CN110466781B - Flying wing type solar auxiliary power supply unmanned aerial vehicle - Google Patents
Flying wing type solar auxiliary power supply unmanned aerial vehicle Download PDFInfo
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- CN110466781B CN110466781B CN201910765327.0A CN201910765327A CN110466781B CN 110466781 B CN110466781 B CN 110466781B CN 201910765327 A CN201910765327 A CN 201910765327A CN 110466781 B CN110466781 B CN 110466781B
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- flank
- fixedly connected
- fixed connection
- unmanned aerial
- plate
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- 238000010248 power generation Methods 0.000 claims abstract description 9
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 16
- 239000011521 glass Substances 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 9
- 229910052742 iron Inorganic materials 0.000 claims description 8
- 238000007789 sealing Methods 0.000 claims description 5
- 238000005187 foaming Methods 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003760 hair shine Effects 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- B64D27/353—
Abstract
The invention discloses a flying wing type solar auxiliary power supply unmanned aerial vehicle, which relates to the field of unmanned aerial vehicles and comprises a rack main body, wherein two sides of the rack main body are fixedly connected with first side wings, one ends of the first side wings, far away from the rack main body, are fixedly connected with second side wings, one ends of the second side wings, far away from the first side wings, are fixedly connected with side wings, and a power generation mechanism is arranged in the second side wings and comprises a solar cell panel arranged in the second side wings, the top ends of the solar cell panel are fixedly connected with a reflection device, and the reflection device comprises a reflection shell.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a flying wing type solar auxiliary power supply unmanned aerial vehicle.
Background
Unmanned aerial vehicles have wide potential in military application of battle reconnaissance in cities and complex terrain conditions, and are currently hot research hotspots in all countries of the world. In the aspect of military practicability, especially as an unmanned aerial vehicle for urban operation reconnaissance, the unmanned aerial vehicle can quickly cruise, can take off and land vertically, has good flexibility and maneuverability, can hover, has low noise, autonomously flies, is easy to control and the like.
The utility model discloses a chinese utility model patent document with publication number CN207242011U discloses a flight stability's all-wing aircraft formula unmanned aerial vehicle, and this unmanned aerial vehicle can keep steadily when flight to avoid sideslipping, in order to satisfy the flight requirement, but this unmanned aerial vehicle's defect lies in its duration low, thereby great reduction unmanned aerial vehicle's work efficiency, the urgent need to improve.
Disclosure of Invention
The invention aims to provide a flying wing type solar auxiliary power supply unmanned aerial vehicle to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme:
a flying wing type solar auxiliary power supply unmanned aerial vehicle comprises a frame main body, wherein two sides of the frame main body are fixedly connected with a first side wing, one end of the first side wing, which is far away from the frame main body, is fixedly connected with a second side wing, one end of the second side wing, which is far away from the first side wing, is fixedly connected with a side wing, a power generation mechanism is arranged in the second side wing, the power generation mechanism comprises a solar cell panel arranged in the second side wing, the top end of the solar cell panel is fixedly connected with a reflection device, the reflection device comprises a reflection shell, one end of the reflection shell is fixedly connected with a side cover, a condenser lens is fixedly connected in the side cover, a reflector lens is fixedly connected at the bottom end of the side cover, a reflection plate is fixedly connected at the top part in the reflection shell, two ends of the second side wing are respectively provided with light-transmitting glass and an exhaust plate, the light-transmitting glass is embedded, the exhaust plate is penetrated and fixedly connected with a rotating shaft, the rotating shaft is rotatably connected with the second side wing, and a sealing mechanism corresponding to the exhaust plate is arranged in the second side wing at the bottom end.
As a further scheme of the invention: and warning lamps are arranged on the side wings.
As a further scheme of the invention: the tail of the rack main body is provided with a driving shell, and driving equipment is arranged in the driving shell.
As a further scheme of the invention: the inside of frame main part is equipped with the installation cavity, is equipped with controlgear and battery in the installation cavity, and the top of installation cavity is equipped with the top cap.
As a further scheme of the invention: the bottom end of the reflecting plate is fixedly provided with a plurality of reflecting bulges.
As a further scheme of the invention: the sealing mechanism comprises a fixed seat, the fixed seat is fixedly connected with the second side wing, mounting grooves communicated with each other are formed in the fixed seat and the second side wing, an electromagnet fixed connection spring, a spring fixed connection iron plate and an iron plate are fixedly connected with the exhaust plate.
As a further scheme of the invention: and the inner surfaces of the side cover and the reflection shell are fixedly adhered with micro-foaming reflection plates.
As a further scheme of the invention: the top of the frame main body is fixedly connected with a radar antenna.
As a further scheme of the invention: and a rain shield is fixedly connected to the second side wing at one side of the exhaust port.
Compared with the prior art, the invention has the beneficial effects that: according to the invention, the reflecting device and the solar cell panel are arranged in the second side wing, so that external light can be guided into the second side wing, power generation is carried out, continuous electric energy is provided for the unmanned aerial vehicle, the cruising ability of the unmanned aerial vehicle is greatly improved, and the working efficiency of the unmanned aerial vehicle is improved.
Drawings
Fig. 1 is a schematic structural diagram of a flying wing type solar auxiliary power supply unmanned aerial vehicle.
Fig. 2 is an internal structure schematic diagram of a second side wing in the flying wing type solar auxiliary power supply unmanned aerial vehicle.
Fig. 3 is a schematic structural diagram of a reflection device in an unmanned aerial vehicle with auxiliary power supply of flying wing type solar energy.
Fig. 4 is a schematic structural diagram of a closing mechanism in the flying wing type solar auxiliary power supply unmanned aerial vehicle.
In the figure: 1-a frame main body, 2-a first side wing, 3-a second side wing, 4-side wings, 5-light-transmitting glass, 6-an exhaust plate, 7-a warning lamp, 8-a driving shell, 9-a top cover, 10-a radar antenna, 11-a solar cell panel, 12-a reflecting device, 13-a rain baffle, 14-an exhaust port, 15-a sealing mechanism, 16-a side cover, 17-a condenser, 18-a reflector, 19-a reflecting shell, 20-a reflecting plate, 21-a reflecting bulge, 22-a fixed seat, 23-an electromagnet, 24-a spring, 25-an iron plate and 26-a rotating shaft.
Detailed Description
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 only a part of the embodiments of the present invention, and not all of the embodiments. 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 the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 in specific cases to those skilled in the art.
Example 1
Referring to fig. 1-4, a flying wing type solar auxiliary power supply unmanned aerial vehicle comprises a frame main body 1, wherein both sides of the frame main body 1 are fixedly connected with a first side wing 2, one end of the first side wing 2 far away from the frame main body 1 is fixedly connected with a second side wing 3, one end of the second side wing 3 far away from the first side wing 2 is fixedly connected with a side wing 4, a power generation mechanism is arranged in the second side wing 3, the power generation mechanism comprises a solar cell panel 11 arranged in the second side wing 3, the top end of the solar cell panel 11 is fixedly connected with a reflection device 12, the reflection device 12 comprises a reflection shell 19, one end of the reflection shell 19 is fixedly connected with a side cover 16, a condenser 17 is fixedly connected in the side cover 16, the bottom end of the side cover 16 is fixedly connected with a reflector 18, the top in the reflection shell 19 is fixedly connected with a reflection plate 20, both ends of the second side wing 3 are respectively provided, the light-transmitting glass 5 is embedded in the surface of the second side wing 3, the side cover 16 is fixedly connected with the light-transmitting glass 5, the second side wing 3 is located on the exhaust plate 6 and provided with an exhaust port 14, the exhaust plate 6 is penetrated through and fixedly connected with a rotating shaft 26, the rotating shaft 26 is rotatably connected with the second side wing 3, and a sealing mechanism 15 corresponding to the exhaust plate 6 is arranged in the second side wing 3 at the bottom end.
Be equipped with warning light 7 on the wing 4, the afterbody of frame main part 1 is equipped with drive shell 8, is equipped with drive arrangement in the drive shell 8, the inside of frame main part 1 is equipped with the installation cavity, is equipped with controlgear and battery in the installation cavity, and the top of installation cavity is equipped with top cap 9, the bottom mounting of reflecting plate 20 is equipped with a plurality of reflection archs 21, the equal fixed subsides of internal surface of side casing 16 and reflection shell 19 are equipped with little foaming reflecting plate 20.
Example 2
Referring to fig. 1 to 4, the other contents of the present embodiment are the same as embodiment 1, except that: the top of the frame body 1 is fixedly connected with a radar antenna 10, and a second side wing 3 at one side of the air outlet 14 is fixedly connected with a rain baffle 13.
Unmanned aerial vehicle is when flight or during the standby, outside sunshine gets into inside the second flank 3 from translucent glass 5, gather after the gathering of condensing lens 17, then on 18 reflection to reflecting plate 20 through the speculum, last light shines on whole solar cell panel 11, solar cell panel 11 electricity generation, thereby attract iron plate 25 to make air discharge plate 6 rotate when electro-magnet 23 circular telegram, exhaust port 14 is opened, the hot-air in the second flank 3 is discharged from exhaust port 14, dispel the heat to solar cell panel 11.
According to the invention, the reflecting device 12 and the solar cell panel 11 are arranged in the second side wing 3, so that external light can be guided into the second side wing 3, power generation is carried out, continuous electric energy is provided for the unmanned aerial vehicle, the cruising ability of the unmanned aerial vehicle is greatly improved, and the working efficiency of the unmanned aerial vehicle is improved.
Claims (1)
1. The utility model provides a flying wing formula solar energy auxiliary power supply unmanned aerial vehicle, includes frame main part (1), the equal fixed connection first flank (2) in both sides of frame main part (1), the one end fixed connection second flank (3) of frame main part (1) are kept away from in first flank (2), the one end fixed connection wing (4) of first flank (2) are kept away from in second flank (3), its characterized in that, be equipped with power generation mechanism in second flank (3), power generation mechanism is including setting up in solar cell panel (11) inside second flank (3), the top fixed connection reflect meter (12) of solar cell panel (11), reflect meter (12) are including reflection shell (19), the one end fixed connection side cover (16) of reflection shell (19), fixed connection condensing lens (17) in side cover (16), the bottom fixed connection speculum (18) of side cover (16), the top fixed connection reflecting plate (20) in the reflecting shell (19), the two ends of the second flank (3) are respectively provided with a light-transmitting glass (5) and an exhaust plate (6), the light-transmitting glass (5) is embedded on the surface of the second flank (3), the side cover (16) is fixedly connected with the light-transmitting glass (5), the second flank (3) is positioned at the exhaust plate (6) and is provided with an exhaust port (14), the exhaust plate (6) is penetrated and fixedly connected with a rotating shaft (26), the rotating shaft (26) is rotatably connected with the second flank (3), a sealing mechanism (15) corresponding to the exhaust plate (6) is arranged in the second flank (3) at the bottom end, the side wings (4) are provided with warning lamps (7), the tail part of the rack main body (1) is provided with a driving shell (8), driving equipment is arranged in the driving shell (8), the inside of the rack main body (1) is provided with an installation cavity, the control equipment and the storage battery are arranged in the mounting cavity, the top of the mounting cavity is provided with a top cover (9), the bottom end of the reflecting plate (20) is fixedly provided with a plurality of reflecting protrusions (21), the closing mechanism (15) comprises a fixed seat (22), the fixed seat (22) is fixedly connected with the second side wing (3), the fixed seat (22) and the second side wing (3) are internally provided with installation grooves communicated with each other, the bottom end in each installation groove is fixedly provided with an electromagnet (23), each electromagnet (23) is fixedly connected with a spring (24), each spring (24) is fixedly connected with an iron plate (25), each iron plate (25) is fixedly connected with the exhaust plate (6), the inner surfaces of the side cover (16) and the reflection shell (19) are fixedly adhered with a micro-foaming reflection plate (20), the top of frame main part (1) fixed connection radar antenna (10), fixed connection weather shield (13) on second flank (3) of gas vent (14) one side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910765327.0A CN110466781B (en) | 2019-08-19 | 2019-08-19 | Flying wing type solar auxiliary power supply unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910765327.0A CN110466781B (en) | 2019-08-19 | 2019-08-19 | Flying wing type solar auxiliary power supply unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110466781A CN110466781A (en) | 2019-11-19 |
| CN110466781B true CN110466781B (en) | 2021-04-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910765327.0A Active CN110466781B (en) | 2019-08-19 | 2019-08-19 | Flying wing type solar auxiliary power supply unmanned aerial vehicle |
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| CN (1) | CN110466781B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113335499A (en) * | 2021-06-01 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | High-mobility unmanned aerial vehicle based on fixed fire alarm auxiliary power |
Citations (6)
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|---|---|---|---|---|
| CN103803089A (en) * | 2012-11-15 | 2014-05-21 | 西安韦德沃德航空科技有限公司 | Unmanned aerial vehicle with solar system arranged at lower portion of unmanned aerial vehicle body |
| CN203708186U (en) * | 2013-12-16 | 2014-07-09 | 李会欣 | Refractive and reflective system for photovoltaic module |
| CN205150263U (en) * | 2015-11-23 | 2016-04-13 | 盐城工学院 | Laser photovoltaic driving system |
| CN205801499U (en) * | 2016-05-31 | 2016-12-14 | 南昌理工学院 | Flying wing type solar powered aircraft |
| CN207117562U (en) * | 2017-09-04 | 2018-03-16 | 乐山市嘉蓝图科技有限公司 | Solar panel group |
| CN208715491U (en) * | 2018-05-09 | 2019-04-09 | 华南理工大学 | A kind of unmanned plane being loaded with the continuation of the journey of microprism surface solar battery |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016138173A1 (en) * | 2015-02-24 | 2016-09-01 | Karem Aircraft, Inc. | Methods for providing a durable solar powered aircraft with a variable geometry wing |
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2019
- 2019-08-19 CN CN201910765327.0A patent/CN110466781B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803089A (en) * | 2012-11-15 | 2014-05-21 | 西安韦德沃德航空科技有限公司 | Unmanned aerial vehicle with solar system arranged at lower portion of unmanned aerial vehicle body |
| CN203708186U (en) * | 2013-12-16 | 2014-07-09 | 李会欣 | Refractive and reflective system for photovoltaic module |
| CN205150263U (en) * | 2015-11-23 | 2016-04-13 | 盐城工学院 | Laser photovoltaic driving system |
| CN205801499U (en) * | 2016-05-31 | 2016-12-14 | 南昌理工学院 | Flying wing type solar powered aircraft |
| CN207117562U (en) * | 2017-09-04 | 2018-03-16 | 乐山市嘉蓝图科技有限公司 | Solar panel group |
| CN208715491U (en) * | 2018-05-09 | 2019-04-09 | 华南理工大学 | A kind of unmanned plane being loaded with the continuation of the journey of microprism surface solar battery |
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| CN110466781A (en) | 2019-11-19 |
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