CN115477019A - Modularization hydrogen energy unmanned aerial vehicle - Google Patents

Modularization hydrogen energy unmanned aerial vehicle Download PDF

Info

Publication number
CN115477019A
CN115477019A CN202211267658.XA CN202211267658A CN115477019A CN 115477019 A CN115477019 A CN 115477019A CN 202211267658 A CN202211267658 A CN 202211267658A CN 115477019 A CN115477019 A CN 115477019A
Authority
CN
China
Prior art keywords
hydrogen
rotorcraft
fuel cell
hydrogen fuel
main
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.)
Pending
Application number
CN202211267658.XA
Other languages
Chinese (zh)
Inventor
沈轶岭
唐煜翔
肖赫
刘海东
封承霖
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.)
Harbin Institute of Technology
Chongqing Research Institute of Harbin Institute of Technology
Original Assignee
Chongqing Research Institute of Harbin Institute of Technology
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 Chongqing Research Institute of Harbin Institute of Technology filed Critical Chongqing Research Institute of Harbin Institute of Technology
Priority to CN202211267658.XA priority Critical patent/CN115477019A/en
Publication of CN115477019A publication Critical patent/CN115477019A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/30—Fuel systems for specific fuels
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
    • H01M8/04089—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
    • H01M8/04201—Reactant storage and supply, e.g. means for feeding, pipes
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Fuel Cell (AREA)

Abstract

The invention provides a modularized hydrogen energy unmanned aerial vehicle, and relates to the field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a main body, a power module and a hydrogen fuel energy supply module; a plurality of main force arms of the rotor wing machine are uniformly arranged on the main body in the circumferential direction, and the main force arms of the rotor wing machine are jointly connected with an undercarriage; the power module comprises rotorcraft external force arms with the same number as the rotorcraft main force arms, the rotorcraft external force arms are respectively detachably arranged at the outer ends of the rotorcraft main force arms, and a take-off and landing rotor module is arranged on any rotorcraft external force arm; the hydrogen fuel energy supply module comprises a hydrogen fuel cell module and a hydrogen gas cylinder which are arranged on the main body, the hydrogen gas cylinder and the hydrogen fuel cell can be detachably arranged on the main body, and the hydrogen fuel cell and the take-off and landing rotor module are connected with each other and are detachably connected through a wire connector. In the invention, the use range is enlarged by the modularized splicing design, and the design of the hydrogen fuel cell has the advantages of long endurance time and environmental protection.

Description

Modularization hydrogen energy unmanned aerial vehicle
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a modularized hydrogen energy unmanned aerial vehicle.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar. The airplane can take off like a common airplane or launch and lift off by a boosting rocket under the radio remote control, and can also be carried to the air by a mother airplane to be thrown and flown. During recovery, the aircraft can automatically land in the same way as a common aircraft landing process, and can also be recovered by a remote control parachute or a blocking net, so that the aircraft can be repeatedly used.
The unmanned aerial vehicle used at present mainly has the following defects:
1. unmanned aerial vehicle mainly uses lithium cell or fuel mostly as the energy, has the relatively short problem of continuation of the journey among the lithium cell application, can produce certain pollution to the environment among the fuel application, has the problem of not environmental protection.
2. The most formula structure as an organic whole of unmanned aerial vehicle, the unmanned aerial vehicle continuation of the journey mileage and the driving system of different specification models all are different, and the unmanned aerial vehicle of different specification models can only use in specific scene, and application range is limited relatively.
To sum up, we propose a modular hydrogen energy unmanned aerial vehicle to solve the above technical problems.
Disclosure of Invention
The invention aims to provide a modularized hydrogen energy unmanned aerial vehicle, the modularized splicing design increases the application range, and the design of a hydrogen fuel cell has the advantages of long endurance time and environmental protection.
The embodiment of the invention is realized by the following steps:
the embodiment of the application provides a modularized hydrogen energy unmanned aerial vehicle, which comprises a main body, a power module and a hydrogen fuel energy supply module;
a plurality of main force arms of the rotor wing machine are uniformly arranged in the circumferential direction of the main body, and the main force arms of the rotor wing machine are jointly connected with an undercarriage;
the power module comprises a plurality of rotor machine external force arms with the same number as the rotor machine main force arms, the plurality of rotor machine external force arms are respectively detachably arranged at the outer ends of the plurality of rotor machine main force arms, and any one of the rotor machine external force arms is provided with a lifting rotor module;
the hydrogen fuel energy supply module comprises a hydrogen fuel cell module arranged on the main body and a hydrogen cylinder used for conveying hydrogen to the hydrogen fuel cell module, the hydrogen cylinder and the hydrogen fuel cell can be detachably arranged on the main body, and the hydrogen fuel cell and the lifting rotor module, the hydrogen fuel cell and the main body are detachably and electrically connected through a wire connector.
In some embodiments of the present invention, the power module further comprises a horn connecting member, the horn connecting member has three connecting portions, one of the connecting portions of the horn connecting member is detachably disposed at an outer end of the main arm of the rotorcraft, and the other two connecting portions of the horn connecting member are disposed with the power module.
In some embodiments of the present invention, the take-off and landing rotor module includes a driving motor disposed on an upper side of an external force arm of the rotor machine, and an output shaft of the driving motor is provided with a rotor member.
In some embodiments of the present invention, the arm connector, the rotorcraft outer arm, and the rotorcraft main arm are all hollow structures, and the lead wire for connecting the driving motor to the hydrogen fuel cell is disposed in the rotorcraft outer arm, the arm connector, and the rotorcraft main arm.
In some embodiments of the present invention, the hydrogen cylinder is disposed at an upper side of the main body, the hydrogen fuel cell is disposed at a rear side of a lower side of the main body, and a connection hole for externally connecting a load module is formed at a front side of the lower side of the main body.
In some embodiments of the present invention, the hydrogen cylinders are connected to the main body by a clip.
In some embodiments of the present invention, slots are symmetrically formed on a bottom side of the main body, and the hydrogen fuel cell module is provided with an insert strip that is inserted into and matched with the slots.
Compared with the prior art, the embodiment of the invention has at least the following advantages or beneficial effects:
(1) The hydrogen cylinders are detachably arranged, so that the hydrogen cylinders with different capacities can be replaced according to different flight time requirements, and the hydrogen cylinder has the advantages of capability of flying for a long time and replacement of small hydrogen cylinders, and light flight in a short time; the hydrogen fuel cell is detachably arranged, so that the hydrogen fuel cells with different output powers can be replaced according to different power requirements of the unmanned aerial vehicle; the power module can be disassembled, different power systems can be replaced according to different task requirements of the airplane, and the flexibility is stronger. According to the invention, the hydrogen cylinder, the hydrogen fuel cell, the power module and the main body are all in a modularized splicing design, and various modules (the hydrogen cylinder, the hydrogen fuel cell and the power module) which are more matched with a flight mission can be selected as far as possible according to flight mission requirements, so that the integral optimized proportion of the unmanned aerial vehicle is achieved, the unmanned aerial vehicles with different performances are formed, and the application range is wider.
(2) In the invention, the hydrogen fuel cell is adopted as a main energy source, so that the endurance time of the airplane is longer compared with that of a common lithium battery airplane, and the airplane is more environment-friendly compared with a diesel airplane.
(3) The lead of the hydrogen fuel cell connected with the driving motor is arranged in the external force arm of the rotor machine, the horn connecting piece and the main force arm of the rotor machine, so that the lead is arranged in a concealed manner, and the hydrogen fuel cell is more reasonable and practical.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram of a modular hydrogen energy unmanned aerial vehicle according to an embodiment of the invention;
FIG. 2 is a schematic structural diagram of a main body according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a storage bin according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a horn connecting member according to an embodiment of the present invention.
An icon: 1-undercarriage, 2-hydrogen fuel cell, 3-storage bin, 4-rotor piece, 5-driving motor, 6-rotor external force arm, 7-hydrogen cylinder, 8-rotor main force arm, 9-main body, 10-hoop, 11-slot, 12-cutting strip, 13-arm connecting piece, 14-nut, 15-external thread.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the embodiments of the present invention, it should be noted that, if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate an orientation or a positional relationship based on an orientation or a positional relationship shown in the drawings, or an orientation or a positional relationship which is usually arranged when the product of the present invention is used, it is only for convenience of description and simplification of the description, but does not indicate or imply that the device or the element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not require that the components be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the embodiments of the present invention, "a plurality" means at least 2.
In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Examples
Referring to fig. 1 to 4, the present embodiment provides a modular hydrogen energy unmanned aerial vehicle, which includes a main body 9, a power module and a hydrogen fuel energy supply module;
a plurality of main force arms 8 of the rotor wing are uniformly arranged on the main body 9 in the circumferential direction, and the plurality of main force arms 8 of the rotor wing are jointly connected with an undercarriage 1;
the power module comprises a plurality of rotor machine external force arms 6 with the same number as the rotor machine main force arms 8, the plurality of rotor machine external force arms 6 are respectively detachably arranged at the outer ends of the plurality of rotor machine main force arms 8, and any one rotor machine external force arm 6 is provided with a lifting rotor module;
the hydrogen fuel energy supply module comprises a hydrogen fuel cell 2 module arranged on the main body 9 and a hydrogen cylinder 7 used for delivering hydrogen to the hydrogen fuel cell 2 module, wherein the hydrogen cylinder 7 and the hydrogen fuel cell 2 can be detachably arranged on the main body 9, and the hydrogen fuel cell 2 and the lifting rotor module and the hydrogen fuel cell 2 and the main body 9 are detachably and electrically connected through wire connectors.
On the first hand, the hydrogen cylinders 7 can be detachably arranged, the hydrogen cylinders 7 with different capacities can be replaced according to different flight time requirements, and the hydrogen cylinder has the advantages that the hydrogen cylinder can fly in a long flight time and can also replace small hydrogen cylinders 7 to fly in a light weight manner in a short flight time; the hydrogen fuel cell 2 is detachably arranged, so that the hydrogen fuel cell 2 with different output power can be replaced according to different power requirements of the unmanned aerial vehicle; due to the detachable arrangement of the power module, different power systems can be replaced according to different task requirements of the airplane, and the flexibility is higher. In the invention, the hydrogen cylinder 7, the hydrogen fuel cell 2, the power module and the main body 9 are all in a modularized splicing design, and all modules (the hydrogen cylinder 7, the hydrogen fuel cell 2 and the power module) which are more matched with a flight task can be selected as far as possible according to the flight task requirement, so that the integral optimized proportion of the unmanned aerial vehicle is achieved, the unmanned aerial vehicles with different performances are formed, and the application range is wider. In the invention, the hydrogen fuel cell 2 is used as a main energy source, so that the endurance time of the airplane is longer compared with that of a common lithium battery airplane, and the airplane is more environment-friendly compared with a diesel airplane.
The hydrogen cylinders 7 and the hydrogen fuel cell 2 are communicated by quick connectors to facilitate replacement of the hydrogen fuel cell 2 or the hydrogen cylinders 7.
In some embodiments of the present invention, the present invention further comprises a boom connecting member 13, the boom connecting member 13 has three connecting portions, one of the connecting portions of the boom connecting member 13 is detachably disposed at the outer end of the main arm 8 of the rotary wing machine, and the other two connecting portions of the boom connecting member 13 are disposed with the power module.
In the above embodiment, the three connection portions are uniformly distributed along the same circumference at intervals, the connection portions connected to the main arm 8 of the rotorcraft are connected by rivets, the outer arm 6 of the rotorcraft of the power module is provided with a nut 14, and the connection portions are provided with external threads 15 in threaded fit with the nut 14, so as to realize detachable connection of the outer arm 6 of the rotorcraft and the connection portions.
In some embodiments of the present invention, the take-off and landing rotor module includes a driving motor 5 disposed on an upper side of an external force arm 6 of the rotor machine, and an output shaft of the driving motor 5 is provided with a rotor member 4.
In the above-mentioned embodiment, driving motor 5 drives rotor 4 and rotates, for unmanned aerial vehicle takes off and land provides lift, driving motor 5 has the stable advantage of power take off as the power supply.
In some embodiments of the present invention, the arm connector 13, the rotorcraft outer arm 6, and the rotorcraft main arm 8 are all hollow structures, and the lead wires of the driving motor 5 connected to the hydrogen fuel cell 2 are disposed in the rotorcraft outer arm 6, the arm connector 13, and the rotorcraft main arm 8.
In the above embodiment, the hollow tube of the external force arm 6 of the rotary wing machine is inserted into the connecting part, and then the nut 14 is connected with the external thread 15 of the connecting part in a thread fit manner, the wire of the driving motor 5 is penetrated in the hollow structure of the external force arm 6 of the rotary wing machine, the arm connecting part 13 and the main force arm 8 of the rotary wing machine, and the wire connector is located at the butt joint of the connecting part and the external force arm 6 of the rotary wing machine, so that the connection of the wire is convenient.
In some embodiments of the present invention, the hydrogen cylinders 7 are disposed on the upper side of the main body 9, the hydrogen fuel cell 2 is disposed behind the lower side of the main body 9, and a connection hole for externally connecting a load module is formed in the front of the lower side of the main body 9.
In the above embodiment, the external load module can be a loading bin, and the loading bin can be detachably arranged on the connecting hole through the bolt, so that the external load module can be replaced, and different loading requirements can be used.
In some embodiments of the present invention, the hydrogen cylinders 7 are connected to the main body 9 by clips 10.
In the above embodiment, the design of the clamp 10 connects the hydrogen cylinder 7 and the main body 9 together, and the hydrogen cylinder 7 can be detachably disposed, so that the hydrogen cylinder 7 can be conveniently replaced.
In some embodiments of the present invention, slots 11 are symmetrically formed on the bottom side of the main body 9, and the hydrogen fuel cell 2 module is provided with inserting strips 12 which are inserted into the slots 11.
In the above embodiment, the hydrogen fuel cell 2 module has the storage chamber 3, the hydrogen fuel cell 2 can be detachably placed in the storage chamber 3, the inserting strips 12 are arranged on two sides of the storage chamber 3, and the two inserting strips 12 are respectively matched with the two inserting slots 11 in an inserting manner, so as to realize detachable connection setting of the hydrogen fuel cell 2 and the main body 9. Main fuselage 9 and the rotatory card location of collecting chamber 3 accessible pivoted also can pass through screw location (screw is all seted up to main fuselage 9 and collecting chamber 3, two kinds of screw butt joints, and two kinds of screws pass through the screw connection to realize collecting chamber 3 and the removable connection of main fuselage 9).
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (7)

1. A modularized hydrogen energy unmanned aerial vehicle is characterized by comprising a main body, a power module and a hydrogen fuel energy supply module;
a plurality of main force arms of the rotor wing machine are uniformly arranged in the circumferential direction of the main body, and the main force arms of the rotor wing machine are jointly connected with an undercarriage;
the power module comprises a plurality of rotorcraft external force arms with the same number as the main force arms of the rotorcraft, the plurality of rotorcraft external force arms are respectively detachably arranged at the outer ends of the plurality of rotorcraft main force arms, and any one of the rotorcraft external force arms is provided with a take-off and landing rotor module;
hydrogen fuel energy supply module including set up in the hydrogen fuel cell module of main fuselage, and be used for to the hydrogen gas cylinder of hydrogen fuel cell module transport hydrogen, hydrogen gas cylinder with hydrogen fuel cell all can dismantle set up in main fuselage, hydrogen fuel cell with take off and land between the rotor module hydrogen fuel cell with all connect through the detachable electricity of wire connector between the main fuselage.
2. The modular hydrogen energy unmanned aerial vehicle of claim 1, further comprising a horn connector, wherein the horn connector has three connecting portions, one of the connecting portions of the horn connector is detachably disposed at an outer end of the main force arm of the rotorcraft, and the other two connecting portions of the horn connector are disposed with the power module.
3. The unmanned aerial vehicle as claimed in claim 2, wherein the take-off and landing rotor module comprises a driving motor disposed on an upper side of an external arm of the rotor machine, and an output shaft of the driving motor is provided with a rotor member.
4. The modular hydrogen energy unmanned aerial vehicle of claim 3, wherein the horn connection member, the outboard arm of the rotorcraft and the main arm of the rotorcraft are all hollow structures, and the wires for connecting the driving motor to the hydrogen fuel cell are arranged in the outboard arm of the rotorcraft, the horn connection member and the main arm of the rotorcraft.
5. The unmanned aerial vehicle as claimed in claim 1, wherein the hydrogen cylinder is disposed on the upper side of the main body, the hydrogen fuel cell is disposed behind the lower side of the main body, and a connection hole for externally connecting a load module is formed in front of the lower side of the main body.
6. The modular hydrogen energy unmanned aerial vehicle of claim 1, wherein the hydrogen cylinders are connected to the main body by clamps.
7. The modular hydrogen energy unmanned aerial vehicle of claim 1, wherein slots are symmetrically formed in the bottom side of the main body, and the hydrogen fuel cell module is provided with a plug strip which is in plug fit with the slots.
CN202211267658.XA 2022-10-17 2022-10-17 Modularization hydrogen energy unmanned aerial vehicle Pending CN115477019A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211267658.XA CN115477019A (en) 2022-10-17 2022-10-17 Modularization hydrogen energy unmanned aerial vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211267658.XA CN115477019A (en) 2022-10-17 2022-10-17 Modularization hydrogen energy unmanned aerial vehicle

Publications (1)

Publication Number Publication Date
CN115477019A true CN115477019A (en) 2022-12-16

Family

ID=84395187

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211267658.XA Pending CN115477019A (en) 2022-10-17 2022-10-17 Modularization hydrogen energy unmanned aerial vehicle

Country Status (1)

Country Link
CN (1) CN115477019A (en)

Similar Documents

Publication Publication Date Title
US8660712B2 (en) Reconfigurable aircraft
CN110035953B (en) Aircraft, in particular hybrid aircraft, with a battery
CN102520727B (en) Reconnaissance system with unmanned plane
WO2017180392A1 (en) Modular aircraft system
WO2020107373A1 (en) Power assembly, power system and unmanned aerial vehicle
CN101391651A (en) Foldable Y shaped three axis two-layer six rotorcraft
CN108001677B (en) Falling off tethered vertical take-off and landing fixed wing unmanned aerial vehicle
CN112770972A (en) Modular multi-rotor unmanned aerial vehicle driven by turbine generator
CN110626495A (en) Small coaxial double-rotor type unmanned aerial vehicle
CN208715479U (en) Modularization supersonic speed unmanned plane
CN214824104U (en) Unmanned aerial vehicle
CN203593161U (en) Variable multi-rotor UAV (unmanned aerial vehicle)
De Wagter et al. Design and testing of a vertical take-off and landing UAV optimized for carrying a hydrogen fuel cell with a pressure tank
Rajendran et al. The development of a small solar powered electric unmanned aerial vehicle systems
CN110422339B (en) Method for assembling coaxial double-rotor unmanned aerial vehicle
CN111717365A (en) Carry polymorphic type unmanned aerial vehicle's dirigible
CN210526847U (en) Small coaxial double-rotor type unmanned aerial vehicle
CN115477019A (en) Modularization hydrogen energy unmanned aerial vehicle
CN212313298U (en) Small-sized solar unmanned aerial vehicle
Chiang et al. Systems integration of a hybrid PEM fuel cell/battery powered endurance UAV
CN211568303U (en) Unmanned aerial vehicle for circuit cruise detection
CN108944470A (en) It is small-sized across solar energy unmanned plane and its energy management method round the clock
CN205952273U (en) Airship
CN111731465B (en) Fuselage frame rack construction and unmanned aerial vehicle for unmanned aerial vehicle
CN212267846U (en) Tilting hybrid electric-transmission vertical take-off and landing fixed-wing unmanned aerial vehicle

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
TA01 Transfer of patent application right
TA01 Transfer of patent application right

Effective date of registration: 20231031

Address after: 401135 No. 618 Liangjiang Avenue, Longxing Town, Yubei District, Chongqing

Applicant after: Chongqing Research Institute of Harbin Institute of Technology

Applicant after: HARBIN INSTITUTE OF TECHNOLOGY

Address before: 618 Liangjiang Avenue, Longxing Town, Yubei District, Chongqing

Applicant before: Chongqing Research Institute of Harbin Institute of Technology