on the glider 2.
  • the electric cable connecting the drone 1 and the glider 2 can be used to send power to the drone 1 motors during horizontal stage of the flight.
  • the drone 1 can have coaxial propeller setup. Bottom propellers can be folded during horizontal stage of the flight to reduce drag.
  • the drone 1 coaxial propeller setup can have bigger pitch value for top propellers and smaller pitch for bottom propellers so that better efficiency is achieved during the horizontal stage of the flight, providing still enough stability and lift during vertical take-off and landing stages.
  • the drone 1 is designed in a way that every motor has its own battery and they are connected in series and/or parallel so that high voltage electricity from the generator 3 can be utilized with almost no added weight.
  • the electric drone glider arrangement is preferably designed so that in an emergency situation the drone 1 can be disconnected from the glider 2 (i.e. the cable and rope 4 connecting the glider 2 and the drone 1 may be detached) and the glider 2 would be able to land as ordinary glider without VTOL capability.
  • the drone 1 is preferably designed so that it may be forced to stop all motors and deploy one or more parachutes.
  • the cable and rope 4 connecting the glider 2 and the drone 1 at both ends is connected to the center of gravity of the drone 1 and the glider 2.
  • the rope 4 is preferably connected to the glider 2 and the drone 1 using roller guidance systems (e.g. curved rail roller track) where center of roller guidance system of the drone 1 is located in the center of gravity of the drone 1 and the center of roller guidance system of the glider 2 is located in the center of gravity of the glider 2.
  • the roller guidance systems are adapted to allow free partial rotation of the drone 1 and the glider 2 around their center of gravity.
  • the electric drone glider arrangement has five stages of flight: vertical take-off, transition from vertical to horizontal flight, horizontal flight, transition from horizontal flight to vertical landing and vertical landing.
  • the drone 1 takes off and gains altitude.
  • the drone 1 starts to lift the glider 2 in the air.
  • the glider 2 wing might be pointed vertically up to increase efficiency.
  • the generator 3 is providing power to the drone 1 motors through the cable 5 (from the generator 3 to the glider 2) and further on through the cable 4 (from the glider 2 to the drone 1 motors) so that the drone 1 batteries are not discharged during take-off.
  • the cable and rope 4 is adjusted short for the glider 2 to have rotating capacity using its ailerons.
  • the cable and rope 5 connecting the glider 2 and the generator 3 is disconnected from glider 2 and falls to the ground (preferably, with small parachute).
  • the drone 1 stops gaining altitude, tilts and starts gaining horizontal speed. As speed increases the glider 2 wing turns from pointing upwards to pointing forward (Fig. 2). When stall speed for the glider 2 is exceeded the drone 1 continues to tilt forward and starts to lose altitude relative to the glider 2. At one point the drone 1 and the glider 2 are both at the same height.
  • the rope 4 connecting the drone 1 and the glider 2 is never loose. As horizontal speed increases even more and stall speed is exceeded for the glider 2 to carry the drone 1 weight, then the drone 1 tilts more to fully vertical position.
  • the cable and rope 4 connecting the drone 1 and the glider 2 is adjusted long enough so that vertical air flow of the drone 1 and horizontal air flow for the glider 2 do not affect each other.
  • the next stage of the flight happens similar to stage two, only in reverse.
  • a speed is gradually reduced until the glider 2 is not able to carry the drone 1 weight.
  • the drone 1 starts to tilt backwards and gain height relative to the glider 2.
  • the speed is reduced even more until the glider 2 stalls.
  • the cable and rope 4 connecting the drone 1 and the glider 2 is adjusted long enough for the same reasons as for the second stage of the flight.
  • the landing stage is similar to the take-off stage only in reverse and there is no cable and rope 5 connecting the glider 2 and generator 3.
  • the drone 1 slowly looses altitude and brings the glider 2 to the ground. Then it keeps descending and lands itself.
  • the cable and rope 4 connecting the drone 1 and the glider 2 might be adjusted short for this stage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Electric Cable Installation (AREA)

Abstract

La présente invention concerne les drones électriques et les planeurs. L'agencement de type planeur/drone électrique comprend : un drone à rotor multiples à portance élevée comprenant des batteries ; un planeur avec ou sans pilote ; un générateur de haute tension ; un câble électrique et une corde raccordant le drone et le planeur ; un câble électrique et une corde raccordant le planeur et le générateur. Le câble et la corde raccordant le planeur et le générateur sont fixés de manière amovible au planeur, de telle sorte que le câble et la corde peuvent être déconnectés du planeur une fois que le planeur est levé à la hauteur suffisante. Le câble et la corde raccordant le planeur et le drone présentent une longueur réglable et, aux deux extrémités, sont raccordés au centre de gravité du drone et du planeur.
PCT/IB2018/050313 2018-01-18 2018-01-18 Agencement de type planeur/drone électrique Ceased WO2019142014A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/IB2018/050313 WO2019142014A1 (fr) 2018-01-18 2018-01-18 Agencement de type planeur/drone électrique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB2018/050313 WO2019142014A1 (fr) 2018-01-18 2018-01-18 Agencement de type planeur/drone électrique

Publications (1)

Publication Number Publication Date
WO2019142014A1 true WO2019142014A1 (fr) 2019-07-25

Family

ID=61226619

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2018/050313 Ceased WO2019142014A1 (fr) 2018-01-18 2018-01-18 Agencement de type planeur/drone électrique

Country Status (1)

Country Link
WO (1) WO2019142014A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102944854B1 (ko) 2025-04-24 2026-03-27 주식회사 쿼터니언 유선 드론 비행 중 비상상황 발생 시 비상착륙 과정에서 유선 케이블을 권취하는 방법

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004106156A1 (fr) * 2003-05-30 2004-12-09 Qinetiq Limited Procede et dispositif de lancement de vehicules aeriens
WO2007141795A1 (fr) * 2006-06-08 2007-12-13 Israel Aerospace Industries Ltd. Système de véhicule aérien sans pilote
WO2013178776A1 (fr) * 2012-06-01 2013-12-05 Logo-Team Ug (Haftungsbeschränkt) Avion, de préférence sans équipage
WO2015143093A2 (fr) 2014-03-18 2015-09-24 Joby Aviation, Inc. Aéronef à décollage et atterrissage verticaux, léger et performant, comprenant des rotors pivotants et des pales de rotor escamotables
US20150275861A1 (en) * 2014-03-31 2015-10-01 Leonid Goldstein Rotor kite wind energy system and more
US9457900B1 (en) * 2014-04-07 2016-10-04 The United States Of America, As Represented By The Secretary Of The Navy Multirotor mobile buoy for persistent surface and underwater exploration
US9694911B2 (en) 2014-03-18 2017-07-04 Joby Aviation, Inc. Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
WO2017210595A2 (fr) 2016-06-03 2017-12-07 Aerovironment, Inc. Véhicule aérien à ailes à décollage et atterrissage verticaux (vtol) avec rotors angulaires complémentaires

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004106156A1 (fr) * 2003-05-30 2004-12-09 Qinetiq Limited Procede et dispositif de lancement de vehicules aeriens
WO2007141795A1 (fr) * 2006-06-08 2007-12-13 Israel Aerospace Industries Ltd. Système de véhicule aérien sans pilote
WO2013178776A1 (fr) * 2012-06-01 2013-12-05 Logo-Team Ug (Haftungsbeschränkt) Avion, de préférence sans équipage
WO2015143093A2 (fr) 2014-03-18 2015-09-24 Joby Aviation, Inc. Aéronef à décollage et atterrissage verticaux, léger et performant, comprenant des rotors pivotants et des pales de rotor escamotables
US9694911B2 (en) 2014-03-18 2017-07-04 Joby Aviation, Inc. Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
US20150275861A1 (en) * 2014-03-31 2015-10-01 Leonid Goldstein Rotor kite wind energy system and more
US9457900B1 (en) * 2014-04-07 2016-10-04 The United States Of America, As Represented By The Secretary Of The Navy Multirotor mobile buoy for persistent surface and underwater exploration
WO2017210595A2 (fr) 2016-06-03 2017-12-07 Aerovironment, Inc. Véhicule aérien à ailes à décollage et atterrissage verticaux (vtol) avec rotors angulaires complémentaires

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102944854B1 (ko) 2025-04-24 2026-03-27 주식회사 쿼터니언 유선 드론 비행 중 비상상황 발생 시 비상착륙 과정에서 유선 케이블을 권취하는 방법

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