CN112141329A - Vertical take-off and landing solar unmanned aerial vehicle - Google Patents
Vertical take-off and landing solar unmanned aerial vehicle Download PDFInfo
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- CN112141329A CN112141329A CN201910571322.4A CN201910571322A CN112141329A CN 112141329 A CN112141329 A CN 112141329A CN 201910571322 A CN201910571322 A CN 201910571322A CN 112141329 A CN112141329 A CN 112141329A
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- 238000005336 cracking Methods 0.000 claims abstract description 15
- 239000000463 material Substances 0.000 claims description 14
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- 229910052799 carbon Inorganic materials 0.000 claims description 9
- 229910000838 Al alloy Inorganic materials 0.000 claims description 8
- 239000000956 alloy Substances 0.000 claims description 8
- 239000002131 composite material Substances 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 239000004917 carbon fiber Substances 0.000 claims description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 240000007182 Ochroma pyramidale Species 0.000 claims description 4
- 239000002023 wood Substances 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 3
- 230000002035 prolonged effect Effects 0.000 abstract description 5
- 230000002349 favourable effect Effects 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000012827 research and development Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000005538 encapsulation Methods 0.000 description 2
- 239000011152 fibreglass Substances 0.000 description 2
- 238000005286 illumination Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- 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
-
- 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
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention provides a vertical take-off and landing solar unmanned aerial vehicle, which comprises: the aircraft comprises an airframe, a frame, a wing group, a fixed wing and a rotor wing group; the wing group comprises a front wing and a rear wing, the front wing and the rear wing are fixed through a connecting piece, the front wing comprises a front main wing and a cracking type aileron, the rear wing comprises a rear main wing and an elevator, and the front wing is fixed on the fuselage; the rotor wing group comprises more than or equal to 4 rotor wing propeller groups, and the rotor wing propeller groups are arranged on the rack; the fuselage comprises a nose, a nacelle and a rudder. The invention adopts a cracking type aileron structure, and no gap exists on the surface of the wing, thereby not only meeting the excellent pneumatic performance of the wing, but also providing favorable guarantee for laying a solar cell panel on the wing; solar energy and oil-electricity hybrid power supply is adopted, so that the cruising time can be prolonged compared with that of a traditional fixed wing unmanned aerial vehicle; adopt the control scheme of rotor for unmanned aerial vehicle possesses the function of VTOL, and based on longer cruising time, it can further expand its application scenario, provides the operating efficiency, saves the cost.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a vertical take-off and landing solar unmanned aerial vehicle.
Background
At the present stage, the fixed-wing unmanned aerial vehicle is limited in wide application in the market due to the short endurance time. In order to improve the cruising time of the fixed-wing unmanned aerial vehicle, a solar panel is used as auxiliary power, so that a new solution is provided. For an industrial-grade fixed wing unmanned aerial vehicle, how to design the whole aerodynamic performance to be excellent, the unmanned aerial vehicle has the advantages of light overall structure weight, long cruising time and the like, and the unmanned aerial vehicle becomes a problem to be solved urgently in the industry of the unmanned aerial vehicle.
In order to improve the endurance time of the existing fixed-wing unmanned aerial vehicle, on one hand, a lighter-weight aircraft is designed, the aerodynamic appearance of the unmanned aerial vehicle is continuously optimized, and the flight resistance is further reduced; on the other hand, adopt oil-electricity hybrid scheme, promote unmanned aerial vehicle's flight time. However, the first design scheme is adopted, so that the effective load of the unmanned aerial vehicle is reduced, and the development of the unmanned aerial vehicle in various application scenes is limited; to oil electric power design scheme, both obviously increased unmanned aerial vehicle's weight, also brought the input of cost, simultaneously relatively pure electric aircraft has also brought the flight potential safety hazard. Therefore, how to design a fixed-wing aircraft is a key problem to be solved by the invention, and on the premise of ensuring the effective load, the fixed-wing aircraft is light and can realize long-time cruising.
Disclosure of Invention
For conventional fixed wing drones, in order to increase the cruising time, compromises must be made in profile layout and cost expenditure. Besides, because the fixed-wing unmanned aerial vehicle adopts a running takeoff mode, the fixed-wing unmanned aerial vehicle is limited in the expansion of a plurality of application scenes, such as fields of aerial survey, border patrol, forest fire prevention and the like. In order to ensure that the cruising time of the fixed-wing unmanned aerial vehicle can be prolonged on the premise that the cost is acceptable, and the fixed-wing unmanned aerial vehicle can adapt to various application scenes to achieve the purpose of one machine with multiple purposes, the invention provides the vertical take-off and landing solar unmanned aerial vehicle.
The specific technical scheme is as follows:
a vertical take-off and landing solar drone, comprising: the aircraft comprises an airframe, a frame, a wing group, a fixed wing and a rotor wing group; the wing group comprises a front wing and a rear wing, the front wing and the rear wing are fixed through a connecting piece, the front wing comprises a front main wing and a cracking type aileron, the rear wing comprises a rear main wing and a lifting rudder, and the front wing is fixed on the fuselage; the rotor wing group comprises more than or equal to 4 rotor wing propeller groups, and the rotor wing propeller groups are arranged on the rack; the fuselage includes a nose, a nacelle, and a rudder.
Preferably, the rear end of the rear wing abuts against the rudder, and the front end abuts against the front wing through a connecting piece.
Preferably, the front wing and the rear wing are covered with a solar panel on the surface.
Preferably, the fixed wing comprises a fixed wing propeller group mounted on the nose.
Preferably, the nacelle comprises an aircraft control system and an energy supply device comprising a fuel tank and a battery pack.
Preferably, the split aileron is located below the front main wing, and the deflection angle range is 0-45 degrees, and the flapped aileron is unidirectional linear deflection.
Preferably, the front wing is fixed on the machine body through a carbon rod, and the fixing mode comprises bolt connection.
Preferably, the material of the fuselage, the frame, the front main wing and the rear main wing comprises one or more of an aircraft layer wood, a composite material, a carbon fiber material and an aluminum alloy material.
Preferably, the material of the split flap comprises one or more of balsa wood, a composite material, a carbon fibre material and an aluminium alloy material.
Preferably, the prop-rotor unit is secured by one or more of screw, pin and snap fastening.
Compared with the prior art, the vertical take-off and landing solar unmanned aerial vehicle has the following advantages:
the vertical take-off and landing solar unmanned aerial vehicle adopts a cracking type aileron structure, no gap exists on the surface of the wing, excellent aerodynamic performance of the wing is met, and favorable guarantee is provided for laying a solar cell panel on the wing; solar energy and oil-electricity hybrid power supply is adopted, so that the cruising time can be prolonged compared with that of a traditional fixed wing unmanned aerial vehicle; adopt the control scheme of rotor for unmanned aerial vehicle possesses the function of VTOL, and based on longer cruising time, it can further expand its application scenario, provides the operating efficiency, saves the cost.
Drawings
Fig. 1 is a schematic diagram of a vertical take-off and landing solar unmanned aerial vehicle according to the present invention;
fig. 2 is a schematic diagram of a vertical take-off and landing solar unmanned aerial vehicle covering a solar panel according to the present invention;
fig. 3 is a front view of a vertical take-off and landing solar unmanned aerial vehicle provided by the invention.
Description of reference numerals:
1 fuselage 2 frame 3 fixed wing propeller group 4 front wing 5 rear wing
6 gyroplane group 7 aircraft nose 8 cabin 9 rudder 10 elevator
11 formula aileron 12 carbon rods 13 solar cell panel 14 connecting piece of ftractureing
Detailed Description
The technical means of the present invention will be described in further detail with reference to specific embodiments. It should be understood that the detailed description and specific examples, while indicating the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the device or element being referred to must have a particular direction, be constructed in a particular 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 meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is a schematic diagram of a vertical take-off and landing solar unmanned aerial vehicle provided by the invention, which includes: the aircraft comprises an airframe 1, a frame 2, a wing group, a fixed wing and a rotor wing group; the wing group comprises a front wing 4 and a rear wing 5, the surfaces of the front wing 4 and the rear wing 5 are covered with a solar panel 13, as shown in fig. 2, the front wing 4 and the rear wing 5 are fixed through a connecting piece 14, and a bolt and screw connection mode is adopted at a specific connection interface. As shown in fig. 3, the rear wing 5 is higher than the front wing 4 in vertical height, the connecting piece 14 is perpendicular to the plane of the rear wing 5 and the plane of the front wing 4, and an integral structure is formed by the connection of the connecting pieces 14, so that the integration of the wing is realized. This has the advantage that: on one hand, the structural strength of the whole wing is enhanced; on the other hand, the area of the wing is increased due to the design of the whole wing, so that the efficiency of laying the solar cell panel 13 on the wing is improved. The front wing 4 comprises a front main wing and a cracking type aileron 11, the cracking type aileron 11 is located below the front main wing, the deflection angle range is 0-45 degrees, the flawing is unidirectional linear deflection, the deflection of the cracking type aileron 11 is driven by a driving device to realize the deflection, and the cracking type aileron 11 is located below the front main wing, and is integrated with the front main wing when the deflection angle is 0 degrees, so that the requirement on the thickness is low, and the thickness is only 1-3 mm, preferably 2 mm. Meanwhile, the structure does not influence the overall aerodynamic performance of the front main wing. The rear wing 5 comprises a rear main wing and an elevator 10, and the front wing 4 is fixed on the machine body 1 through a carbon rod 12 in a bolt connection mode; the rotor set includes greater than or equal to 4 prop-rotor sets 6, preferably 4 prop-rotor sets 6. The rotor propeller group 6 is arranged on the frame 2, and the fixing mode comprises one or more of screw fixation, pin fixation and buckle fixation; the aircraft body 1 comprises an aircraft nose 7, an engine room 8 and a rudder 9, and the fixed wing comprises a fixed wing propeller group 3 and is arranged on the aircraft nose 7; the cabin 8 comprises an aircraft control system and an energy supply device, the energy supply device comprises an oil tank and a battery pack, the solar cell panel 13 is connected with the energy supply device, energy sharing is achieved, the battery pack can be charged by the solar cell panel 13, and the purpose of prolonging the endurance time is achieved. The rear end of the rear wing 5 is abutted to the rudder 9, the specific connection mode comprises bolt connection and the like, and the front end is abutted to the front wing 4 through a connecting piece 14, so that wing integration is realized. The rear wing 5 is connected to the rudder 9 by a carbon rod 12.
The material of fuselage 1, frame 2, preceding main wing and back main wing includes one or more in aviation layer wood, combined material, carbon-fibre material and the aluminium alloy material.
The material of the cracking type aileron 11 comprises one or more of balsa wood, composite material, carbon fiber material and aluminum alloy material.
The prop-rotor unit 6 is fixed to the frame 2 by one or more of screw fixation, pin fixation, and snap fixation.
In the present invention, the prop-rotor set 6 and the fixed-wing propeller set 3 include propellers, motors, etc., the motors being connected to energy supply means, which are well known to those skilled in the art and therefore not described in detail.
The solar panel 13 may be fixed to the front wing 4 and the rear wing 5 by means of bonding, glass fiber reinforced plastic encapsulation, welding, or the like.
The invention is a scheme which is low in cost and easy to realize in engineering application by using a novel fixed wing unmanned aerial vehicle structure, taking a cracking type aileron 11 as a basis, taking solar energy as auxiliary power (a specific form is a solar cell panel 13), and using four rotor propeller groups 6 to replace the traditional landing gear running design.
The invention aims to provide a novel appearance layout form of a fixed wing unmanned aerial vehicle, which is used for greatly improving the cruising time of the fixed wing unmanned aerial vehicle and solving the defects of short cruising time, running takeoff, heavy oil-electricity power structure and the like of the conventional fixed wing unmanned aerial vehicle. Meanwhile, in order to increase the laying area of the solar cell panels 13 on the upper surface of the front wing 4, the invention adopts the split type ailerons 11 to replace the traditional aileron design form, so that the aerodynamic appearance of the wing surface is not damaged on the basis of increasing the laying number of the solar cell panels to 6-8%. In addition, the front wing 4 and the rear wing 5 form a closed integral structure through a connecting piece 14 in a connecting mode of screws, buckles, magnets and the like, and the structural strength of the integral structure is obviously enhanced. The more outstanding characteristics are, this kind of design, it is with solar energy as auxiliary power, has prolonged unmanned aerial vehicle's time of endurance greatly.
The invention relates to a vertical take-off and landing solar unmanned aerial vehicle with a new configuration, which has the working principle that: firstly, the flight control of the airplane adopts a layout form that a cracking type aileron 11 replaces a traditional aileron and is used for controlling the rolling motion of the airplane in flight; the pitching motion of the airplane is controlled by adopting an elevator 10, and the heading motion of the airplane is controlled by adopting a rudder 9. Secondly, the design scheme of the cracking type aileron 11 is adopted, so that the upper surface of the front wing 4 is smooth, and the solar cell panel can be conveniently laid to a greater extent. Based on the hybrid power scheme of the solar cell panel 13 and the energy supply device, when the illumination intensity reaches 15 ten thousand LUX, the power supply of the solar energy meets the power consumption of the whole machine, and when the illumination intensity is larger than the critical value, redundant electric quantity is supplied to the battery for charging through the energy supply device. Thirdly, the vertical take-off and landing solar aircraft is designed to be a five-rotor wing, the four-rotor-wing propeller group 6 is fixed through the rack 2 and is used for providing operations of vertical take-off and landing, hovering and the like, and the fixed-wing propeller group 3 on the aircraft nose 7 is used for providing power for the advancing of the whole aircraft. For a low-altitude solar unmanned aerial vehicle (less than 500m), the layout design form can be used for conveniently realizing engineering application on the basis of saving cost to the greatest extent.
The structural layout of the vertical take-off and landing solar unmanned aerial vehicle with the new layout is explained in detail. According to the vertical take-off and landing solar unmanned aerial vehicle structure, the front wing 4 is connected with the vehicle body 1 through the carbon rod 12, and the position of the front wing 4 is fixed through the bolt and the screw; the rear wing 5 is connected with the fuselage 1 through a carbon rod 12, and the position of the rear wing 5 is fixed by bolts and screws. The front wing 4 and the rear wing 5 are fixed by bolts and screws to form an integral structure. On one hand, the structural strength of the whole wing is enhanced; on the other hand, the area of the wing is increased due to the design of the whole wing, so that the efficiency of laying the solar cell panel on the wing is improved. And the design scheme of the split aileron 11 is adopted, so that the upper surface of the front wing 4 does not generate an assembly gap, not only is an excellent aerodynamic appearance obtained, but also the number of the solar panels 13 paved on the front wing 4 is further increased. It is outer, to this design, adopt the hybrid scheme of fixed wing screw group 3 and rotor screw group 6, can realize this unmanned aerial vehicle VTOL, reduced unmanned aerial vehicle to the demand in flight place, more do benefit to the application in trade market. Most importantly, a cabin cover is designed on the unmanned aerial vehicle body 1 and used for loading 18650 batteries, meanwhile, the power supply is combined with solar energy for supplying power, and the unmanned aerial vehicle can achieve longer cruising time through optimization of an energy supply device.
The main reasons for innovating the vertical take-off and landing solar unmanned aerial vehicle with the new configuration are as follows: firstly, research and development and engineering application of the conventional solar unmanned aerial vehicle mainly focus on research during high-altitude long-endurance, and for low-altitude application scenes, the research and development of vertical take-off and landing solar energy are limited by cost and technical consideration, so that the development of the vertical take-off and landing solar energy is still immature, and the vertical take-off and landing solar energy becomes a new research and development direction of the unmanned aerial vehicle in order to further promote the endurance of the fixed-wing unmanned aerial vehicle; secondly, a split type aileron structure is adopted, no gap exists on the surface of the wing, the excellent aerodynamic performance of the wing is met, and the favorable guarantee is provided for laying a solar cell panel on the wing; thirdly, solar energy and a battery are adopted for hybrid power supply, and compared with the traditional fixed wing unmanned aerial vehicle, the cruise time can be averagely increased by 40% -60%; fourthly, a control scheme of the rotor wing is adopted, so that the unmanned aerial vehicle has a vertical take-off and landing function, the application scene can be further expanded based on longer cruising time, the operation efficiency is improved, and the cost is saved;
the airframe 1, the frame 2, the front main wing and the rear main wing are made of aviation laminated wood, composite materials, carbon fiber materials, aluminum alloy materials and the like;
the cracking type aileron 11 is made of balsa wood, a composite material, a carbon fiber material, an aluminum alloy material and the like;
the front main wing and the split type aileron 11 can be connected by a connecting rod, a bearing, a screw and the like;
the fixing mode of the rotor propeller group 6 can be realized by screw fixation, pin fixation, bayonet fixation and the like;
the solar panel 13 may be fixed by means of adhesion, glass fiber reinforced plastic encapsulation, welding, or the like.
In conclusion, the vertical take-off and landing solar unmanned aerial vehicle provided by the invention adopts a cracking type aileron structure, no gap exists on the surface of the wing, not only is the excellent aerodynamic performance of the wing satisfied, but also the favorable guarantee is provided for laying a solar cell panel on the wing; solar energy and oil-electricity hybrid power supply is adopted, so that the cruising time can be prolonged compared with that of a traditional fixed wing unmanned aerial vehicle; adopt the control scheme of rotor for unmanned aerial vehicle possesses the function of VTOL, and based on longer cruising time, it can further expand its application scenario, provides the operating efficiency, saves the cost.
The above embodiments are all preferred embodiments of the present invention, and therefore do not limit the scope of the present invention. Any equivalent structural and equivalent procedural changes made to the present disclosure without departing from the spirit and scope of the present disclosure are within the scope of the present disclosure as claimed.
Claims (10)
1. The utility model provides a VTOL solar energy unmanned aerial vehicle which characterized in that includes: the aircraft comprises an airframe (1), a frame (2), a wing group, a fixed wing and a rotor wing group;
the aircraft wing set comprises a front wing (4) and a rear wing (5), the front wing (4) and the rear wing (5) are fixed through a connecting piece, the front wing (4) comprises a front main wing and a cracking type aileron (11), the rear wing (5) comprises a rear main wing and an elevator (10), and the front wing (4) is fixed on an aircraft body (1);
the rotor wing group comprises more than or equal to 4 rotor wing propeller groups (6), and the rotor wing propeller groups (6) are arranged on the frame (2);
the aircraft body (1) comprises an aircraft nose (7), an engine room (8) and a rudder (9).
2. Vertical take-off and landing solar drone according to claim 1, characterized in that the rear wing (5) has its rear end in abutment with the rudder (9) and its front end in abutment with the front wing (4) through a connection (14).
3. Vertical take-off and landing solar drone according to claim 1, characterised in that the front wing (4) and the rear wing (5) are surface-covered with solar panels (13).
4. A vtol solar drone according to claim 1, characterised in that the fixed wings comprise fixed-wing propellers (3), mounted on a head (7).
5. Vertical take-off and landing solar drone according to claim 1, characterized in that said nacelle (8) comprises an aircraft control system and energy supply means comprising an oil tank and a battery.
6. The VTOL solar UAV according to claim 1, wherein the split aileron (11) is located under the front main wing with a deflection angle in the range of 0-45 ° and unidirectional linear deflection.
7. The VTOL solar UAV according to claim 1, wherein the front wing (4) is fixed on the fuselage (1) by a carbon rod (12) in a manner including bolting.
8. The VTOL solar UAV of claim 1, wherein the materials of the fuselage (1), the frame (2), the front main wing and the rear main wing comprise one or more of aerospace laminated wood, composite materials, carbon fiber materials and aluminum alloy materials.
9. A vtol solar drone according to claim 1, characterised in that the material of the split aileron (11) comprises one or more of balsa, composite, carbon fibre and aluminium alloy materials.
10. A vtol solar drone according to claim 1, characterised in that the fixing means of the prop-rotor group (6) comprise one or more of screw, pin and snap fixing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910571322.4A CN112141329A (en) | 2019-06-28 | 2019-06-28 | Vertical take-off and landing solar unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910571322.4A CN112141329A (en) | 2019-06-28 | 2019-06-28 | Vertical take-off and landing solar unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN112141329A true CN112141329A (en) | 2020-12-29 |
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|---|---|---|---|
| CN201910571322.4A Pending CN112141329A (en) | 2019-06-28 | 2019-06-28 | Vertical take-off and landing solar unmanned aerial vehicle |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937834A (en) * | 2021-04-14 | 2021-06-11 | 北京航空航天大学 | Adopt small-size unmanned aerial vehicle of ally oneself with pneumatic overall arrangement of wing formula |
| CN113665785A (en) * | 2021-08-11 | 2021-11-19 | 西安羚控电子科技有限公司 | Hang up fixed wing unmanned aerial vehicle |
| CN114180049A (en) * | 2021-10-22 | 2022-03-15 | 上海新云彩航空科技有限责任公司 | Box-shaped composite wing aircraft |
-
2019
- 2019-06-28 CN CN201910571322.4A patent/CN112141329A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937834A (en) * | 2021-04-14 | 2021-06-11 | 北京航空航天大学 | Adopt small-size unmanned aerial vehicle of ally oneself with pneumatic overall arrangement of wing formula |
| CN112937834B (en) * | 2021-04-14 | 2022-06-28 | 北京航空航天大学 | Adopt small-size unmanned aerial vehicle of antithetical couplet wing formula aerodynamic configuration |
| CN113665785A (en) * | 2021-08-11 | 2021-11-19 | 西安羚控电子科技有限公司 | Hang up fixed wing unmanned aerial vehicle |
| CN114180049A (en) * | 2021-10-22 | 2022-03-15 | 上海新云彩航空科技有限责任公司 | Box-shaped composite wing aircraft |
| CN114180049B (en) * | 2021-10-22 | 2024-02-02 | 上海新云彩航空科技有限责任公司 | Box type composite wing aircraft |
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