[go: up one dir, main page]

WO2019058312A1 - Structure solaire flottante aérienne manœuvrable - Google Patents

Structure solaire flottante aérienne manœuvrable Download PDF

Info

Publication number
WO2019058312A1
WO2019058312A1 PCT/IB2018/057283 IB2018057283W WO2019058312A1 WO 2019058312 A1 WO2019058312 A1 WO 2019058312A1 IB 2018057283 W IB2018057283 W IB 2018057283W WO 2019058312 A1 WO2019058312 A1 WO 2019058312A1
Authority
WO
WIPO (PCT)
Prior art keywords
propellers
fuselage
balloon
solar panels
navigating
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/IB2018/057283
Other languages
English (en)
Inventor
Ravi Shankar
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of WO2019058312A1 publication Critical patent/WO2019058312A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S20/00—Solar heat collectors specially adapted for particular uses or environments
    • F24S20/80—Airborne solar heat collector modules, e.g. inflatable structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/06—Rigid airships; Semi-rigid airships
    • B64B1/24—Arrangement of propulsion plant
    • B64B1/30—Arrangement of propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/40—Balloons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/30—Lighter-than-air aircraft, e.g. aerostatic aircraft
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S20/00—Solar heat collectors specially adapted for particular uses or environments
    • F24S20/50—Rollable or foldable solar heat collector modules
    • F24S20/55—Rollable or foldable solar heat collector modules made of flexible materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
    • B64U2101/31—UAVs specially adapted for particular uses or applications for imaging, photography or videography for surveillance
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/40—Solar thermal energy, e.g. solar towers
    • Y02E10/47—Mountings or tracking

Definitions

  • THIS APPLICATION IS A PATENT OF ADDITION TO INDIAN PATENT APLLICATION NO. 201721014708 FILED ON APRIL 25 th , 2017.
  • the present disclosure relates to the field of solar panels. More specifically, the present disclosure relates to the field of maneuverable aerial floating solar structure.
  • Indian patent application number 201721014708 discloses a floating solar structure which is used for supplying power to a remotely located load.
  • the floating solar structure as disclosed in Indian patent application number 201721014708, uses a balloon, a floating media, a flexible solar panel, and a support arrangement.
  • the flexible solar panel is securely disposed on the balloon which contains the floating media entrapped therewithin.
  • the support arrangement is configured at an operative bottom of the balloon to securely hold the flexible solar panel on the balloon.
  • the floating solar structure, of Indian patent application number 201721014708 is kept stationary by means of an anchor.
  • An object of the present disclosure is to provide a maneuverable aerial floating solar structure.
  • Yet another object of the present disclosure is to provide a maneuverable aerial floating solar structure, which has simple configuration.
  • the present disclosure envisages a maneuverable aerial floating solar structure comprising a floatable balloon, a plurality of flexible solar panels, a fuselage, and a maneuvering unit.
  • a floating media is entrapped within the floatable balloon to levitate the floatable balloon above the ground.
  • the floating media is a helium gas.
  • the plurality of flexible solar panels is securely disposed on the floatable balloon and is configured to generate a solar power.
  • Each of the solar panels is coupled with each other by a coupling means.
  • the shape of the solar panels is selected from the group consisting of a hexagon, a square, a rectangle, a triangle, a circle, a trapezoid, and any geometrical or non-geometrical shape thereof.
  • the coupling means have at least one O-ring.
  • the fuselage is coupled to the floatable balloon.
  • the maneuvering unit is configured to provide mobility to the structure.
  • the maneuvering unit includes a plurality of arms, a plurality of propellers and a swiveling mechanism.
  • the plurality of arms is coupled to the fuselage and each of the propellers is mounted on a free end of each of the arms.
  • the swiveling mechanism is configured to angularly displace the arms at a pre-defined angle with respect to the fuselage to provide controlled mobility of the structure in a desired direction.
  • the fuselage includes an input means and a control unit.
  • the input means is configured to receive at least one operating command from an operator, and further configured to generate at least one operating signal.
  • the control unit is configured to cooperate with the input means to receive at least one operating signal, and is further configured to generate a navigating signal to determine navigating propellers from the plurality of propellers.
  • the control unit is configured to control the mobility of the structure by controlling the navigating propellers.
  • control unit is configured to generate a power generation signal to control the operation of the non-navigating propellers from the plurality of propellers.
  • the non-navigating propellers are configured to generate an auxiliary power.
  • a power supply unit is configured to provide power to the plurality of propellers and is further configured to be charged by at least one of the solar power and the auxiliary power.
  • an emergency landing unit is configured to detect malfunctioning of the structure, and is further configured to facilitate controlled landing of the fuselage upon detection of malfunctioning of the structure.
  • the emergency landing unit is configured to deploy a first set of parachutes in the event of malfunctioning of the structure.
  • the emergency landing unit includes deployment of a second set of parachutes subsequent to the failure of the first set of parachutes, and deployment of a third parachute subsequent to the failure of the second set of parachutes.
  • a support arrangement is configured at an operative bottom of the floatable balloon.
  • the support arrangement includes a pair of spaced apart rings interconnected via a plurality of wires and a plurality of support cables.
  • a first ring of the pair of rings is configured to securely hold the flexible solar panels on the floatable balloon.
  • a second ring is configured to provide mechanical coupling to the fuselage with the balloon via the plurality of support cables.
  • Figure 1 illustrates an isometric view of a maneuverable aerial floating solar structure
  • Figure 2 illustrates a side view of the maneuverable aerial floating solar structure of Figure
  • Figure 3 illustrates a bottom view of the maneuverable aerial floating solar structure of Figure 1;
  • Figure 4 illustrates an isometric view of a plurality of flexible solar panels mounted on the maneuverable aerial floating solar structure of Figure 1;
  • Figure 5 illustrates an operative top portion of the maneuverable aerial floating solar structure of Figure 1.
  • the present disclosure envisages a maneuverable aerial floating solar structure.
  • An embodiment of the maneuverable aerial floating solar structure, of the present disclosure is now being described with reference to the accompanying drawing. The description provided is purely by way of example and illustration.
  • Figure l Illustrates an isometric view of a maneuverable aerial floating solar structure 100.
  • Figure 2 illustrates a side view of the maneuverable aerial floating solar structure 100.
  • Figure 3 illustrates a bottom view of the maneuverable aerial floating solar structure 100.
  • Figure 4 illustrates an isometric view of a plurality of flexible solar panels 108 mounted on the maneuverable aerial floating solar structure 100.
  • Figure 5 illustrates an operative top portion of the maneuverable aerial floating solar structure 100.
  • the maneuverable aerial floating solar structure 100 (hereinafter referred as “structure 100") comprises a floatable balloon 102 (hereinafter also referred as “balloon 102"), a plurality of flexible solar panels 108, a support arrangement 104, a fuselage 110, and a maneuvering unit (not shown in figures).
  • a floating media is entrapped within the balloon 102.
  • the floating media is a helium gas.
  • the plurality of flexible solar panels 108 is securely disposed on the balloon 102.
  • the flexible solar panels 108 are configured to generate a solar power.
  • Each flexible solar panels 108 are coupled to each other by a coupling means 108b, thereby providing flexibility.
  • the shape of the solar panels 108a is selected from the group consisting of a hexagon, a square, a rectangle, a triangle, a circle, a trapezoid, and any geometrical or non- geometrical shape thereof.
  • the coupling means 108b have at least one O-ring.
  • the support arrangement 104 is configured at an operative bottom of the balloon 102.
  • the support arrangement 104 includes a pair of spaced apart rings (202, 204) interconnected via a plurality of wires 206, and a plurality of the support cables.
  • a first ring 202, of the pair of rings (202, 204), is configured to securely hold the plurality of flexible solar panels 108 which are mounted on the balloon 102.
  • a second ring is configured to provide mechanical coupling to the fuselage 110 with the balloon 102 via the plurality of support cables 106.
  • at least one loop 114 is configured at an operative bottom of the support arrangement 104. The at least one support cable 106 is secured to the at least one loop 114, thereby enabling the mechanical coupling of the balloon 102 with the fuselage 110.
  • the maneuvering unit includes a plurality of arms 118, a plurality of propellers 112 and a swiveling mechanism.
  • the plurality of arms is coupled to the fuselage 110.
  • Each propeller 112 is mounted on a free end of each of the arms 118.
  • the plurality of arms 118 is configured to securely support the plurality of propellers 112.
  • the plurality of propellers 112 is configured to provide controlled mobility, take-off, and landing of the structure 100.
  • the fuselage 110 includes an emergency landing unit (not shown in figures), an input means (not shown in figures), a control unit (not shown in figures), a release mechanism (not shown in figures), a plurality of control panels (not shown in figures), a cockpit (not shown in figures), a pantry (not shown in figures), at least one lavatory (not shown in figures), and a plurality of seating arrangements (not shown in figures).
  • the input means is configured to receive at least one operating command by a remote device, from an operator and is further configured to generate at least one operating signal.
  • the control unit is configured to cooperate with the input means to receive at least one operating signal.
  • the control unit is further configured to generate a navigating signal to determine navigating propellers 112 from the plurality of propellers 112.
  • the swiveling mechanism is configured to angularly displace the arms 118 of the structure at a pre-defined angle with respect to the fuselage 110, based on the navigating signal.
  • the control unit is configured to control the mobility of the structure in a desired direction during propulsion, by controlling the operation of the navigating propellers.
  • the control unit is also configured to generate a power generation signal and further configured to control the operation of non-navigating propellers from the plurality of propellers 112, to generate an auxiliary power.
  • the fuselage 110 includes a power supply unit (not shown in figures).
  • the power supply unit includes at least one battery. At least one battery is further configured to provide power to the plurality of propellers 112. The at least one battery is further configured to be charged by at least one of the solar power and the auxiliary power.
  • the solar power generated by the plurality of flexible solar panels 108 and the auxiliary power generated by non-navigating propellers is supplied to the battery by means of an electrically conductive cable (not shown in figures).
  • the emergency landing unit is configured to detect malfunctioning of the structure 100.
  • the release mechanism is configured to detach the fuselage 110 from the support arrangement 104, thereby releasing the fuselage 110.
  • the emergency landing unit gets activated.
  • the emergency landing unit includes a first set of parachutes 120, a second set of parachutes 122, and a third parachute 124.
  • the emergency landing unit is configured to facilitate steady landing of the fuselage 110.
  • Each of the first set of parachutes 120, the second set of parachutes 122, and the third parachute 124 are housed within a plurality of housing configured at an operative top surface of the fuselage 110.
  • the first set of parachutes 120 and the second set of parachutes 122 are alternately arranged along the periphery of the fuselage 110.
  • the third parachute 124 is centrally located with respect to the fuselage 110.
  • the first set of parachutes 120 are deployed wherein the first set of parachutes is configured to facilitate steady landing of the fuselage 110.
  • the second set of parachutes 122 are deployed in an event of failure or malfunctioning of the first set of parachutes 120.
  • the third parachute 124 is deployed.
  • the fuselage also includes a surveillance unit (not shown in the figures).
  • the surveillance unit may include at least one camera.
  • the at least one camera is configured to capture and monitor the activities on the ground such as behavior of traffic on the ground, military purpose applications and the like.
  • the at least one camera is selected from the group consisting of an infrared camera, a day and night camera, and a PTZ (Pan, tilt and zoom) camera.
  • a plurality of wheels 116 is coupled to the operative bottom of the fuselage 110.
  • the plurality of wheels 116 is connected to the fuselage 110 via a suspension mechanism (not shown in the figures).
  • the suspension mechanism is configured to provide the cushioning effect and bear the load of the structure 100 during take-off and landing.
  • the plurality of wheels 116 is configured to retract after takeoff and retrieve before landing.
  • the structure 100 of the present disclosure is cost effective, simple in configuration, and also provides an economical mode of aerial transport.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Sustainable Energy (AREA)
  • Thermal Sciences (AREA)
  • Sustainable Development (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne le domaine de la structure solaire flottante aérienne manœuvrable qui est mobile dans la nature et présente une configuration simple. La structure comprend un ballon, des panneaux solaires flexibles, un agencement de support, un fuselage, une pluralité de bras et une pluralité d'hélices. Un milieu flottant est piégé dans le ballon. Les panneaux solaires flexibles sont disposés de manière sûre sur le ballon. Les panneaux solaires flexibles comprennent une pluralité de panneaux solaires couplés l'un à l'autre par un moyen de couplage et sont en outre conçus pour générer une énergie solaire. L'agencement de support est conçu au niveau d'un fond fonctionnel du ballon. Le fuselage est couplé à l'agencement de support par l'intermédiaire d'une pluralité de câbles de support. La pluralité de bras est couplée au fuselage et chacune des hélices est montée sur une extrémité libre de chacun des bras.
PCT/IB2018/057283 2017-09-25 2018-09-21 Structure solaire flottante aérienne manœuvrable Ceased WO2019058312A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IN201723034024 2017-09-25
IN201723034024 2017-09-25

Publications (1)

Publication Number Publication Date
WO2019058312A1 true WO2019058312A1 (fr) 2019-03-28

Family

ID=65811117

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2018/057283 Ceased WO2019058312A1 (fr) 2017-09-25 2018-09-21 Structure solaire flottante aérienne manœuvrable

Country Status (1)

Country Link
WO (1) WO2019058312A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112918656A (zh) * 2021-02-26 2021-06-08 中国航天空气动力技术研究院 一种高空球载太阳能无人机系统
WO2024110115A1 (fr) * 2022-11-23 2024-05-30 Technische Universiteit Delft Drone à ballon
CN118803457A (zh) * 2024-09-10 2024-10-18 浙江宇迈智能科技有限公司 一种应急用的无线网络信号传输设备及其操作方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6142414A (en) * 1999-01-26 2000-11-07 Doolittle; William Rotor--aerostat composite aircraft
DE10206306A1 (de) * 2002-02-12 2003-08-21 Dieter Lampart Rettungskabine für vom Flugzeugabsturz bedrohte Insassen
US6877693B1 (en) * 1998-06-23 2005-04-12 Yves Barbarie Aerostat for transporting equipment and passengers
US20120235410A1 (en) * 2011-03-15 2012-09-20 Serrano Richard J Lighter than air wind and solar energy conversion system

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6877693B1 (en) * 1998-06-23 2005-04-12 Yves Barbarie Aerostat for transporting equipment and passengers
US6142414A (en) * 1999-01-26 2000-11-07 Doolittle; William Rotor--aerostat composite aircraft
DE10206306A1 (de) * 2002-02-12 2003-08-21 Dieter Lampart Rettungskabine für vom Flugzeugabsturz bedrohte Insassen
US20120235410A1 (en) * 2011-03-15 2012-09-20 Serrano Richard J Lighter than air wind and solar energy conversion system

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112918656A (zh) * 2021-02-26 2021-06-08 中国航天空气动力技术研究院 一种高空球载太阳能无人机系统
WO2024110115A1 (fr) * 2022-11-23 2024-05-30 Technische Universiteit Delft Drone à ballon
NL2033602B1 (en) * 2022-11-23 2024-05-30 Univ Delft Tech A balloon enabled drone
CN118803457A (zh) * 2024-09-10 2024-10-18 浙江宇迈智能科技有限公司 一种应急用的无线网络信号传输设备及其操作方法

Similar Documents

Publication Publication Date Title
AU2014200597B2 (en) Autonomous aircraft
WO2019058312A1 (fr) Structure solaire flottante aérienne manœuvrable
US10822122B2 (en) Vertical landing systems for space vehicles and associated methods
US6199793B1 (en) System for deployment and retrieval of airborne towed vehicles
US5593113A (en) Methods and apparatus for selectively attaching and releasing multiple payloads suspended from an aircraft
US9527604B2 (en) Unmanned air vehicle recovery system
US9027879B1 (en) Modular adaptive configured helicopter
US9669947B2 (en) Small unmanned aerial vehicle (SUAV) shipboard recovery system
US20200115054A1 (en) Maneuverable capture apparatus for airborne deployment and retrieval of parasite aircraft
WO2002042149A2 (fr) Systeme de transport de charge spherique plus leger que l'air
JP2011068346A (ja) 拘束及び解放装置
US11104439B2 (en) System and method for deployment and retrieval of parasite aircraft
US9359046B2 (en) Submersible towed body deployment and recovery device
US20160221689A1 (en) Line Intersect Vehicle Launch and Recovery
US9598149B1 (en) System for the deployment and recovery of towed sensors
CN107108031A (zh) 悬停飞行器及其操控方法
KR20190050679A (ko) 드론용 낙하산 장치
US20210237876A1 (en) Parasite aircraft for airborne deployment and retrieval
EP2892800A1 (fr) Lanceur de véhicule sous-marin sans équipage
CN112124610A (zh) 用于垂直起降飞行器的着舰装置及舰船
WO2018041254A1 (fr) Support pour article largué
US7334757B2 (en) Airship retrieval system
NL2013876B1 (en) Wind power generation system and method of operating the same.
US2345615A (en) Multiple weight aerial delivery container launching rig
CN112607026A (zh) 一种多旋翼无人机自动回收释放装置及方法

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18857677

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18857677

Country of ref document: EP

Kind code of ref document: A1

122 Ep: pct application non-entry in european phase

Ref document number: 18857677

Country of ref document: EP

Kind code of ref document: A1