CN207389530U - solar energy unmanned plane - Google Patents
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- CN207389530U CN207389530U CN201720376397.3U CN201720376397U CN207389530U CN 207389530 U CN207389530 U CN 207389530U CN 201720376397 U CN201720376397 U CN 201720376397U CN 207389530 U CN207389530 U CN 207389530U
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- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
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Abstract
The utility model provides a kind of solar energy unmanned plane.Solar energy unmanned plane includes：Fuselage；By the outwardly directed multiple wings of fuselage, and the angle of two neighboring wing is adjusted；Adjusting mechanism, adjusting mechanism and wing connect to adjust the included angle A between two neighboring wing.The utility model solves the problems, such as that the wing angle of solar energy unmanned plane in the prior art is unadjustable.
Description
Technical field
The utility model is related to flight equipment technical field, in particular to a kind of solar energy unmanned plane.
Background technology
At present, in the world there are no practical solar energy unmanned plane, during the relevant scientific research in various countries persistently carries out.
Foremost solar energy unmanned plane is the Environmental Studies and sensor technology that Aero Vironment companies are NASA
Plan " Apollo number " the solar energy unmanned plane developed.Equipped with 14 propellers on the fuselage of " Apollo " number, power resources in
Solar panel on wing.When sunlight is not very strong in the morning, the solar cell of " Apollo " equipment can be winged
Machine provides 10 kilowatts of electric energy, and aircraft is enable to climb with 33 meters per second of speed.Noon, the electric energy that battery provides reach
40 kilowatts, the power performance of aircraft reaches optimum state, can be flown with 30 to 50 kilometers per hour of cruising speed.At night, fly
Machine then carries out cruising flight by the electric energy of storage.
" west wind " (Zephyr) number solar energy unmanned plane of British scientist development uses GPS navigation, maximum
Flying height can reach 40000 meters.Wing is made of carbon fibre, and 12.2 meters wide, surface is covered with Pork-pieces solar energy
On the one hand solar panel, the solar energy being collected into drive propeller, are on the one hand stored into 40 section lithium batteries, used for night.
Near space solar energy unmanned plane is usually in the high-altitude flight apart from ground 20km~100km.This is highly in
Between the highest flying height of aircraft and the minimum orbit altitude of satellite.The research of near space solar energy unmanned plane has become generation
The emerging field that boundary's aerospace industry is given priority to.Near space does not have the absorption and reflection of cloud layer and air, solar radiant energy
Metric density is bigger than ground, theoretically flies that obtain more high then daylighting collection energy benefit better.Come accordingly, with respect to conventional solar energy unmanned plane
It says, solar energy unmanned plane has a clear superiority in terms of endurance with flying height.This advantage cause solar energy unmanned plane it is possible that with
It substitutes the partial function of low-orbit satellite, promotes the well-being of mankind.
Compared with satellite, since the operation height of near space solar energy unmanned plane is low, typically just low orbit satellite is very
One of to 1/20th, high-resolution earth observation easy to implement can effectively make up moonscope part blind spot.To scouting,
Scope requirement is low, using general digital camera, it is possible to acquisition and the comparable photo of high-precision satellite quality, and manufacture
It is at low cost, the launch facility of complex and expensive is not required, to ground-support equipment requirement also than relatively low, most of component and effectively load
The recyclable reuse of lotus, therefore efficiency ratio is high, emission process is relatively simple.In addition, payload technical difficulty is small, it is easy to more
New and maintenance.
But the technology of solar energy unmanned plane is newer at present, there are still many shortcomings, such as solar energy unmanned plane
The problem of wing angle can not be adjusted just needs to solve.
Utility model content
The main purpose of the utility model is that provide a kind of solar energy unmanned plane, with solve in the prior art solar energy without
The problem of man-machine wing angle is unadjustable.
To achieve these goals, the utility model provides a kind of solar energy unmanned plane, including：Fuselage；From fuselage to
The multiple wings overhang, and the angle of two neighboring wing is adjusted；Adjusting mechanism, adjusting mechanism are connected to adjust with wing
Included angle A between two neighboring wing.
Further, adjusting mechanism includes the drive rod being arranged in fuselage, and the first end of drive rod is connected with fuselage, drives
The second end of lever is connected the position for changing wing with the swing by drive rod with wing.
Further, adjusting mechanism includes the drive rod being arranged in fuselage, and the first end of drive rod is connected with fuselage, drives
The second end of lever is connected to change the position of wing by the stretching motion of drive rod with wing.
Further, drive rod is multiple that multiple drive rods connect one to one with multiple wings.
Further, adjusting mechanism further includes the first connecting rod and second connecting rod being arranged in fuselage, and the second of drive rod
End is connected by first connecting rod with first wing, and the second end of drive rod is connected by second connecting rod with second wing.
Further, guide rail is provided on fuselage, adjusting mechanism includes the rack and pinion to cooperate, and rack is arranged on
On guide rail, gear is arranged on wing, and when gear rotates, wing is moved along guide rail.
Further, in pairs, and two wings in same group are on same straight line wing, and in same group
Two wings stretch out in the opposite direction.
Further, wing is four, and four wings are arranged in X-shaped, and two wings on diagonal are one group,
It is fixedly connected with two wings in group.
Further, the included angle A between two neighboring wing is more than or equal to 10 degree and less than or equal to 120 degree.
Further, solar energy unmanned plane further includes：Main screw, before main screw is pivotably mounted on fuselage
End；Auxiliary propeller, auxiliary propeller are arranged on the external part of wing.
Further, it is provided with solar battery sheet on the surface of wing.
Further, solar battery sheet is both provided on the surface that wing is oppositely arranged.
Further, solar energy unmanned plane further includes：For gathering the illuminance sensor of intensity of illumination, illuminance sensing
Device is arranged on wing；Controller, controller are arranged in fuselage, and illuminance sensor drives adjusting mechanism by controller
Action.
Further, it is provided with load cabin in fuselage.
Using the technical solution of the utility model, wing is arranged on fuselage, and adjusting mechanism is connected to adjust phase with wing
Included angle A between adjacent two wings.In this way, the solar energy unmanned plane can be according to specific operating condition, by adjusting machine
Angle between the wing makes solar energy unmanned plane better adapt to current running environment, to improve operation stability and reliability,
Ensure good aerodynamic characteristic.
Description of the drawings
The accompanying drawings which form a part of this application are used to provide a further understanding of the present invention, this practicality
New schematic description and description does not form the improper restriction to the utility model for explaining the utility model.
In the accompanying drawings：
Fig. 1 shows the structure diagram of solar energy unmanned plane in the alternative embodiment of the utility model；
Fig. 2 shows the top view of Fig. 1；
Fig. 3 shows the right view of Fig. 1.
Wherein, above-mentioned attached drawing is marked including the following drawings：
10th, fuselage；20th, wing；40th, main screw；50th, auxiliary propeller.
Specific embodiment
It should be noted that in the case where there is no conflict, the feature in embodiment and embodiment in the application can phase
Mutually combination.The utility model will be described in detail below with reference to the accompanying drawings and embodiments.
It is pointed out that unless otherwise specified, all technical and scientific terms used in this application have and the application
The normally understood identical meanings of person of an ordinary skill in the technical field.
In the utility model in the case where not making explanation on the contrary, the noun of locality such as " upper and lower, top, bottom " used is usually
Be for direction shown in the drawings or for component in itself on vertical, vertical or gravity direction for；Together
Sample, it for ease of understanding and describes, " inside and outside " refers to the inside and outside of the profile compared with each component in itself, but the above-mentioned noun of locality is simultaneously
It is not used in limitation the utility model.
In order to solve the problems, such as that the wing angle of solar energy unmanned plane in the prior art is unadjustable, the utility model provides
A kind of solar energy unmanned plane.
Embodiment one
As shown in Figure 1 to Figure 3, solar energy unmanned plane includes fuselage 10, adjusting mechanism and outwardly directed more by fuselage 10
A wing 20, the angle of two neighboring wing 20 are adjusted, and adjusting mechanism is connected to adjust two neighboring wing 20 with wing 20
Between included angle A.
In this way, the solar energy unmanned plane can according to specific operating condition, by adjusting the angle between wing 20,
Solar energy unmanned plane is made to better adapt to current running environment, to improve operation stability and reliability, ensures good gas
Dynamic characteristic.
Load cabin is provided in fuselage 10 in the utility model.In this way, the space availability ratio in fuselage 10 is effectively improved,
And ensure the cleaning outside fuselage 10, increase frontal resistance is avoided, improves the operational reliability of solar energy unmanned plane.
The utility model provides power source by solar energy for solar energy unmanned plane.The sun is provided on the surface of wing 20
It can cell piece.In such manner, it is possible to ensure that solar energy unmanned plane is chronically at operating status and energy supply is uninterrupted.
In order to ensure that solar energy unmanned plane can also navigate by water at night, solar energy unmanned plane further includes accumulator, electric power storage
Pond is connected with solar battery sheet, for storing electric energy, in case being energized at night.
Optionally, solar battery sheet is both provided on the surface that wing 20 is oppositely arranged.In this way, solar energy large area
The surface of wing 20 is covered, the efficiency of energy collection of solar energy unmanned plane can be effectively improved, improves the utilization of solar energy, is ensured
The energy source and power of solar energy unmanned plane.
In this embodiment, solar energy unmanned plane further includes controller and for gathering the illuminance of intensity of illumination sensing
Device, illuminance sensor are arranged on wing 20, and controller is arranged in fuselage 10, and illuminance sensor is driven by controller
Dynamic adjusting mechanism action.First, default illumination intensity value is provided in controller, during solar energy unmanned plane is run,
Real-time lighting intensity value is gathered by illuminance sensor, and real-time lighting intensity value and default illumination intensity value are compared
Compared with when real-time lighting intensity value is more than default intensity of illumination, adjusting mechanism is failure to actuate；It is preset when real-time lighting intensity value is less than
During intensity of illumination, adjusting mechanism acts so that the angle between two neighboring wing 20 changes, until real-time lighting intensity value is big
When default illumination intensity value, stop the action of adjusting mechanism.
In view of the performance of solar cell silicon wafer, change as far as possible gentle aerofoil profile using airfoil curvature.Meanwhile the sun
The groundwork region of energy unmanned plane is near space, and the low-density low reynolds number characteristic in the space determines that aerofoil profile should meet
The low-resistance promotion performance of low reynolds number.
Optionally, the section configuration of wing 20 can select aerofoil profile AH79-100A, aerofoil profile SA7038, aerofoil profile WB-135-35
With aerofoil profile NACA4409 as embodiment, this four sections of aerofoil profiles lifting resistance characteristic under low reynolds number is relatively good.
It should be noted that fuselage 10 should be as small as possible on the basis of equipment installation is ensured.
In this embodiment, fuselage 10 is rotary structure, and the body shell that fuselage 10 is arranged successively by multilayer is formed,
Wing 20 is arranged on body shell.Wherein, two neighboring wing 20 is not arranged on same body shell.Once adjacent two
A wing 20 is fixedly connected with same body shell, and the angle between the two wings 20 can not just change.
In said structure, when needing to change the angle between two neighboring wing 20, by the movement of adjusting mechanism,
Make to have the body shell of different wings 20 to relatively rotate, so as to fulfill the angulation change between adjacent wing 20.
As shown in Figure 1, wing 20 is in pairs, and two in same group wing 20 is on same straight line, and same
Two wings 20 in group stretch out in the opposite direction.Specifically, wing 20 is four, and four wings 20 are arranged in X-shaped, and
Two wings 20 on diagonal are one group, are fixedly connected with two wings 20 in group.
Shown in please referring to Fig.1, four wings 20 include first wing 20 diagonally set and the 3rd wing 20, diagonal
Set second wing 20 and the 4th wing 20, wherein, first wing 20 and the 3rd wing 20 it is relatively motionless, second
A wing 20 and the 4th wing 20 are relatively motionless.Wherein, first wing 20 is located at the upper left corner in Fig. 1, second wing
20 are located at the upper right corner of Fig. 1.
Since the transfer efficiency of solar cell silicon wafer (being exactly above-mentioned solar battery sheet) is relatively low, it is necessary to using super
Big wing area is to meet electricity needs.But to ensure enough lifting resistance characteristics, the increase of wing area is typically to pass through
Increase the aspect ratio of wing to realize.And super large aspect ratio often results in its flexibility and very big shadow is caused to aeroelasticity greatly very much
It rings.Meanwhile the structure design of big flexible wing also has very big difficulty.In order to reduce the large deformation of wing and aeroelasticity
Can, by aerodynamic arrangement's form design of solar energy unmanned plane into X-shaped.
It please refers to Fig.1, when the 20 times deflection of first wing 20 and second wing, the 3rd wing 20 and the 4th machine
When the wing 20 upward deflects, included angle A reduces；When first wing 20 and second wing 20 upward deflect, the 3rd 20 He of wing
When 4th wing 20 deflects down, included angle A increase.
In this embodiment, adjusting mechanism includes the drive rod being arranged in fuselage 10, the first end and fuselage of drive rod
10 connections, the second end of drive rod are connected the position for changing wing 20 with the swing by drive rod with wing 20.Due to the reality
Applying in example has two groups of wings 20, therefore drive rod also should be two, and two drive rods connect respectively from a wing 20 in different groups
It connects, by the swing of drive rod, realizes the adjusting of included angle A.
Optionally, included angle A is more than or equal to 10 degree and less than or equal to 120 degree.
It should be noted that being limited by wing thickness and adjusting mechanism installation, included angle A can not accomplish 0 °.And wing
20 in it is fully horizontal when, the lateral stability of solar energy unmanned plane can very poor, therefore, limitation minimum 10 ° of included angle A.Work as machine
When the wing 20 is substantially vertical, wing 20 cannot provide lift, and therefore, limitation included angle A is 120 ° maximum.
Certainly, the scope of included angle A is determined by the aerodynamic lift of solar energy unmanned plane.It, can be with when in close to space vehicle
Included angle A is adjusted according to flight progress.When sunlight is more sufficient, solar energy unmanned plane is adjusted according to the situation of sunlight and pressed from both sides
Angle A, to absorb solar energy as far as possible；When in dark, solar energy unmanned plane will reduce included angle A, become as far as possible
Flat sudden preservation energy is kept into level.At this moment, solar energy unmanned plane will be driven by the energy being stored in energy storage battery.
In order to improve the operation stability of solar energy unmanned plane, solar energy unmanned plane further includes main screw 40 and auxiliary spiral shell
Paddle 50 is revolved, the front end auxiliary propeller 50 that main screw 40 is pivotably mounted on fuselage 10 is arranged on the external part of wing 20.
The main screw 40 for providing flying power is mounted on the front end of fuselage 10, and the external part of wing 20 is mounted on auxiliary propeller
50.To ensure enough control efficiencies, the installation of auxiliary propeller 50 should be in allowed limits close proximity to outside, to be used for
Ensure the control stability of solar energy unmanned plane in from ground to close to space vehicle, while can be carried in close to space vehicle
For flying power.
It please refers to Fig.1, it is necessary to illustrate, by loading onto auxiliary propeller 50 in the end of wing 20 so that solar energy
During unmanned plane goes up near space from ground, when vertical gust influence is run into, by controlling X-shaped wing 20
On, the rotation of two auxiliary propellers 50 positioned at two auxiliary propellers 50 of upside or positioned at downside ensures solar energy
Unmanned plane realizes elevating movement；When laterally prominent wind is run into, need to control positioned at left side two auxiliary propellers 50 or
Positioned at the rotation of two auxiliary propellers 50 in left side, the divertical motion of guarantee solar energy unmanned plane.Aerodynamic arrangement's form
Roll damping is very big, and stability is preferable, generally need not specially manipulate.After near space, auxiliary propeller 50 and master
Propeller 40 provides the flying power of solar energy unmanned plane together.
Wherein, the principal screw motor for main screw 40 being driven to move is located in fuselage 10.
Solar energy unmanned plane in the present embodiment is a kind of near space solar energy unmanned plane, can realize that high altitude long time flies
Row, to carry out ground monitoring, the payload such as meteorological observation sensor are carried in communication.
Embodiment two
Difference lies in each wing 20 all moves independently of one another with embodiment one.
At this point, drive rod is multiple, multiple drive rods connect one to one with multiple wings 20.In this way, pass through multiple drives
The self-movement of lever, can allow multiple 20 each autokinesis of wing, can also change above-mentioned included angle A.
It is of course also possible to part wing 20 is connected with drive rod.In this way, when a wing 20 rotates, can equally change
Its angled relationships between adjacent wing 20, so as to achieve the purpose that improve the runnability of solar energy unmanned plane.
Embodiment three
Difference lies in the manner of execution of drive rod is different with embodiment one.
In this embodiment, adjusting mechanism includes the drive rod being arranged in fuselage 10, the first end and fuselage of drive rod
10 connections, the second end of drive rod are connected to change the position of wing 20 by the stretching motion of drive rod with wing 20.Pass through
The length of drive rod changes, and the position between wing 20 and fuselage 10 can be made to change, and makes wing 20 with respect to 10 turns of fuselage
It is dynamic, it can also achieve the purpose that change two neighboring 20 angled relationships of wing.
Optionally, drive rod is the structures such as telescopic cylinder or linear motor.
Example IV
Difference lies in adjusting mechanism further includes the first connecting rod being arranged in fuselage 10 and second and connects with embodiment one
Bar.
Specifically, the second end of drive rod is connected by first connecting rod with first wing 20, the second end of drive rod
It is connected by second connecting rod with second wing 20.
It please refers to Fig.1, first connection of wing 20 is located at the upper left corner in figure, and second wing 20 is located at the upper right in figure
Angle.In this way, when drive rod is swung, first connecting rod and second connecting rod can drive two wings 20 to be rotated compared with fuselage 10, from
And realize the change of included angle A.
Embodiment five
Difference lies in, drive rod it is not to swing with example IV, but stretching motion.When drive rod stretching motion
When, while the position of coupled first connecting rod and second connecting rod can be changed, so that wing 20 moves.
Embodiment six
Difference lies in the structure of adjusting mechanism is different with embodiment one.
Specifically, guide rail is provided on fuselage 10, adjusting mechanism includes the rack and pinion to cooperate, and rack is set
On guide rail, gear is arranged on wing 20, and when gear rotates, wing 20 is moved along guide rail.Pass through matching somebody with somebody for wheel and rack
It closes, can also realize the change of 20 position of wing.
Embodiment seven
Difference lies in the structure of fuselage 10 is different with embodiment one.
Specifically, it is contemplated that the problem of weight, fuselage 10 is not that the body shell being arranged successively by multilayer is formed.And
It is the body shell of a rotary structure, the resigning slot hole installed for wing 20 is reserved on the body shell.Wing 20
It is slidably arranged at resigning slot hole and is connected with the adjusting mechanism in fuselage 10.It should be noted that due to needing allowing bit length
It installs sealing structure at hole additional, so that after fuselage 10 is connected with wing 20, sealing is kept in fuselage 10.
Obviously, above-mentioned described embodiment is only the embodiment of the utility model part rather than the reality of whole
Apply example.Based on the embodiment in the utility model, those of ordinary skill in the art institute without making creative work
The every other embodiment obtained should all belong to the scope of the utility model protection.
It should be noted that term used herein above is merely to describe specific embodiment, and be not intended to restricted root
According to the illustrative embodiments of the application.As used herein, unless the context clearly indicates otherwise, otherwise singulative
It is also intended to include plural form, additionally, it should be understood that, when in the present specification using term "comprising" and/or " bag
Include " when, indicate existing characteristics, step, work, device, component and/or combination thereof.
It should be noted that term " first " in the description and claims of this application and above-mentioned attached drawing, "
Two " etc. be the object for distinguishing similar, without being used to describe specific order or precedence.It should be appreciated that it so uses
Data can exchange in the appropriate case, so that presently filed embodiment described herein can be with except illustrating herein
Or the order beyond those of description is implemented.In addition, term " comprising " and " having " and their any deformation, it is intended that
Cover it is non-exclusive include, for example, containing the process of series of steps or unit, method, system, product or equipment need not limit
In those steps or unit for clearly listing, but may include not list clearly or for these processes, method, production
The intrinsic other steps of product or equipment or unit.
The above is only the preferred embodiment of the utility model only, is not intended to limit the utility model, for this
For the technical staff in field, various modifications and changes may be made to the present invention.It is all in the spirit and principles of the utility model
Within, any modifications, equivalent replacements and improvements are made should be included within the scope of protection of this utility model.
Claims (12)
1. a kind of solar energy unmanned plane, which is characterized in that including：
Fuselage (10)；
By the outwardly directed multiple wings (20) of the fuselage (10), and the angle of the two neighboring wing (20) is adjusted；
Adjusting mechanism, the adjusting mechanism are connected to adjust the folder between the two neighboring wing (20) with the wing (20)
Angle A is provided with solar battery sheet on the surface of the wing (20)；
For gathering the illuminance sensor of intensity of illumination, the illuminance sensor is arranged on the wing (20)；
Controller, the controller is arranged in the fuselage (10), and the illuminance sensor is driven by the controller
The dynamic adjusting mechanism action.
2. unmanned plane according to claim 1, which is characterized in that the adjusting mechanism includes being arranged on the fuselage (10)
Interior drive rod, the first end of the drive rod are connected with the fuselage (10), the second end of the drive rod and the wing
(20) connect to change the position of the wing (20) by the swing of the drive rod.
3. unmanned plane according to claim 1, which is characterized in that the adjusting mechanism includes being arranged on the fuselage (10)
Interior drive rod, the first end of the drive rod are connected with the fuselage (10), the second end of the drive rod and the wing
(20) connect to change the position of the wing (20) by the stretching motion of the drive rod.
4. the solar energy unmanned plane according to Claims 2 or 3, which is characterized in that the drive rod is multiple described to be multiple
Drive rod connects one to one with multiple wings (20).
5. the solar energy unmanned plane according to Claims 2 or 3, which is characterized in that the adjusting mechanism, which further includes, to be arranged on
First connecting rod and second connecting rod in the fuselage (10), the second end of the drive rod pass through the first connecting rod and first
Wing (20) connection, the second end of the drive rod are connected by second connecting rod with second wing (20).
6. unmanned plane according to claim 1, which is characterized in that be provided with guide rail, the adjusting on the fuselage (10)
Mechanism includes the rack and pinion to cooperate, and the rack is arranged on the guide rail, and the gear is arranged on the wing
(20) on, when the gear rotates, the wing (20) is moved along the guide rail.
7. solar energy unmanned plane according to any one of claim 1 to 3, which is characterized in that the wing (20) is two-by-two
One group, and two wings (20) in same group are on same straight line, and the wing (20) of two in same group
It stretches out in the opposite direction.
8. solar energy unmanned plane according to claim 7, which is characterized in that the wing (20) is four, described in four
Wing (20) is arranged in X-shaped, and two wings (20) on diagonal are one group, with two wings in group
(20) it is fixedly connected.
9. solar energy unmanned plane according to any one of claim 1 to 3, which is characterized in that the two neighboring wing
(20) included angle A between is more than or equal to 10 degree and less than or equal to 120 degree.
10. solar energy unmanned plane according to any one of claim 1 to 3, which is characterized in that the solar energy unmanned plane
It further includes：
Main screw (40), the main screw (40) are pivotably mounted on the front end of the fuselage (10)；
Auxiliary propeller (50), the auxiliary propeller (50) are arranged on the external part of the wing (20).
11. solar energy unmanned plane according to claim 1, which is characterized in that the surface that the wing (20) is oppositely arranged
On be both provided with the solar battery sheet.
12. solar energy unmanned plane according to claim 1, which is characterized in that be provided with load cabin in the fuselage (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720376397.3U CN207389530U (en) | 2017-04-11 | 2017-04-11 | solar energy unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720376397.3U CN207389530U (en) | 2017-04-11 | 2017-04-11 | solar energy unmanned plane |
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| Publication Number | Publication Date |
|---|---|
| CN207389530U true CN207389530U (en) | 2018-05-22 |
Family
ID=62401808
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720376397.3U Active CN207389530U (en) | 2017-04-11 | 2017-04-11 | solar energy unmanned plane |
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| CN (1) | CN207389530U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113788138A (en) * | 2021-10-19 | 2021-12-14 | 南京理工大学 | Variable-angle solar wing structure suitable for unmanned aerial vehicle |
-
2017
- 2017-04-11 CN CN201720376397.3U patent/CN207389530U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113788138A (en) * | 2021-10-19 | 2021-12-14 | 南京理工大学 | Variable-angle solar wing structure suitable for unmanned aerial vehicle |
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