CN205819537U - A kind of wing being applicable to small-sized electric unmanned plane - Google Patents
A kind of wing being applicable to small-sized electric unmanned plane Download PDFInfo
- Publication number
- CN205819537U CN205819537U CN201620572115.2U CN201620572115U CN205819537U CN 205819537 U CN205819537 U CN 205819537U CN 201620572115 U CN201620572115 U CN 201620572115U CN 205819537 U CN205819537 U CN 205819537U
- Authority
- CN
- China
- Prior art keywords
- spring
- wing
- clamp
- hole
- buckle
- 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
- 239000000463 material Substances 0.000 claims description 10
- 229920006351 engineering plastic Polymers 0.000 claims description 4
- 239000011152 fibreglass Substances 0.000 claims description 3
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical compound CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 claims description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 241001669680 Dormitator maculatus Species 0.000 claims description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 229910052744 lithium Inorganic materials 0.000 claims description 2
- 229910052751 metal Inorganic materials 0.000 claims description 2
- 239000002184 metal Substances 0.000 claims description 2
- 230000005611 electricity Effects 0.000 claims 1
- 239000000835 fiber Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 abstract description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 229920003023 plastic Polymers 0.000 description 3
- 239000004033 plastic Substances 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 230000000007 visual effect Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a kind of wing being applicable to small-sized electric unmanned plane, it includes wing root (1), wing (2) and fast assembling-disassembling assembly (3).Fast assembling-disassembling assembly (3) includes buckle (3A), lower pinch plate (3B), upper clamp (3C), lower clamp (3D) and is placed in the spring of clamp (3C, 3D) lower section, upper buckle (3A) is placed in the through hole of wing (2) top panel, lower pinch plate (3B) is placed in the through hole of wing (2) lower panel, upper clamp (3C) is placed in the blind hole of wing root (1) top panel, and lower clamp (3D) is placed in the blind hole of wing root (1) lower panel.Wing (2) is merged with wing root (1) and separates by Quick-dismantle component (3) by this utility model, thus reaches the technique effect of simple and fast dismounting.
Description
Technical field
This utility model relates to a kind of wing being applied to small-sized electric unmanned plane, more particularly, refers to a kind of being suitable for
The wing with fast assembling-disassembling in small-sized electric unmanned plane.
Background technology
Unmanned plane is broadly for need not the various remotely-piloted vehicle that driver's boarding is driven, and electronic unmanned plane is kinetic force
Source is the unmanned plane of electric energy, and current below 100kg unmanned plane is referred to as SUAV.The most all in substantial amounts of use
SUAV carries out taking photo by plane, surveys and draws, investigation etc..
SUAV conveniently can use in multi-environment.But longer wing is for carrying the most not
Just, even if some SUAV wing is dismantled and assembled at present, the most only structure utilizes the materials such as carbon pipe to be directly connected to, although side
Carry, but do not solve fast assembling-disassembling problem, this structure all can be wasted during each use dismounting
Time, reduce service efficiency, it is also possible to damage unmanned plane.
Summary of the invention
In order to improve the defect that one wing exists, and it is unfavorable for the transport of small-sized electric unmanned plane, this utility model
Devising a kind of wing with fast assembling-disassembling being applicable to small-sized electric unmanned plane, this wing can be quick by Quick-dismantle component
Realize the fast assembling-disassembling of wing and wing root and ensure bonding strength.
This utility model devises a kind of wing with fast assembling-disassembling being applicable to small-sized electric unmanned plane, and this is quickly torn open
The wing of dress includes wing root (1), wing (2) and fast assembling-disassembling assembly (3)；Wing (2) is hollow structure, and battery (4) is placed in
In cavity (2C)；
The connecting portion (1A) of wing root (1) one end is fixed with fuselage, and machine is inserted in the aerofoil profile Plug Division (1B) of wing root (1) other end
In the cavity (2C) of the wing (2)；The top panel (1B1) of aerofoil profile Plug Division (1B) is provided with blind hole (1B1A), blind hole on this
(1B1A) it is used for placing buckle (3C), AA spring (31), AB spring (32), AC spring (33), AD spring (34)；Aerofoil profile grafting
The lower panel (1B2) in portion (1B) is provided with lower blind hole (1B2A), and this lower blind hole (1B2A) is used for placing lower clamp (3D), BA spring
(35), BB spring (36), BC spring (37), BD spring (38)；
The top panel (2A) of wing (2) is provided with through hole (2A1), and upper through hole (2A1) is for the upper button of Quick-dismantle component (3)
Plate (3A) other end passes；The lower panel (2B) of wing (2) is provided with lower through-hole (2B1), and lower through-hole (2B1) is used for Quick-dismantle component
(3) lower pinch plate (3B) other end passes；The cavity (2C) of wing (2) one end is used for placing aerofoil profile Plug Division (1B)；
Fast assembling-disassembling assembly (3) include buckle (3A), lower pinch plate (3B), upper buckle (3C), lower buckle (3D) and
AA spring (31), AB spring (32), AC spring (33), AD spring (34), BA spring (35), BB spring (36), BC spring (37),
BD spring (38)；
The other end of AA spring (31), AB spring (32), AC spring (33) and AD spring (34) is separately mounted to buckle
(3C) in four grooves (3C2) of bottom panel (3C1), AA spring (31), AB spring (32), AC spring (33) and AD spring
(34) one end contacts with the upper blind hole (1B1A) of the top panel of aerofoil profile Plug Division (1B) (1B1)；
The other end of BA spring (35), BB spring (36), BC spring (37) and BD spring (38) is separately mounted to lower buckle
(3D) in four grooves of bottom panel, one end of BA spring (35), BB spring (36), BC spring (37) and BD spring (38) with
Lower blind hole (1B2A) contact of the lower panel (1B2) of aerofoil profile Plug Division (1B)；
One end of upper buckle (3A) is bonded in upper through hole (2A1) place of the top panel (2A) of wing (2), and upper buckle (3A)
The other end top panel (2A) that is placed in wing (2) upper through hole (2A1) in；
One end of lower pinch plate (3B) is bonded in lower through-hole (2B1) place of the lower panel (2B) of wing (2), and lower pinch plate (3B)
The other end lower panel (2B) that is placed in wing (2) lower through-hole (2B1) in；
In the upper blind hole (1B1A) of the top panel (1B1) that upper buckle (3C) is arranged on the aerofoil profile Plug Division (1B) of wing root (1),
And upper buckle (3C) bottom is provided with AA spring (31), AB spring (32), AC spring (33) and AD spring (34)；
In the lower blind hole (1B2A) of the lower panel (1B2) that lower buckle (3D) is arranged on the aerofoil profile Plug Division (1B) of wing root (1),
And lower buckle (3D) bottom is provided with BA spring (35), BB spring (36), BC spring (37) and BD spring (38).
The advantage of the wing that this utility model has fast assembling-disassembling is:
1. whole wing is designed to Split type structure, by fast assembling-disassembling assembly 3 realize wing 2 and wing root 1 combination or
Separate so that the small-sized electric unmanned plane after tearing open is easy to carry.
2. the fast assembling-disassembling assembly 3 of spring and click-on design is used, it is possible to make small-sized electric unmanned plane be easy to wing and assemble
More rapid, also make the wing of small-sized electric unmanned plane dismantle simpler, safety simultaneously.
3. the fast assembling-disassembling assembly 3 of this utility model design, when wing 2 is by external force deformation, under the inefficacy of buckle,
Reach wing 2 to separate with wing root 1, while playing protection wing root 1, make fuselage also be protected.
Accompanying drawing explanation
Fig. 1 is the external structure with fast assembling-disassembling wing being applicable to small-sized electric unmanned plane of the present utility model.
Figure 1A is outside another visual angle with fast assembling-disassembling wing being applicable to small-sized electric unmanned plane of the present utility model
Portion's structure chart.
Figure 1B is the exploded view with fast assembling-disassembling wing being applicable to small-sized electric unmanned plane of the present utility model.
Fig. 1 C is that another visual angle with fast assembling-disassembling wing being applicable to small-sized electric unmanned plane of the present utility model is divided
Xie Tu.
Fig. 2 is the structure chart of Quick-dismantle component of the present utility model.
Fig. 2 A is another viewing angle constructions figure of Quick-dismantle component of the present utility model.
Fig. 3 is that the assembling with fast assembling-disassembling wing and battery being applicable to small-sized electric unmanned plane of the present utility model divides
Unhitch composition.
Fig. 3 A is the sectional structure chart after wing of the present utility model assembles with battery.
| 1. wing root | 1A. connecting portion | 1B. aerofoil profile Plug Division |
| 1B1. top panel | The upper blind hole of 1B1A. | 1B2. lower panel |
| Blind hole under 1B2A. | 2. wing | 2A. top panel |
| The upper through hole of 2A1. | 2B. lower panel | 2B1. lower through-hole |
| 2C. cavity | 3. fast assembling-disassembling assembly | The upper buckle of 3A. |
| 3B. lower pinch plate | The upper clamp of 3C. | 3C1. bottom panel |
| 3C2. groove | Clamp under 3D. | 31.AA spring |
| 32.AB spring | 33.AC spring | 34.AD spring |
| 35.BA spring | 36.BB spring | 37.BC spring |
| 38.BD spring | 4. battery |
Detailed description of the invention
Below in conjunction with accompanying drawing, this utility model is described in further detail.
Seeing shown in Fig. 1, Figure 1A, Figure 1B, Fig. 1 C, this utility model devises a kind of small-sized electric unmanned plane that is applicable to
Having the wing of fast assembling-disassembling, the wing of described fast assembling-disassembling includes wing root 1, wing 2 and fast assembling-disassembling assembly 3.Wing 2 is
Hollow structure, battery 4 is arranged in the cavity 2C of wing 2.
Wing root 1:
Seeing shown in Fig. 1, Figure 1A, Figure 1B, Fig. 1 C, Fig. 2, Fig. 2 A, Fig. 3, the connecting portion 1A of wing root 1 one end is solid with fuselage
Fixed, the aerofoil profile Plug Division 1B of wing root 1 other end inserts in the cavity 2C of wing 2.The top panel 1B1 of aerofoil profile Plug Division 1B is provided with
Upper blind hole 1B1A, on this blind hole 1B1A be used for placing clamp 3C and four springs (AA spring 31, AB spring 32, AC spring 33,
AD spring 34), the other end of i.e. four springs (AA spring 31, AB spring 32, AC spring 33, AD spring 34) is each arranged on
In the groove 3C2 of the bottom panel 3C1 of clamp 3C；The lower panel 1B2 of aerofoil profile Plug Division 1B is provided with lower blind hole 1B2A, this lower blind hole
1B2A is used for placing lower clamp 3D and four springs (BA spring 35, BB spring 36, BC spring 37, BD spring 38), i.e. four bullets
The other end of spring (BA spring 35, BB spring 36, BC spring 37, BD spring 38) is arranged in the groove bottom lower clamp 3D.
In this utility model, wing root 1 material is fiberglass, carbon fiber, the contour strength plastic material of engineering plastics.
Wing 2:
Seeing shown in Fig. 1, Figure 1A, Figure 1B, Fig. 1 C, Fig. 3, Fig. 3 A, wing 2 is hollow structure.On the top panel 2A of wing 2
It is provided with through hole 2A1, upper through hole 2A1 and passes for the upper buckle 3A other end of Quick-dismantle component 3；Set on the lower panel 2B of wing 2
Lower through-hole 2B1, lower through-hole 2B1 is had to pass for the lower pinch plate 3B other end of Quick-dismantle component 3.The cavity 2C of wing 2 one end is used for
Place aerofoil profile Plug Division 1B.Battery 4 is arranged in the cavity 2C of wing 2, and the profile of battery 4 is mated with the aerofoil profile of wing 2, this
Sample is conducive to saving space, and battery 4 is lithium battery.
In this utility model, wing 2 selects NACA 2212 aerofoil profile.
In this utility model, wing 2 material is fiberglass, carbon fiber, the contour strength plastic material of engineering plastics.But
The strength of materials of wing root 1 is higher than the strength of materials of wing 2.
Fast assembling-disassembling assembly 3:
Seeing shown in Fig. 1, Figure 1A, Figure 1B, Fig. 1 C, Fig. 2, Fig. 2 A, fast assembling-disassembling assembly 3 includes buckle 3A, lower buckles
Plate 3B, upper buckle 3C, lower buckle 3D and eight springs (AA spring 31, AB spring 32, AC spring 33, AD spring 34, BA springs
35, BB spring 36, BC spring 37, BD spring 38).Wherein, upper buckle 3A is identical with the structure of lower pinch plate 3B, upper buckle 3C with under
The structure of buckle 3D is identical.Metal spring selected by spring.Upper buckle 3A, lower pinch plate 3B, upper buckle 3C and lower buckle 3D are glass
The contour strength plastic material of steel, carbon fiber, engineering plastics.
AA spring 31, AB spring 32, the other end of AC spring 33 and AD spring 34 are separately mounted to the bottom surface of buckle 3C
In four groove 3C2 of plate 3C1, AA spring 31, AB spring 32, AC spring 33 and AD spring 34 one end respectively with aerofoil profile grafting
The bottom contact of upper blind hole 1B1A of the top panel 1B1 of portion 1B.
BA spring 35, BB spring 36, the other end of BC spring 37 and BD spring 38 are separately mounted to the bottom surface of lower buckle 3D
In four grooves of plate, under BA spring 35, BB spring 36, one end of BC spring 37 and BD spring 38 and aerofoil profile Plug Division (1B)
The bottom contact of the lower blind hole (1B2A) of panel (1B2).
One end of upper buckle 3A is bonded at the upper through hole 2A1 of the top panel 2A of wing 2, and the other end of upper buckle 3A is put
In the upper through hole 2A1 of the top panel 2A of wing 2.
At the lower through-hole 2B1 of the lower panel 2B that one end of lower pinch plate 3B is bonded in wing 2, and the other end of lower pinch plate 3B is put
In the lower through-hole 2B1 of the lower panel 2B of wing 2.
In upper blind hole 1B1A of the top panel 1B1 that upper buckle 3C is arranged on the aerofoil profile Plug Division 1B of wing root 1, and upper buckle 3C
Bottom is provided with AA spring 31, AB spring 32, AC spring 33 and AD spring 34.
In lower blind hole 1B2A of the lower panel 1B2 that lower buckle 3D is arranged on the aerofoil profile Plug Division 1B of wing root 1, and lower buckle 3D
Bottom is provided with BA spring 35, BB spring 36, BC spring 37 and BD spring 38.
In this utility model, when wing 2 is subject to 200% impulsive force exceeding design load, wing 2 part can become
Shape, the wing 2 deformation under the conditions of external force result in pinch plate (3A, 3B) in Quick-dismantle component 3 and lost efficacy, and causes the impulsive force cannot
It is delivered to wing root 1, thus protects wing root 1 and be not damaged, owing to wing root 1 is fixed with fuselage, also make fuselage not be damaged.
Application Quick-dismantle component 3 carries out separation when taking apart, presses buckle 3A and lower pinch plate 3B, it is achieved wing 2 and the wing simultaneously
The separation of root 1.I.e. going up buckle 3A when pressing, the other end of upper buckle 3A contacts with upper buckle 3C, causes buckle 3C to depress to
Less than upper through hole 2A1；When lower pinch plate 3B presses, the other end of lower pinch plate 3B contacts with lower buckle 3D, causes lower buckle 3D to depress
To less than lower through-hole 2B1；When on ensureing, buckle 3C and lower buckle 3D are simultaneously less than through hole on wing 2, then reach wing 2 with
The separation of wing root 1.
When application Quick-dismantle component 3 assembles, the aerofoil profile Plug Division 1B of wing root 1 is inserted in the cavity 2C of wing 2, when upper
Buckle 3C upsprings when running into through hole 2A1, and lower buckle 3D upsprings when running into lower through-hole 2B1, reaches to assemble locking wing 2 and wing root
1。
This utility model is a kind of wing with fast assembling-disassembling being applicable to small-sized electric unmanned plane, to be solved is
How to realize the technical problem of wing dismounting easily and efficiently, wing 2 is entered with wing root 1 by this utility model by Quick-dismantle component 3
Row merges assembling and separates, thus reaches the technique effect of simple quick release.
Claims (6)
1. the wing being applicable to small-sized electric unmanned plane, it is characterised in that: the wing of fast assembling-disassembling include wing root (1),
Wing (2) and fast assembling-disassembling assembly (3)；Wing (2) is hollow structure, and battery (4) is placed in cavity (2C)；
The connecting portion (1A) of wing root (1) one end is fixed with fuselage, and wing is inserted in the aerofoil profile Plug Division (1B) of wing root (1) other end
(2) in cavity (2C)；The top panel (1B1) of aerofoil profile Plug Division (1B) is provided with blind hole (1B1A), blind hole (1B1A) on this
For placing upper clamp (3C), AA spring (31), AB spring (32), AC spring (33), AD spring (34)；Aerofoil profile Plug Division (1B)
Lower panel (1B2) be provided with lower blind hole (1B2A), this lower blind hole (1B2A) be used for placing lower clamp (3D), BA spring (35),
BB spring (36), BC spring (37), BD spring (38)；
The top panel (2A) of wing (2) is provided with through hole (2A1), and upper through hole (2A1) is for the upper buckle of Quick-dismantle component (3)
(3A) other end passes；The lower panel (2B) of wing (2) is provided with lower through-hole (2B1), and lower through-hole (2B1) is used for Quick-dismantle component
(3) lower pinch plate (3B) other end passes；The cavity (2C) of wing (2) one end is used for placing aerofoil profile Plug Division (1B)；
Fast assembling-disassembling assembly (3) includes buckle (3A), lower pinch plate (3B), upper clamp (3C), lower clamp (3D) and AA bullet
Spring (31), AB spring (32), AC spring (33), AD spring (34), BA spring (35), BB spring (36), BC spring (37), BD bullet
Spring (38)；
The other end of AA spring (31), AB spring (32), AC spring (33) and AD spring (34) is separately mounted to clamp (3C)
Bottom panel (3C1) four grooves (3C2) in, AA spring (31), AB spring (32), AC spring (33) and AD spring (34)
One end contacts with the upper blind hole (1B1A) of the top panel of aerofoil profile Plug Division (1B) (1B1)；
The other end of BA spring (35), BB spring (36), BC spring (37) and BD spring (38) is separately mounted to lower clamp (3D)
Bottom panel four grooves in, BA spring (35), BB spring (36), BC spring (37) and one end of BD spring (38) and aerofoil profile
Lower blind hole (1B2A) contact of the lower panel (1B2) of Plug Division (1B)；
One end of upper buckle (3A) is bonded in upper through hole (2A1) place of the top panel (2A) of wing (2), and upper buckle (3A) is another
In the upper through hole (2A1) of the top panel (2A) that one end is placed in wing (2)；
One end of lower pinch plate (3B) is bonded in lower through-hole (2B1) place of the lower panel (2B) of wing (2), and lower pinch plate (3B)
In the lower through-hole (2B1) of the lower panel (2B) that the other end is placed in wing (2)；
In the upper blind hole (1B1A) of the top panel (1B1) that upper clamp (3C) is arranged on the aerofoil profile Plug Division (1B) of wing root (1), and on
Clamp (3C) bottom is provided with AA spring (31), AB spring (32), AC spring (33) and AD spring (34)；
In the lower blind hole (1B2A) of the lower panel (1B2) that lower clamp (3D) is arranged on the aerofoil profile Plug Division (1B) of wing root (1), and under
Clamp (3D) bottom is provided with BA spring (35), BB spring (36), BC spring (37) and BD spring (38).
The wing being applicable to small-sized electric unmanned plane the most according to claim 1, it is characterised in that: wing (2) is NACA
2212 aerofoil profiles.
The wing being applicable to small-sized electric unmanned plane the most according to claim 1, it is characterised in that: battery (4) is lithium electricity
Pond, the profile of battery (4) is mated with the aerofoil profile of wing (2).
The wing being applicable to small-sized electric unmanned plane the most according to claim 1, it is characterised in that: spring is metal elastic
Spring.
The wing being applicable to small-sized electric unmanned plane the most according to claim 1, it is characterised in that: upper buckle (3A), under
Buckle (3B), upper clamp (3C) and lower clamp (3D) are the processing of high intensity plasticity engineering plastic materials.
The wing being applicable to small-sized electric unmanned plane the most according to claim 1, it is characterised in that: upper buckle (3A), under
Buckle (3B), upper clamp (3C) and lower clamp (3D) are fiberglass or carbon fibre material processing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620572115.2U CN205819537U (en) | 2016-06-14 | 2016-06-14 | A kind of wing being applicable to small-sized electric unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620572115.2U CN205819537U (en) | 2016-06-14 | 2016-06-14 | A kind of wing being applicable to small-sized electric unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205819537U true CN205819537U (en) | 2016-12-21 |
Family
ID=57568651
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620572115.2U Active CN205819537U (en) | 2016-06-14 | 2016-06-14 | A kind of wing being applicable to small-sized electric unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205819537U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651162A (en) * | 2017-09-27 | 2018-02-02 | 西安冰果智能航空科技有限公司 | A kind of unmanned plane wing quick assembling mechanism |
-
2016
- 2016-06-14 CN CN201620572115.2U patent/CN205819537U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651162A (en) * | 2017-09-27 | 2018-02-02 | 西安冰果智能航空科技有限公司 | A kind of unmanned plane wing quick assembling mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2012028467A8 (en) | Air sucking vehicle fuselage component, method for producing an air sucking vehicle fuselage component and a vehicle, especially an aircraft, with an air sucking vehicle fuselage component | |
| EP2849253A3 (en) | Battery pack | |
| EP2337137A3 (en) | Rechargeable battery | |
| CN205819537U (en) | A kind of wing being applicable to small-sized electric unmanned plane | |
| CN104494805A (en) | Carbon fiber multi-rotor unmanned aircraft fuselage and method for manufacturing the same | |
| CN105364772B (en) | A kind of lightweight gas turbine power turbine disk decomposer and method | |
| CN202894202U (en) | Rivet guide positioning riveting tool | |
| US10566587B2 (en) | Electrified vehicle plate with integrated compression limiter | |
| CN206031756U (en) | Unmanned aerial vehicle wing | |
| CN202460716U (en) | Separated type geared roller for double-geared roller crusher | |
| CN105691599B (en) | A kind of undercarriage disassembly and assembly structure of aircraft | |
| CN209535437U (en) | A kind of aircraft frame and its aircraft | |
| CN209903278U (en) | Cutting device for lamp box cloth calender | |
| CN202246525U (en) | Polytetrafluoroethylene glass fiber cloth demolding cloth | |
| CN107785510A (en) | One kind sealing nail pressing device | |
| CN205600752U (en) | Clamping jaw structure | |
| CN207487107U (en) | Convenient for the holding structure of pedestal dismounting | |
| CN204565712U (en) | Fast-positioning device | |
| CN205686601U (en) | A kind of fuselage beam | |
| CN212033116U (en) | Unmanned aerial vehicle battery case loads structure | |
| CN213921511U (en) | Special frock of aircraft cabin luggage rack actuator dismouting | |
| CN219456267U (en) | Weak current engineering intelligent detection equipment | |
| CN220924547U (en) | Quick detach formula unmanned aerial vehicle undercarriage and unmanned aerial vehicle | |
| CN211417568U (en) | Unmanned aerial vehicle frame and unmanned aerial vehicle | |
| CN203793614U (en) | Unmanned aerial vehicle wing connecting structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information |
Inventor after: Li Wei Inventor before: Chen Pei |
|
| CB03 | Change of inventor or designer information | ||
| CP03 | Change of name, title or address |
Address after: Room 301-9, North Block, 3rd Floor, Building 1, Yard 1, Automobile Museum East Road, Fengtai District, Beijing, 100160 Patentee after: Beijing Beehive Sky Technology Co.,Ltd. Country or region after: China Address before: 271200 No. 536 Lianhua Mountain Road, Xintai Economic Development Zone, Tai'an, Shandong Patentee before: SHANDONG HONEYCOMB AVIATION TECHNOLOGY Co.,Ltd. Country or region before: China |
|
| CP03 | Change of name, title or address | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240402 Address after: 100160 room 301-6, North block, 3 / F, building 1, yard 1, East Road of Automobile Museum, Fengtai District, Beijing Patentee after: HONEYCOMB AEROSPACE TECNOLOGIES (BEIJING) CO.,LTD. Country or region after: China Address before: Room 301-9, North Block, 3rd Floor, Building 1, Yard 1, Automobile Museum East Road, Fengtai District, Beijing, 100160 Patentee before: Beijing Beehive Sky Technology Co.,Ltd. Country or region before: China |
|
| TR01 | Transfer of patent right |