CN206782043U - A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure - Google Patents
A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure Download PDFInfo
- Publication number
- CN206782043U CN206782043U CN201720566394.6U CN201720566394U CN206782043U CN 206782043 U CN206782043 U CN 206782043U CN 201720566394 U CN201720566394 U CN 201720566394U CN 206782043 U CN206782043 U CN 206782043U
- Authority
- CN
- China
- Prior art keywords
- fuselage
- rotor
- horn
- motor
- aerial vehicle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Abstract
The utility model discloses a kind of Rapid Combination multi-rotor unmanned aerial vehicle structure, it is related to unmanned vehicle technical field.The structure includes：Fuselage main body and the wing being connected with multiple fuselage main bodies；The fuselage main body includes fuselage epimere, middle fuselage and the fuselage hypomere set gradually from top to bottom；The fuselage epimere includes：Umbrella storehouse and fuselage upper casing；The middle fuselage includes：Middle fuselage housing, horn fixed seat and horn connector A；Fuselage upper plate, fuselage lower plate, power supply section board, battery, umbrella storehouse fixed plate and flight control assemblies are set in the inner chamber of the middle fuselage housing；The fuselage hypomere includes piece housing under fuselage；Piece housing is sequentially detachably connected successively under the fuselage upper casing, the middle fuselage housing, the fuselage.The utility model realizes the multi-rotor unmanned aerial vehicle of different take-off weights, and the shortening unmanned plane manufacturing cycle is short, reduces execution task cost, improves task efficiency.
Description
Technical field
It the utility model is related to unmanned vehicle technical field, more particularly to a kind of Rapid Combination multi-rotor unmanned aerial vehicle knot
Structure.
Background technology
Unmanned plane have flexible light, in light weight, small volume, easily assembly and disassembly, as needed can carry different task equipment,
The features such as manufacturing cycle is short, largely used in military markets and commercial market.
But with the fast development of unmanned flight's technology, more and more higher is required to unmanned plane.The dismounting of existing unmanned plane
By means of instrument, the problem of dismounting is slow, disassembly and assembly time is long be present.
Utility model content
The purpose of this utility model is to provide a kind of Rapid Combination multi-rotor unmanned aerial vehicle structure, so as to solve prior art
Present in foregoing problems.
To achieve these goals, Rapid Combination multi-rotor unmanned aerial vehicle structure described in the utility model, the structure include：
Fuselage main body and the wing being connected with multiple fuselage main bodies；
The fuselage main body includes fuselage epimere, middle fuselage and the fuselage hypomere set gradually from top to bottom；The machine
Section includes with it：Umbrella storehouse and fuselage upper casing；
The middle fuselage includes：Middle fuselage housing, horn fixed seat and horn connector A；The middle fuselage shell
Fuselage upper plate, fuselage lower plate, power supply section board, battery, umbrella storehouse fixed plate and flight control assemblies are set in the inner chamber of body；It is described
Horn fixed seat it is spacing between the fuselage upper plate and the fuselage lower plate and the horn fixed seat run through the fuselage in
Piece housing is connected with the horn connector A；The fuselage upper plate, the power supply section board and the fuselage lower plate are from top to bottom
Set gradually, the battery is spacing in the gap that the fuselage upper plate and the fuselage lower plate are formed through the power supply section board
In；The umbrella storehouse pass through the fuselage upper casing after be fixed in the fixed plate of the umbrella storehouse, umbrella storehouse fixed plate with it is described
Fuselage upper plate connects；The flight control assemblies are arranged on the bottom surface of the fuselage lower plate；The fuselage hypomere includes fuselage
Lower piece housing；Piece housing sequentially detachably connects successively under the fuselage upper casing, the middle fuselage housing, the fuselage
Connect；The horn of the wing is fixed in the horn fixed seat, and the horn connector A and the wing horn are detachable
Connection.
Preferably, the wing includes：Horn, rotor, rotor carry end, undercarriage and horn connector B；The horn
One end sets horn connector B, and the other end sets rotor to carry end；
The agent structure that the rotor carries end is column construction, and rotation is respectively provided with the upper and lower bottom surface of the column construction
Wing anchor tip；Motor is set in the inner chamber of the column construction, and the motor is connected with the rotor anchor tip；Pass through water
Flat-folded overlapping piece, the undercarriage are detachably connected with the horn connector B；The horn connector A is connected with the horn
Part B pin connections.
It is highly preferred that when the quantity of the rotor is 1, the upper bottom surface of the column construction sets rotor anchor tip,
The rotor is fixed on the rotor anchor tip；
When the quantity of the rotor is 2, rotor anchor tip is respectively provided with the upper and lower bottom surface of the column construction, often
A rotor is fixed on the individual rotor anchor tip.
It is highly preferred that when the quantity of the rotor is 1, the column construction is divided into motor waterproof from top to bottom
Lid, motor cabinet and lower bottom cover；The motor is set between the upper motor waterproof cover and the motor cabinet, and the motor is fixed on
On the motor cabinet；Electron speed regulator is set between the motor cabinet and the lower bottom cover.
It is highly preferred that when the quantity of the rotor is 2, the column construction is divided into motor waterproof from top to bottom
Lid, motor cabinet and lower motor waterproof cover；The motor, the motor are set between the upper motor waterproof cover and the motor cabinet
It is fixed on the motor cabinet；Electron speed regulator is set between the motor cabinet and the lower motor waterproof cover.
Preferably, the undercarriage includes undercarriage leg, undercarriage base and the undercarriage rubber base being sequentially arranged；Institute
The fixed connector for stating horizontal folding part is fixedly connected with the undercarriage leg and the horn connector B respectively；The water
The flexible connection head of flat-folded overlapping piece and the horn connector B pin connections.
Preferably, the middle fuselage also includes battery protection frame, and the battery protection frame is enclosed in the week of the battery
Enclose.
Preferably, silica gel U-shaped pad is set between the umbrella storehouse and the fuselage upper casing.
Preferably, the quantity of the horn fixed seat is at least 3, and divides along the even circumferential of the middle fuselage housing
Cloth.
Preferably, reinforcing plate, inner circle of the reinforcing plate along the middle fuselage housing are also set up on the fuselage upper plate
Week is uniformly distributed.
The beneficial effects of the utility model are：
Unmanned plane structure described in the utility model be Rapid Combination and can realize different take-off weights more rotors nobody
Machine, the shortening unmanned plane manufacturing cycle is short, reduces execution task cost, improves task efficiency.Unmanned plane knot described in the utility model
Structure has the characteristics of tool-free installation, rapid-assembling/disassembling, Rapid Combination, anti-aircraft bombing, substantially increases unmanned plane outdoor study task
Efficiency.
Brief description of the drawings
Fig. 1 is the rotor structure schematic diagram of three axle six；
Fig. 2 is the structural representation of fuselage main body top half；
Fig. 3 is the structural representation of fuselage main body the latter half；
Fig. 4 is power supply distributor plate and battery protection frame schematic diagram；
Fig. 5 is the structure connection diagram between umbrella storehouse and fuselage upper casing and fuselage upper plate；
Fig. 6 is the connection diagram of wing and middle fuselage；
Fig. 7 is undercarriage installment state schematic diagram；
Fig. 8 is undercarriage folded state schematic diagram；
Fig. 9 is the unmanned plane structural representation of the rotor of six axle six；
Figure 10 is the unmanned plane structural representation of the rotor of four axle four；
Figure 11 is the unmanned plane structural representation of the rotor of four axle eight.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing, to this reality
It is further elaborated with new.It should be appreciated that embodiment described herein is only explaining this practicality
It is new, it is not used to limit the utility model.
Embodiment
Reference picture 1, Rapid Combination multi-rotor unmanned aerial vehicle structure described in the present embodiment, the structure include：Fuselage main body and
The wing 4 being connected with multiple fuselage main bodies；The fuselage main body includes fuselage epimere 1, the machine set gradually from top to bottom
Body stage casing 2 and fuselage hypomere 3；Explanation, which is explained in more detail, is：
(1) reference picture 2, the fuselage epimere 1 include：Umbrella storehouse 1-1 and fuselage upper casing 1-2；The umbrella storehouse 1-1 with
Silica gel U-shaped pad 1-3 is set between the fuselage upper casing 1-2.
Reference picture 5, umbrella storehouse fixed plate are used to fix umbrella storehouse, and umbrella storehouse fixed plate is connected by hexagonal double-ended bolt and fuselage.
Umbrella chamber structure prevents aircraft bombing when can ensure mechanical disorder.
(2) reference picture 2 and Fig. 3, the middle fuselage 2 include：Middle fuselage housing 2-1, horn fixed seat and horn connect
Fitting A 8；Fuselage upper plate 2-2, fuselage lower plate 2-3, power supply section board 2-4, electricity are set in the inner chamber of the middle fuselage housing
Pond 2-6, umbrella storehouse fixed plate 2-7 and flight control assemblies；The horn fixed seat is spacing in the fuselage upper plate 2-2 and the machine
Between body lower plate 2-3 and the horn fixed seat is connected through the middle fuselage housing 2-1 with the horn connector A 8；
Reference picture 4, the fuselage upper plate 2-2, the power supply section board 2-4 and the fuselage lower plate 2-3 from top to bottom according to
Secondary setting, the battery 2-6 are spacing in the fuselage upper plate 2-2 and the fuselage lower plate 2-3 through the power supply section board 2-4
In the gap of formation；The umbrella storehouse 1-1 is fixed on the umbrella storehouse fixed plate 2-7 after passing through the fuselage upper casing 1-2, is led to
Cross that umbrella storehouse supports A1-1-1 and umbrella storehouse supports B 1-1-2, the umbrella storehouse fixed plate 2-7 is connected with the fuselage upper plate 2-2；
The flight control assemblies are arranged on the bottom surface of the fuselage lower plate 2-3.
1st, on battery
The middle fuselage is also enclosed in the battery 2-6's including battery protection frame 2-5, the battery protection frame 2-5
Around.The battery is that 2-6 is lithium battery.
Power supply distributor plate 2-4 realizes that power supply is distributed in battery circumferential, facilitates unmanned plane body to connect up.Battery protection frame 2-5
Ensure that battery 2-6 is deformed or destroyed caused by not hit by fuselage upper plate 2-2 edges.
2nd, on horn fixed seat
The quantity of the horn fixed seat is at least 3, and is distributed along the even circumferential of the middle fuselage housing 2-1.
The horn fixed seat is bolted between the fuselage upper plate 2-2 and the fuselage lower plate 2-3.It is described
Horn fixed seat includes left horn fixed seat and right arm fixed seat, and the horn connector A is fixed on by high-strength bolt
Between left horn fixed seat and right arm fixed seat.
3rd, on flight control assemblies
The flight control assemblies include flight controller fixed plate 2-8 and are fixed on the flight controller fixed plate 2-
8 flight controller 2-9, by flight controller pillar, the flight controller fixed plate 2-8 is fixed on the fuselage lower plate
2-3 bottom surface.
4th, two rotors are installed on a wing
When wing installs two rotors, reinforcing plate is also set up on the fuselage upper plate 2-2, the reinforcing plate is along institute
The inner periphery for stating middle fuselage housing 2-1 is uniformly distributed.
(3) the fuselage hypomere 3 includes piece housing 3-1 under fuselage；
Piece housing 3-1 sequentially successively may be used under the fuselage upper casing 1-2, the middle fuselage housing 2-1, the fuselage
Dismantling connection；Specially：Piece housing 3-1 leads under the fuselage upper casing 1-2, the middle fuselage housing 2-1, the fuselage
Neck realization connection is crossed, piece housing 3-1 is provided with neck under fuselage upper casing 1-2, fuselage, is closed in middle fuselage housing 2-1
Piece housing 3-1 under fuselage upper casing 1-2, fuselage, it is real by rotating piece housing 3-1 under upper fuselage upper casing 1-2, fuselage
Now fasten.
(4) horn of the wing 4 is fixed in the horn fixed seat, the horn connector A8 and the wing
Horn be detachably connected.
Reference picture 6, the wing 4 include：Horn 4-1, rotor 4-2, rotor carry end 4-3, undercarriage 5 and horn connector
B 7；One end of the horn sets horn connector B 7, and the other end sets rotor to carry end；The rotor carries the agent structure at end
For column construction, rotor anchor tip is respectively provided with the upper and lower bottom surface of the column construction；In the inner chamber of the column construction
Motor is set, and the motor is connected with the rotor anchor tip；By horizontal folding part 6, the undercarriage 5 and the horn
Connector B 7 is detachably connected.
1st, on column construction
Indicator lamp, the indicator lamp and the motor connection are set on the outer wall of the column construction.
Motor cabinet and motor waterproof cover are also set up in the inner chamber of the column construction；The motor is fixed on the motor cabinet
On, the motor waterproof cover is fastened on the motor.
2nd, on undercarriage
Reference picture 7 and Fig. 8, the undercarriage 5 include undercarriage leg 5-1, the undercarriage base 5-2 being sequentially arranged and risen
Fall frame rubber base 5-3；
The fixed connector of the horizontal folding part 6 is fixed with the undercarriage leg and the horn connector B7 respectively
Connection；The flexible connection head of the horizontal folding part 6 and the horn connector B7 pin connections, the quick folding of pin connection undercarriage
It is folded.No instrument fast folding, convenient installation, packaging and transport are also realized by pin connection.
3rd, on horn connector A and the horn connector B
Reference picture 5, by quick pin 9, the horn connector A8 and the pin connections of horn connector B 7, realize fast
Quick-mounting is torn open, the pin connection limitation radial and axial activity of horn between the horn connector A8 and the horn connector B 7.
4th, on wing
When the quantity of the rotor is 1, the upper bottom surface of the column construction sets rotor anchor tip, and the rotor is consolidated
It is scheduled on the rotor anchor tip；The column construction is divided into motor waterproof cover, motor cabinet and bottom from top to bottom
Lid；The motor is set between the upper motor waterproof cover and the motor cabinet, and the motor is fixed on the motor cabinet；Institute
State and electron speed regulator is set between motor cabinet and the lower bottom cover.
When the quantity of the rotor is 2, rotor anchor tip is respectively provided with the upper and lower bottom surface of the column construction, often
A rotor is fixed on the individual rotor anchor tip.The column construction is divided into motor waterproof from top to bottom
Lid, motor cabinet and lower motor waterproof cover；The motor, the motor are set between the upper motor waterproof cover and the motor cabinet
It is fixed on the motor cabinet；Electron speed regulator is set between the motor cabinet and the lower motor waterproof cover.
Unmanned plane structure described in embodiment 1 is the unmanned plane structure of the rotor of three axle six, can be with according to the quantity of wing
Make the unmanned plane structure of the rotor of six axle six as shown in Figure 9, the unmanned plane structure of the rotor of four axle four as shown in Figure 10, such as Figure 11 institutes
Show the unmanned plane structure of the rotor of four axle eight.
By using above-mentioned technical proposal disclosed in the utility model, following beneficial effect has been obtained：
Unmanned plane structure described in the utility model be Rapid Combination and can realize different take-off weights more rotors nobody
Machine, the shortening unmanned plane manufacturing cycle is short, reduces execution task cost, improves task efficiency.Unmanned plane knot described in the utility model
Structure has the characteristics of tool-free installation, rapid-assembling/disassembling, Rapid Combination, anti-aircraft bombing, substantially increases unmanned plane outdoor study task
Efficiency.
Described above is only preferred embodiment of the present utility model, it is noted that for the common skill of the art
For art personnel, on the premise of the utility model principle is not departed from, some improvements and modifications can also be made, these improve and
Retouching should also regard the scope of protection of the utility model.
Claims (10)
1. a kind of Rapid Combination multi-rotor unmanned aerial vehicle structure, it is characterised in that the structure includes：Fuselage main body and with multiple institutes
State the wing (4) of fuselage main body connection；
The fuselage main body includes fuselage epimere (1), middle fuselage (2) and the fuselage hypomere (3) set gradually from top to bottom；
The fuselage epimere (1) includes：Umbrella storehouse (1-1) and fuselage upper casing (1-2)；
The middle fuselage (2) includes：Middle fuselage housing (2-1), horn fixed seat and horn connector A (8)；The fuselage
Fuselage upper plate (2-2), fuselage lower plate (2-3), power supply section board (2-4), battery (2-6), umbrella are set in the inner chamber of middle housing
Storehouse fixed plate (2-7) and flight control assemblies；The horn fixed seat is spacing under the fuselage upper plate (2-2) and the fuselage
Between plate (2-3) and the horn fixed seat is connected through the middle fuselage housing (2-1) with the horn connector A (8)；
The fuselage upper plate (2-2), the power supply section board (2-4) and the fuselage lower plate (2-3) set gradually from top to bottom,
The battery (2-6) is spacing in the fuselage upper plate (2-2) and the fuselage lower plate (2- through the power supply section board (2-4)
3) in the gap formed；The umbrella storehouse (1-1) is fixed on umbrella storehouse fixed plate after passing through the fuselage upper casing (1-2)
On (2-7), umbrella storehouse fixed plate (2-7) is connected with the fuselage upper plate (2-2)；The flight control assemblies are arranged on described
On the bottom surface of fuselage lower plate (2-3)；
The fuselage hypomere (3) includes piece housing (3-1) under fuselage；
Piece housing (3-1) is sequentially successively under the fuselage upper casing (1-2), the middle fuselage housing (2-1), the fuselage
It is detachably connected；
The horn of the wing (4) is fixed in the horn fixed seat, the horn connector A (8) and the machine of the wing
Arm is detachably connected.
2. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 1, it is characterised in that the wing (4) includes：Machine
Arm, rotor, rotor carry end, undercarriage and horn connector B (7)；
One end of the horn sets horn connector B (7), and the other end sets rotor to carry end；
The agent structure that the rotor carries end is column construction, and being respectively provided with rotor on the upper and lower bottom surface of the column construction fixes
Joint；Motor is set in the inner chamber of the column construction, and the motor is connected with the rotor anchor tip；Pass through horizontal folding
Part (6), the undercarriage are detachably connected with the horn connector B (7)；The horn connector A (8) connects with the horn
Fitting B (7) pin connection.
3. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 2, it is characterised in that
When the quantity of the rotor is 1, the upper bottom surface of the column construction sets rotor anchor tip, and the rotor is fixed on
On the rotor anchor tip；
When the quantity of the rotor is 2, rotor anchor tip, Mei Gesuo are respectively provided with the upper and lower bottom surface of the column construction
State and a rotor is fixed on rotor anchor tip.
4. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 2, it is characterised in that the quantity of the rotor is 1
When individual, the column construction is divided into motor waterproof cover, motor cabinet and lower bottom cover from top to bottom；The upper motor waterproof cover
The motor is set between the motor cabinet, and the motor is fixed on the motor cabinet；The motor cabinet and the bottom
Electron speed regulator is set between lid.
5. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 2, it is characterised in that the quantity of the rotor is 2
When individual, the column construction is divided into motor waterproof cover, motor cabinet and lower motor waterproof cover from top to bottom；The upper motor
The motor is set between waterproof cover and the motor cabinet, and the motor is fixed on the motor cabinet；The motor cabinet and institute
State and electron speed regulator is set between lower motor waterproof cover.
6. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 2, it is characterised in that the undercarriage (5) includes
Undercarriage leg, undercarriage base and the undercarriage rubber base being sequentially arranged；
The fixed connector of the horizontal folding part (6) is fixed with the undercarriage leg and the horn connector B (7) respectively
Connection；The flexible connection head of the horizontal folding part (6) and horn connector B (7) pin connection.
7. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 1, it is characterised in that the middle fuselage also includes
Battery protection frame (2-5), the battery protection frame (2-5) are enclosed in around the battery (2-6).
8. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 1, it is characterised in that the umbrella storehouse (1-1) and institute
State and silica gel U-shaped pad (1-3) is set between fuselage upper casing (1-2).
9. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 1, it is characterised in that the number of the horn fixed seat
Amount is at least 3, and is distributed along the even circumferential of the middle fuselage housing (2-1).
10. Rapid Combination multi-rotor unmanned aerial vehicle structure according to claim 1, it is characterised in that the fuselage upper plate (2-2)
On also set up reinforcing plate, inner periphery of the reinforcing plate along the middle fuselage housing (2-1) is uniformly distributed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720566394.6U CN206782043U (en) | 2017-05-19 | 2017-05-19 | A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720566394.6U CN206782043U (en) | 2017-05-19 | 2017-05-19 | A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206782043U true CN206782043U (en) | 2017-12-22 |
Family
ID=60712510
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720566394.6U Active CN206782043U (en) | 2017-05-19 | 2017-05-19 | A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206782043U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107097928A (en) * | 2017-05-19 | 2017-08-29 | 北京帝测科技股份有限公司 | A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure |
| CN109455291A (en) * | 2018-12-25 | 2019-03-12 | 拓攻（南京）机器人有限公司 | A kind of rack and unmanned plane for unmanned plane |
-
2017
- 2017-05-19 CN CN201720566394.6U patent/CN206782043U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107097928A (en) * | 2017-05-19 | 2017-08-29 | 北京帝测科技股份有限公司 | A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure |
| CN109455291A (en) * | 2018-12-25 | 2019-03-12 | 拓攻（南京）机器人有限公司 | A kind of rack and unmanned plane for unmanned plane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107097928A (en) | A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure | |
| CN206782043U (en) | A kind of Rapid Combination multi-rotor unmanned aerial vehicle structure | |
| CN104787318A (en) | Multi-rotor unmanned aerial vehicle with function of loaded long-time flying | |
| CN205854488U (en) | A kind of solar energy charging type unmanned plane | |
| CN205854465U (en) | A kind of low windage unmanned plane | |
| CN102778887A (en) | Pneumatic performance comprehensive testing platform of non-tail-rotor reaction torque system of a helicopter | |
| CN206141829U (en) | Many rotors of stationary vane combined type aircraft | |
| CN108162795A (en) | A kind of airborne aircraft aerial power supply unit of mating solar energy | |
| CN204916171U (en) | Many rotor unmanned aerial vehicle with flight of load long term | |
| CN106494640A (en) | A kind of multi-rotor unmanned aerial vehicle test and training unified platform | |
| CN102424111A (en) | Flexible saucer-shaped aircraft | |
| CN208488103U (en) | A kind of magnetic compass correction simulator | |
| CN106628104A (en) | Agricultural plant protection unmanned aerial vehicle carrying mechanism | |
| CN106696620A (en) | Novel single double ducted fan combined type hovercar | |
| CN209192231U (en) | A kind of teaching type unmanned plane | |
| CN205916331U (en) | Plant protection unmanned plane | |
| CN104843191B (en) | Contactless smart rain insensitive device for unmanned plane | |
| CN106741910A (en) | A kind of disc-shaped unmanned machine | |
| CN207157491U (en) | The wing of unmanned plane and aileron attachment structure | |
| CN206704550U (en) | To the depopulated helicopter fuselage interior structure of arrangement after a kind of turboaxle motor | |
| CN205345344U (en) | Eight plant protection machines | |
| CN110174025A (en) | A kind of wind and solar integrated new energy guided missile vertical air flat pad | |
| CN204327406U (en) | A kind of high altitude wind power plant | |
| CN104421103A (en) | Wind power generating device combining solar panels and power generating device consisting of wind power generating devices | |
| CN208634703U (en) | A kind of steady holder of two shaft types increasing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |