CN211253048U - Unmanned aerial vehicle powered by hydrogen fuel cell - Google Patents
Unmanned aerial vehicle powered by hydrogen fuel cell Download PDFInfo
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- CN211253048U CN211253048U CN201922247395.6U CN201922247395U CN211253048U CN 211253048 U CN211253048 U CN 211253048U CN 201922247395 U CN201922247395 U CN 201922247395U CN 211253048 U CN211253048 U CN 211253048U
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- 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
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- 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
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Abstract
The utility model relates to a general aviation field, concretely relates to unmanned aerial vehicle of hydrogen fuel cell power. Including well fuselage, horizontal arrangement right fuselage and left fuselage on the right side of well fuselage and left side and left fuselage, preceding wing, back wing, vertical fin and arrange the power device of well fuselage tail end, well fuselage right fuselage with the inside equipartition of left fuselage has been put hydrogen storage device, hydrogen storage device is used for the storage compressed hydrogen, the inside hydrogen fuel galvanic pile that has still arranged of well fuselage, right fuselage with left fuselage for well fuselage symmetrical arrangement. The utility model discloses a three fuselage design scheme can divide into the great hydrogen storage device of volume left, in, the three hydrogen storage device in the right side, settle respectively in the three fuselage in the left side in the right side, effectively reduces single fuselage volume when guaranteeing that enough big space stores hydrogen fuel, and then reduces unmanned aerial vehicle's flight resistance.
Description
Technical Field
The utility model relates to a general aviation field, concretely relates to unmanned aerial vehicle of hydrogen fuel cell power.
Background
In the development of unmanned aerial vehicles, endurance has always been a big problem. The traditional battery with lower energy density cannot meet the requirement of the unmanned aerial vehicle for long-term navigation. Adopt fuel engine, though can satisfy the long endurance demand, its big and not environmental protection's of noise shortcoming has restricted unmanned aerial vehicle's development.
In the 60's of the 20 th century, hydrogen fuel cells have been successfully used in the aerospace field. An Apollo spacecraft that travels to and from space and the earth has installed a hydrogen fuel cell. In the field of unmanned aerial vehicles, a plurality of domestic and foreign companies have started research and release products, and after the hydrogen fuel cell technology is adopted, the endurance time of the unmanned aerial vehicle is obviously prolonged. The unmanned aerial vehicle adopting the hydrogen fuel cell has the characteristics of no pollution, no noise and high efficiency. The hydrogen fuel cell is applied to the unmanned aerial vehicle, and the technical problem of miniaturization of the hydrogen fuel cell cannot be avoided. The hydrogen fuel that present unmanned aerial vehicle used is compression gaseous hydrogen basically, and its hydrogen storage device is bulky, for satisfying its installation, needs great fuselage volume, will lead to the unmanned aerial vehicle resistance great. If use less fuselage will reduce hydrogen storage device volume to shorten unmanned aerial vehicle duration, can't reach the demand during long voyage.
SUMMERY OF THE UTILITY MODEL
The utility model provides a technical problem provide an unmanned aerial vehicle of small-size hydrogen fuel cell power.
The utility model provides a technical scheme that its technical problem adopted is:
the utility model provides an unmanned aerial vehicle of hydrogen fuel cell power, is in including well fuselage, horizontal arrangement right fuselage and left side of well fuselage the right fuselage and left fuselage, preceding wing, back wing, vertical fin and arranging the power device of well fuselage tail end, well fuselage right fuselage with the inside equipartition of left fuselage has put hydrogen storage device, hydrogen storage device is used for saving compressed hydrogen, the inside hydrogen fuel galvanic pile that has still been arranged of well fuselage, right fuselage with left fuselage for well fuselage symmetrical arrangement, preceding wing horizontal symmetry install well fuselage right fuselage with the front end of left fuselage well fuselage with right fuselage with form the symmetrical left and right sides preceding wing inner segment between the left fuselage right side with left fuselage left side forms the symmetrical left and right sides preceding wing outer segment, back wing horizontal symmetry installs well fuselage, The right side fuselage with the rear end of left side fuselage the middle fuselage with right side fuselage with form the back wing inner segment about of symmetry between the fuselage of a left side right side fuselage right side with the back wing outer segment about left side fuselage left side forms the symmetry, right side fuselage with left side fuselage afterbody symmetry is provided with the vertical fin, the hydrogen fuel galvanic pile is used for handling the middle fuselage right side fuselage with compressed hydrogen among the inside hydrogen storage device of left side fuselage will the chemical energy of hydrogen turns into the required electric energy of unmanned aerial vehicle to get up electric energy storage, follow-up doing power device provides the electric energy, drives unmanned aerial vehicle and moves ahead, the inside integrated flight control system of middle fuselage, electromechanical system and aviation system.
Furthermore, front wing tip winglets and elevators are symmetrically arranged on the left and right front wing outer sections, and rear wing tip winglets and ailerons are symmetrically arranged on the left and right rear wing outer sections.
Further, the left and right rear wing inner sections are provided with flaps.
Further, a rudder is arranged on the rear side of the vertical tail.
Furthermore, hydrogen fuel transmission pipelines are arranged in the left and right front wing inner sections and the left and right rear wing inner sections and are connected with hydrogen storage devices inside the right fuselage and the left fuselage.
Further, the lower ends of the middle fuselage, the right fuselage and the left fuselage are provided with undercarriage.
Preferably, the middle fuselage, the right fuselage and the left fuselage are streamlined fuselages.
Further, the middle fuselage, the right fuselage and the left fuselage may all be equipped with mission loads.
The utility model has the advantages that:
1. adopt three fuselage design scheme, can divide into the great hydrogen storage device of volume left, in, three hydrogen storage device on the right side, settle respectively in the three fuselage on the left and in the right side, effectively reduce single fuselage volume when guaranteeing that enough big space stores hydrogen fuel, and then reduce unmanned aerial vehicle's flight resistance.
2. Left and right fuselage is connected through front and back wing, can effectual enhancement unmanned aerial vehicle's structural strength, and task load all can be installed to left and middle and right fuselage moreover, makes its space effective utilization.
Drawings
FIG. 1 is a three-dimensional structure of the present invention;
labeled as:
1. the hydrogen storage device comprises a middle fuselage, 101, a hydrogen storage device, 102, a hydrogen fuel cell stack, 2, a right fuselage, 3, a left fuselage, 4, a front wing, 41, a front wing inner section, 42, a front wing outer section, 43, a front wing tip winglet, 44, an elevator, 5, a rear wing, 51, a rear wing inner section, 52, a rear wing outer section, 53, a rear wing tip winglet, 54, an aileron, 55, a flap, 6, a vertical tail, 61, a rudder, 7 and a power device.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
The utility model provides an unmanned aerial vehicle of hydrogen fuel cell power, as shown in figure 1, including well fuselage 1, horizontal arrangement in the right of well fuselage 1 and the left right fuselage 2 and left fuselage 3, preceding wing 4, back wing 5, vertical fin 6 and arrange power device 7 of well fuselage 1 tail end, well fuselage 1, right fuselage 2 and the inside hydrogen storage device 101 that has arranged of left fuselage 3, hydrogen storage device 101 is used for the storage to compress hydrogen, still arranges hydrogen fuel cell stack 102 in the fuselage 1, right fuselage 2 and left fuselage 3 are symmetrical for well fuselage 1, and preceding wing 4 horizontal symmetry is installed at the front end of fuselage 1, right fuselage 2 and left fuselage 3, forms symmetrical left and right preceding wing inner segment 41 between fuselage 1 and right fuselage 2 and left fuselage 3, forms symmetrical left and right preceding wing outer segment 42 in right fuselage 2 right side and left fuselage 3 left side, and back wing 5 horizontal symmetry is installed at well fuselage 1, right fuselage 2, The rear end of right side fuselage 2 and left fuselage 3, form the back wing interior section 51 about the symmetry between mesofuselage 1 and right fuselage 2 and left fuselage 3, form the back wing exterior section 52 about the symmetry on right fuselage 2 right side and left fuselage 3 left side, right fuselage 2 and the symmetry of left fuselage 3 afterbody are provided with vertical fin 6, hydrogen fuel galvanic pile 102 is arranged in handling fuselage 1, the compression hydrogen in the inside hydrogen storage device 101 of right fuselage 2 and left fuselage 3, turn into the chemical energy of hydrogen the required electric energy of unmanned aerial vehicle, and store the electric energy, follow-up for power device 7 provides the electric energy, drive unmanned aerial vehicle moves ahead.
Furthermore, the wingtips of the left and right front wing outer sections 42 are set as front wing wingtip winglets 43, and the rear sides of the left and right front wing outer sections 42 are hinged with elevators 44; the wingtips of the left and right rear wing outer sections 52 are rear wing wingtip winglets 53, the rear sides of the left and right rear wing outer sections 52 are hinged with ailerons 54, the rear sides of the left and right rear wing inner sections 51 are hinged with wing flaps 55, and the vertical tails 6 at the tails of the right fuselage 2 and the left fuselage 3 are hinged with rudders 61. Wingtip winglets at two ends of the front wing 4 and the rear wing 5 are used for reducing induced resistance when the unmanned aerial vehicle flies; the elevators 44 are used for pitching steering of the drone; the ailerons 54 are used for roll control of the drone; the flap 55 is used for increasing lift force when the unmanned aerial vehicle takes off and lands; the rudder 61 is used for the sailing steering of the drone.
Pipelines for hydrogen fuel transmission are arranged inside the left front wing inner section 41, the right front wing inner section 41, the left rear wing inner section 51 and the right rear wing inner section 51, the pipelines are connected with the hydrogen storage devices 101 inside the right fuselage 2 and the left fuselage 3, then the hydrogen fuel galvanic pile inside the middle fuselage 1 is connected in a unified mode, the three-section hydrogen storage devices 101 are installed in the three fuselages respectively, and the size of each fuselage is effectively reduced while the large enough space is guaranteed for storing hydrogen fuel.
Further, the lower ends of the middle fuselage 1, the right fuselage 2 and the left fuselage 3 can be provided with undercarriage, the front end of the lower surface of the middle fuselage 1 can be provided with undercarriage, and the rear ends of the lower surfaces of the right fuselage 2 and the left fuselage 3 are symmetrically provided with undercarriage, so that a three-point undercarriage is formed. Or the front and rear ends of the lower surfaces of the right fuselage 2 and the left fuselage 3 are symmetrically provided with undercarriages to form a four-point undercarriage.
Preferably, the middle fuselage 1, the right fuselage 2 and the left fuselage 3 are streamline fuselages which can be provided with mission loads, and a flight control system, an electromechanical system and an aeronautical system are integrated in the middle fuselage 1.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. The utility model provides a hydrogen fuel cell powered unmanned aerial vehicle which characterized in that: including well fuselage (1), horizontal arrangement right fuselage (2) and left fuselage (3) on the right of well fuselage (1) and left side, preceding wing (4), back wing (5), vertical fin (6) and arrange power device (7) at well fuselage (1) tail end, well fuselage (1) right fuselage (2) with hydrogen storage device (101) have been put to left fuselage (3) inside equipartition, hydrogen storage device (101) are used for the storage compressed hydrogen, well fuselage (1) inside has still arranged hydrogen fuel pile (102), right fuselage (2) with left fuselage (3) for well fuselage (1) symmetrical arrangement, preceding wing (4) horizontal symmetry is installed well fuselage (1), right fuselage (2) and the front end of left fuselage (3) form symmetrical left and right sides preceding wing interior section (41) between well fuselage (1) with right fuselage (2) and left fuselage (3), right side fuselage (2) right side with left side fuselage (3) left side forms the outer section of wing (42) before the left and right sides of symmetry, back wing (5) horizontal symmetry install in fuselage (1) right side fuselage (2) with the rear end of left side fuselage (3) fuselage (1) with right side fuselage (2) with form the back wing inner segment (51) about the symmetry between left side fuselage (3) right side fuselage (2) right side with left side fuselage (3) left side forms the outer section of back wing (52) about the symmetry, right side fuselage (2) with left side fuselage (3) afterbody symmetry is provided with vertical fin (6), hydrogen fuel pile (102) are used for handling the compressed hydrogen in fuselage (1), right side fuselage (2) and the inside hydrogen storage device (101) of left side fuselage (3), will the chemical energy of hydrogen turns into the required electric energy of unmanned aerial vehicle, the electric energy is stored and then is supplied to the power device (7) to drive the unmanned aerial vehicle to move forward, and a flight control system, an electromechanical system and an aeronautical electric system are integrated in the middle fuselage (1).
2. The hydrogen fuel cell powered drone of claim 1, characterized in that: front wing tip winglets (43) and elevators (44) are symmetrically arranged on the left and right front wing outer sections (42), and rear wing tip winglets (53) and ailerons (54) are symmetrically arranged on the left and right rear wing outer sections (52).
3. The hydrogen fuel cell powered drone of claim 2, characterized in that: and flaps (55) are arranged on the inner sections (51) of the left rear wing and the right rear wing.
4. A hydrogen fuel cell powered drone according to claim 3, characterized in that: a rudder (61) is arranged at the rear side of the vertical tail (6).
5. A hydrogen fuel cell powered drone according to any of claims 1 to 4, characterized in that: hydrogen fuel transmission pipelines are arranged in the left and right front wing inner sections (41) and the left and right rear wing inner sections (51) and are connected with the right fuselage (2) and a hydrogen storage device (101) inside the left fuselage (3).
6. The hydrogen fuel cell powered drone of claim 5, characterized in that: the lower ends of the middle fuselage (1), the right fuselage (2) and the left fuselage (3) are provided with undercarriage.
7. The hydrogen fuel cell powered drone of claim 6, characterized in that: the middle machine body (1), the right machine body (2) and the left machine body (3) are streamline machine bodies.
8. The hydrogen fuel cell powered drone of claim 7, characterized in that: the middle machine body (1), the right machine body (2) and the left machine body (3) can be provided with task loads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922247395.6U CN211253048U (en) | 2019-12-16 | 2019-12-16 | Unmanned aerial vehicle powered by hydrogen fuel cell |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922247395.6U CN211253048U (en) | 2019-12-16 | 2019-12-16 | Unmanned aerial vehicle powered by hydrogen fuel cell |
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| Publication Number | Publication Date |
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| CN211253048U true CN211253048U (en) | 2020-08-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201922247395.6U Active CN211253048U (en) | 2019-12-16 | 2019-12-16 | Unmanned aerial vehicle powered by hydrogen fuel cell |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114919752A (en) * | 2022-04-26 | 2022-08-19 | 西北工业大学 | ECMS-MPC-based energy management method for hydrogen fuel hybrid unmanned aerial vehicle |
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2019
- 2019-12-16 CN CN201922247395.6U patent/CN211253048U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114919752A (en) * | 2022-04-26 | 2022-08-19 | 西北工业大学 | ECMS-MPC-based energy management method for hydrogen fuel hybrid unmanned aerial vehicle |
| CN114919752B (en) * | 2022-04-26 | 2024-05-03 | 西北工业大学 | Energy management method of hydrogen fuel hybrid unmanned aerial vehicle based on ECMS-MPC |
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