CN108910016A - Quick Release wing and unmanned vehicle - Google Patents
Quick Release wing and unmanned vehicle Download PDFInfo
- Publication number
- CN108910016A CN108910016A CN201810812704.7A CN201810812704A CN108910016A CN 108910016 A CN108910016 A CN 108910016A CN 201810812704 A CN201810812704 A CN 201810812704A CN 108910016 A CN108910016 A CN 108910016A
- Authority
- CN
- China
- Prior art keywords
- wing
- pipe
- spacer pin
- quick release
- elastic component
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Handcart (AREA)
Abstract
The invention discloses a kind of Quick Release wing and unmanned vehicles.Quick Release wing includes the first wing module and the second wing module, is provided with hollow pipe in the first wing module, the limit channels for radially extending and penetrating through hollow pipe are provided on hollow pipe.It is provided with the installation axle with hollow pipe cooperation in second wing module, corresponds to limit channels in installation axle and is provided with limit hole.Quick Release wing further includes spacer pin and elastic component, and spacer pin is arranged in limit channels, and the first end of spacer pin extends to the outside of the first wing module；The lock position that spacer pin has the Quick Release position for overcoming elastic component elastic force to extract outward and resetted by elastic component driving.Quick Release wing, which is divided into two parts, can effectively reduce the span and occupied space of wing, facilitate storage and transport unmanned vehicle.Elastic component and spacer pin cooperation can guarantee the reliability of wing installation, while keep the dismantling of Quick Release wing more convenient.
Description
Technical field
The present invention relates to air vehicle technique field more particularly to a kind of Quick Release wings and unmanned vehicle.
Background technique
With the emergence of unmanned vehicle industry, unmanned vehicle is all widely used in all trades and professions.
In the prior art, it due to fixed-wing stability and structural strength is compared to rotor, has great advantages, unmanned plane
More and more using the aircraft of fixed-wing in industry, unmanned plane Fixed Wing AirVehicle also obtains the favor of more and more people.But
It is because unmanned plane Fixed Wing AirVehicle is sufficiently bulky, the span is very long, causes the packaging of aircraft and transport very inconvenient, to transport
Process brings very big difficulty.In the actual operation process, for rotor craft, the method generallyd use be by rotor from fly
It disassembles and is transported on row device；Rotor is reinstalled on aircraft again when use.And this method for fixed-wing it is winged simultaneously
It is not applicable.Therefore for Fixed Wing AirVehicle, it will usually which fixed-wing, i.e. the wing of aircraft is divided into two sections.Without using flight
When device, wing is dismantled into storage；When needing using aircraft, wing is re-assemblied, forms a complete wing.Mesh
The assembling mode of preceding use is usually to be assembled with bolt, screws on screw bolt and nut after wing is assembled and is fixed, should
Method requires to twist bolt and nut in each dismounting, causes dismounting inconvenient, reduces dismounting speed and efficiency.In addition, also
The method fastened using hardware hasp lock is arranged hasp lock in the outer surface of wing, buckles lock after being completed
Complete fastening.This method the problem is that, hasp lock is exposed in airfoil outer surface, will increase aerofoil surface resistance, while shadow
Ring wing appearance.
Summary of the invention
The big span length of wing volume in order to solve the Fixed Wing AirVehicle that above-mentioned background technique proposes causes to pack and transport
The problem of defeated difficulty, the present invention provides a kind of Quick Release wing and unmanned vehicles.
According to an aspect of the present invention, a kind of Quick Release wing, including the first wing module and the second wing module are provided,
It is provided with hollow pipe in first wing module, the limit channels for radially extending and penetrating through hollow pipe are provided on hollow pipe；The
The installation axle with hollow pipe cooperation is provided in two wing modules；Limit channels are corresponded in installation axle is provided with limit hole；Quick Release
Wing further includes spacer pin and elastic component, and spacer pin is set as passing through limit hole from limit channels, and the first end of spacer pin
Extend to the outside of the first wing module；Spacer pin has the Quick Release position for overcoming elastic component elastic force to extract outward and by elastic component
Drive the lock position resetted.
Preferably, limit channels include the first pipe extended to the first wing sidewalls direction, and hollow pipe is first
Perforation is correspondingly arranged at the position of pipeline connection, the second end of spacer pin runs through hollow pipe by perforation；Limit channels further include
It is arranged on the side wall of the first wing module, and the second pipe of corresponding first pipe setting, second pipe is by the first wing mould
The side wall of block extends to first pipe, and second pipe is formed with spacer pin entrance on the side wall of the first wing module.
Preferably, elastic component is between first pipe and second pipe, and is set on spacer pin；It is arranged on spacer pin
Have and removably support block, supports block between first pipe and elastic component；Elastic component is supported on supporting block, to drive limit
Position pin is reset to lock position.
Preferably, elastic component is spring.
Preferably, the first end of spacer pin is provided with stopper section, and the diameter of stopper section is greater than the diameter of spacer pin entrance.
Preferably, it is provided with pull ring on stopper section or stopper section is pull ring.
Preferably, it is additionally provided with positioning pipe in the first wing module, is provided with positioning pipe one by one in the second wing module
Corresponding locating shaft.
Preferably, positioning pipe at least there are two.
Preferably, the first wing module includes upper covering and lower covering, and upper covering and lower covering constitute accommodating cavity；First machine
Wing module further includes closing the end wall of accommodating cavity, is additionally provided with the reinforcing rib parallel with end wall in accommodating cavity, hollow pipe is by end wall
Reinforcing rib is extended to, and is formed with cooperation entrance on end wall.
According to another aspect of the present invention, a kind of unmanned vehicle is provided, unmanned vehicle includes main body, on main body
It is provided with the Quick Release wing of any of the above-described, the first wing module is fixedly connected on main body.
According to the technique and scheme of the present invention, the wing of large-scale unmanned plane is divided into two parts, the first wing module and second
Wing module, when installing wing, the installation axle of the second wing module is inserted into the hollow pipe of the first wing module, elastic component driving limit
Position pin passes through limit hole by limit channels and enters lock position, locks the first wing module and the second wing module, completes wing
Installation.When disassembling wing, spacer pin overcomes the elastic force of elastic component to exit limit hole by limit channels to enter Quick Release position, the second machine
Wing module is extracted from the first wing module, completes dismantling.Pass through the cooperation of elastic component and spacer pin, it is ensured that wing installation
Reliability, while keeping the dismantling of wing more convenient.When not using unmanned vehicle, wing is disassembled can be with for two parts
The span and occupied space for effectively reducing wing facilitate storage and transport unmanned vehicle.
Detailed description of the invention
Fig. 1 is that Quick Release wing provided in an embodiment of the present invention is completed structure chart；
Fig. 2 is the explosive view of Quick Release wing provided in an embodiment of the present invention；
Fig. 3 is the enlarged drawing in Fig. 2 at A；
Fig. 4 is that structure chart is completed in the spacer pin of Quick Release wing provided in an embodiment of the present invention and elastic component assembly.
Specific embodiment
In order to solve the technical issues of proposing in background technique, present inventor expects large-scale wing being divided into two
Part, two parts are cooperated and are fixed using attachment device when in use, attachment device are removed when not in use, by two
The extension set wing separates, and facilitates storage or transport.To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with
Attached drawing is described in further detail embodiments of the present invention.
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, Quick Release wing of the invention, including the first wing module 10 and the second wing
Module 20, the first wing module 10 and the assembling cooperation of the second wing module 20, form a complete wing.In order to guarantee first
Wing module 10 and the second wing module 20 have certain cooperation precision, and hollow pipe 13 is arranged in the first wing module 10,
The installation axle 21 cooperated with hollow pipe 13 is provided in second wing module 20.When assembling wing, installation axle 21 is inserted into hollow
In pipe 13, the assembling of the first wing module 10 and the second wing module 20 is completed.Quick Release wing is divided into two parts can be effective
The span and occupied space for reducing wing facilitate storage and transport unmanned vehicle.
In order to guarantee that the cooperation of hollow pipe 13 and installation axle 21 has certain stability, prevent installation axle 21 from deviating from hollow
Pipe 13 improves the reliability of Quick Release wing, and setting position-limit mechanism limits hollow shaft 21, is fixed on installation axle 21 hollow
In pipe 13.Setting radially extends and penetrates through the limit channels of hollow pipe 13, corresponding limit in installation axle 21 on hollow pipe 13
Limit hole 211 is arranged in channel.After the assembly is completed, limit hole 211 is connected to limit channels for installation axle 21 and hollow pipe 13.Quick Release machine
The wing further includes spacer pin 30 and elastic component 32, and the two is arranged in the first wing module 10.Specifically, the setting of spacer pin 30 exists
In limit channels, there is the Quick Release position for overcoming 32 elastic force of elastic component to extract outward and by the locking position of the driving reset of elastic component 32
It sets.In lock position, elastic component 32 provides elastic force to spacer pin 30, and spacer pin 30 is driven to pass through limit hole from limit channels
211, to limit the axial displacement of installation axle 21.Installation axle 21 is fixed relative to hollow pipe 13 at this time and can not move, Ke Yibao
It demonstrate,proves the first wing module 10 and stablizing for the second wing module 20 cooperates, improve the reliability of Quick Release wing.In Quick Release position, limit
Position pin 30 overcomes the elastic force of elastic component 32, moves along limit channels and exits limit hole 211, to release the axial direction to installation axle 21
The limitation of displacement, installation axle 21 can be extracted from hollow pipe 13, the first wing module 10 and the separation of the second wing module 20, complete
At the dismantling of Quick Release wing.Setting elastic component 32 and spacer pin 30 are cooperated, and elastic component 32 provides reliably to spacer pin 30
Elastic force, driving spacer pin 30 stablize the reliability that the assembling of Quick Release wing is further increased in lock position.In addition, user only needs
Overcome the elastic force of elastic component 32 that spacer pin 30 is made to retract Quick Release position, extracting installation axle 21 can be completed the dismantling of Quick Release wing,
It is simple and fast, improve the dismounting speed and efficiency of Quick Release wing.
In the present embodiment, it as shown in Figure 1, the first end of spacer pin 30 extends to the outside of the first wing module 10, uses
Family can apply active force in the first end of spacer pin 30, such as push or pull on the first end of spacer pin 30, make spacer pin 30 can
To overcome the elastic force of elastic component 32.That is, user can operate in the first end of spacer pin 30, make spacer pin 30 in Quick Release position
It sets and switches between lock position, carry out the dismounting of Quick Release wing.
First wing module 10 includes upper covering 11 and lower covering 12, and upper covering 11 and lower covering 12 cooperate, assembly
It is internal after the completion to form cavity, constitute the accommodating cavity of the first wing module 10.First wing module 10 further includes closing accommodating cavity
End wall 16, as shown in figure 3, end wall 16 is arranged in the mating surface of the first wing module 10, for connect upper covering 11 and under
Covering 12 simultaneously forms effectively closing.The reinforcing rib 17 parallel with end wall 16 is additionally provided in accommodating cavity, hollow pipe 13 is by end wall
16 extend to reinforcing rib 17, form cooperation entrance, on end wall 16 in order to the installation of installation axle 21.Reinforcing rib 17 and end wall 16
The both ends of hollow pipe 13 are supported, guarantee the stabilization of hollow pipe 13, while also effectively raising the intensity of hollow pipe 13.It needs
It is bright, in order to mitigate the weight of the first wing module 10, hollow design can be carried out on end wall 16 and reinforcing rib 17.
The opposite first wing module 10 of the second wing module 20 rotates in order to prevent, it is preferable that as shown in figure 3,
Positioning pipe 14 is additionally provided in first wing module 10, it is fixed correspondingly with positioning pipe 14 to be provided in the second wing module 20
Position axis 22.Positioning pipe 14 is formed with positioning entrance on end wall 16, and locating shaft 22 is assemblied in positioning pipe 14 from positioning entrance insertion
In, can limit the second wing module 20 can not rotate around the axis of installation axle 21, guarantee that the second wing module 20 installs when side
To correct, complete Quick Release wing is cooperatively formed with the first wing module 10.Meanwhile setting positioning pipe 14 and locating shaft 22 may be used also
To guarantee that the limit hole 211 of installation axle 21 is connected to limit channels, spacer pin 30 can accurately pass through installation axle 21 and hollow pipe
13, give full play to position-limiting action.Positioning pipe 14, which can be set one, also can be set two, and locating shaft 22 is also correspondingly arranged one
It is a or two.If a positioning pipe 14, positioning pipe 14 and 21 collective effect of installation axle is arranged, the second wing module 20 of limitation turns
Dynamic, installation axle 21 and hollow pipe 13 bear the effect of the axial moment of the second wing module 20 at this time.Two positioning pipes 14 are set,
The rotation of the second wing module 20 is limited by two positioning pipes 14, it is big that locating shaft 22 and positioning pipe 14 bear the second wing module 20
Partial axial moment reduces the axial moment effect of installation axle 21 and hollow pipe 13, and installation axle 21 and hollow can be improved
The reliability of pipe 13.Preferably, positioning pipe 14 is at least arranged two, and unequal feelings can be set into the caliber of positioning pipe 14
Condition, in order to distinguish during installation.It will be appreciated that the quantity of positioning pipe 14 and locating shaft 22 can also be according to Quick Release
The cross section size of wing is selected, and the present invention does not do specific requirement.
In the present embodiment, as shown in Figure 3 and Figure 4, limit channels include extending to 10 sidewall direction of the first wing module
First pipe 151, and the second pipe 152 being arranged on the side wall of the first wing module 10.Second pipe 152 and the first pipe
Road 151 is corresponding, and is extended from the side wall of the first wing module 10 to first pipe 151.Second pipe 152 is in the first wing module
Spacer pin entrance is formed on 10 side wall, the second end of spacer pin 30 is entered in limit channels by spacer pin entrance.Hollow pipe
13 are correspondingly arranged on perforation at the position that first pipe 151 connects, which runs through hollow along the movement routine of spacer pin 30
The tube wall of 13 opposite sides of pipe.The second end of spacer pin 30 enters perforation from first pipe 151, and passes through perforation through hollow
Pipe 13.The aperture of spacer pin entrance and the aperture of the perforation on hollow pipe 13 should be consistent with the diameter of axle of spacer pin 30, with branch
Support spacer pin 30.The aperture of first pipe 151 and second pipe 152 should be slightly bigger than the diameter of axle of spacer pin 30, to facilitate spacer pin
30 is mobile, quickly switches in Quick Release position and lock position.Certainly, tapered body, limit channels pair can be set in spacer pin 30
That answers is arranged to tapered channel, i.e., the aperture of limit channels by spacer pin entrance, along limit channels axis direction by
Decrescence small, the diameter of axle of spacer pin 30 is also gradually reduced since first end, along axis direction.It can be further improved limit in this way
The cooperation tightness of position pin 30 and limit channels, while spacer pin 30 can also be moved more easily in limit channels.
It is the form disconnected between first pipe 151 and second pipe 152, centre has certain accommodation space.Elasticity
Part 32 is arranged in the accommodation space, i.e. elastic component 32 is set in limit between first pipe 151 and second pipe 152
On the pin 30 of position.I.e. spacer pin 30 is inserted into second pipe 152 from spacer pin entrance, and forward movement is threaded through in elastic component 32, in turn
Run through hollow pipe 13 in into first pipe 151.It is provided on spacer pin 30 and removably supports block 33, support block 33 and elasticity
Part 32 cooperates, to drive spacer pin 30 to be reset to lock position.Specifically, supporting block 33 is located at first pipe 151 and bullet
Property part 32 between, elastic component 32 is supported on supporting block 33, by supporting block 33 to spacer pin 30 provide elastic force.Support block 33
It can be bolt, threaded hole 301 be correspondingly arranged on the corresponding position of spacer pin 30, bolt is matched with threaded hole 301 by screw thread
It closes, is mounted on spacer pin 30 or is disassembled from spacer pin 30 so that block 33 will be supported.To first be supported when installation block 33 from
It is removed on spacer pin 30, and elastic component 32 is fixed on preset position.Spacer pin 30 is inserted into from spacer pin entrance, is threaded through
In limit channels and elastic component 32, make threaded hole 301 between elastic component 32 and first pipe 151, then block 33 will be supported and pacified
It is filled on spacer pin 30, to complete the installation of elastic component 32 and spacer pin 30.Setting removably supports block 33, can be in bullet
It after spring failure, is replaced in time, guarantees the reliability of Quick Release wing installation.
To guarantee that elastic component 32 has certain elastic force, to drive spacer pin 30 to be in lock position, elastic component 32 it is initial
Length needs to be greater than or equal to the distance between first pipe 151 and second pipe 152.After installation is complete, elastic component 32 is
It is supported block 33 and second pipe 152 compresses, to have certain elastic force.In addition, the diameter of axle of elastic component 32 need to be with the second pipe
The wall thickness in road 152 is cooperated, i.e. the internal diameter of elastic component 32 is less than the outer diameter of second pipe 152, so that elastic component 32 can
It supports on the end face of second pipe 152, elastic component 32 can be effectively compressed by supporting block 33.It is of course also possible in bullet
Between property part 32 and second pipe 152 and elastic component 32 and supports and load onto elastomeric pad between block 33 respectively, as shown in figure 3,
So that elastic component 32 has effective supporting point, the counter-active effect of elastic force is given full play to.Preferably, elastic component 32 can select bullet
Spring or other can generate the mechanism of certain elastic force because of deformation occurs.It, can be accurate according to the stiffness factor of spring
Ground calculates the elastic force that spring has under certain deflection, and user can select suitable stiffness system according to the specific requirements of oneself
Number improves installation speed and efficiency to facilitate the installation of Quick Release wing.
After spacer pin 30 and elastic component 32 are installed, elastic component 32 is supported on supporting block 33, passes through the effect of elastic force
Make spacer pin 30 through hollow pipe 13, spacer pin 30 is located at lock position.That is, when spacer pin 30 is not by external force,
Positioned at lock position.When needing to install the second wing module 20, apply active force in the first end of spacer pin 30, will limit
Pin 30 pulls out, so that the second end of spacer pin 30 retreats in first pipe 151, is located at Quick Release position.Elastic component 32 is supported
Jacking block 33 is compressed to second pipe 152, generates elastic force, acting in opposition is on supporting block 33.Installation axle 21 is inserted at this time hollow
In pipe 13, and the active force in the first end for acting on spacer pin 30 is cancelled, spacer pin 30 being driven through in elastic force
Limit hole 211 and hollow pipe 13, are reset to lock position, and installation axle 21 is locked in hollow pipe 13.If desired second is dismantled
When wing module 20, equally apply active force in the first end of spacer pin 30, pulls out spacer pin 30 and make it into Quick Release
Position.Installation axle 21 is extracted at this time and cancels the active force on spacer pin 30, the disassembly of the second wing module 20 can be completed, letter
It is single quick.
Apply active force in the first end of spacer pin 30 for convenience, it is preferable that stop in the first end setting of spacer pin 30
Stopper 31, the diameter of stopper section 31 are greater than the diameter of spacer pin entrance.When spacer pin 30 is in lock position, stopper section 31 is hindered
For gear in spacer pin inlet, user can be by applying active force to stopper section 31.Stopper section 31 can be arranged to hexagon
Or other are convenient for the shape of applied force, facilitate the operation of user.It is specifically as follows, sets stopper section 31 to the shape of pull ring,
Or the pull ring of operation is convenient in setting on stopper section 31.
According to another aspect of the present invention, a kind of unmanned vehicle is provided, unmanned vehicle includes main body, on main body
It is provided with above-mentioned Quick Release wing.First wing module 10 of Quick Release wing is fixedly connected on main body, the second wing module
20 by 21 groups of the first wing of device modules 10 of installation axle for cooperating with hollow pipe 13.Unmanned vehicle when not in use, by
Two wing modules 20 remove, and reduce the volume and occupied space of unmanned vehicle, facilitate storage or transport.It needs to be flown with nobody
When row device, then the second wing module 20 loaded into use, it is simple and fast, facilitate operation.
In conclusion Quick Release wing of the invention is divided into two parts, the first wing module and the second wing module, fitting machine
When the wing, the installation axle of the second wing module is inserted into the hollow pipe of the first wing module, and elastic component drives spacer pin by limit channels
Enter lock position across limit hole, lock the first wing module and the second wing module, completes wing installation；Disassemble wing
When, spacer pin overcomes the elastic force of elastic component to exit limit hole by limit channels to enter Quick Release position, and the second wing module is from first
It is extracted in wing module, completes dismantling.Pass through the cooperation of elastic component and spacer pin, it is ensured that the reliability of wing installation, together
When keep the dismantling of wing more convenient.
The above description is merely a specific embodiment, under above-mentioned introduction of the invention, those skilled in the art
Other improvement or deformation can be carried out on the basis of the above embodiments.It will be understood by those skilled in the art that above-mentioned tool
Body description only preferably explains that the purpose of the present invention, protection scope of the present invention should be subject to the protection scope in claims.
Claims (10)
1. a kind of Quick Release wing, including the first wing module and the second wing module, which is characterized in that
Hollow pipe is provided in the first wing module, be provided on the hollow pipe radially extend and penetrate through it is described hollow
The limit channels of pipe；
The installation axle with hollow pipe cooperation is provided in the second wing module；The limit is corresponded in the installation axle
Channel is provided with limit hole；
The Quick Release wing further includes spacer pin and elastic component, and the spacer pin is set as passing through from the limit channels described
Limit hole, and the first end of the spacer pin extends to the outside of the first wing module；
The spacer pin, which has the Quick Release position for overcoming the elastic component elastic force to extract outward and driven by the elastic component, to be resetted
Lock position.
2. Quick Release wing according to claim 1, which is characterized in that
The limit channels include the first pipe extended to the first wing sidewalls direction, and the hollow pipe is described
Perforation is correspondingly arranged at the position of first pipe connection, the second end of the spacer pin is by the perforation through described hollow
Pipe；
The limit channels further include being arranged on the side wall of the first wing module, and correspond to the first pipe setting
Second pipe, the second pipe are extended from the side wall of the first wing module to the first pipe, the second pipe
Spacer pin entrance is formed on the side wall of the first wing module.
3. Quick Release wing according to claim 2, which is characterized in that
The elastic component is set on the spacer pin between the first pipe and second pipe；
Be provided on the spacer pin and removably support block, it is described support block be located at the first pipe and the elastic component it
Between；
The elastic component is supported to be supported on block described, to drive the spacer pin to be reset to the lock position.
4. Quick Release wing according to any one of claim 1 to 3, which is characterized in that
The elastic component is spring.
5. Quick Release wing according to claim 2, which is characterized in that
The first end of the spacer pin is provided with stopper section, and the diameter of the stopper section is greater than the diameter of the spacer pin entrance.
6. Quick Release wing according to claim 5, which is characterized in that
It is provided with pull ring on the stopper section or the stopper section is pull ring.
7. Quick Release wing according to claim 1, which is characterized in that
It is additionally provided with positioning pipe in the first wing module, is provided in the second wing module with the positioning pipe one by one
Corresponding locating shaft.
8. Quick Release wing according to claim 7, which is characterized in that
The positioning pipe at least there are two.
9. Quick Release wing according to claim 1, which is characterized in that
The first wing module includes upper covering and lower covering, and the upper covering and lower covering constitute accommodating cavity；Described first
Wing module further includes closing the end wall of the accommodating cavity, and the reinforcement parallel with the end wall is additionally provided in the accommodating cavity
Muscle, the hollow pipe extends to the reinforcing rib by the end wall, and cooperation entrance is formed on the end wall.
10. a kind of unmanned vehicle, which is characterized in that the unmanned vehicle includes main body,
The described in any item Quick Release wings of claim 1 to 9 are provided on the main body, the first wing module is fixed to be connected
It connects on the main body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810812704.7A CN108910016A (en) | 2018-07-23 | 2018-07-23 | Quick Release wing and unmanned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810812704.7A CN108910016A (en) | 2018-07-23 | 2018-07-23 | Quick Release wing and unmanned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108910016A true CN108910016A (en) | 2018-11-30 |
Family
ID=64415708
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810812704.7A Pending CN108910016A (en) | 2018-07-23 | 2018-07-23 | Quick Release wing and unmanned vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108910016A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110282113A (en) * | 2019-06-25 | 2019-09-27 | 西安爱生技术集团公司 | A kind of fast assembly and disassembly mechanism of unmanned plane Wing-fuselage |
| CN110920884A (en) * | 2019-12-05 | 2020-03-27 | 中国特种飞行器研究所 | Ground effect aircraft wing structure that can dismantle fast |
| CN112520011A (en) * | 2020-12-14 | 2021-03-19 | 中宇航通(北京)航空集团有限公司 | Quick-release quick-lock structure and method and unmanned aerial vehicle |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090302159A1 (en) * | 2007-01-16 | 2009-12-10 | Sagem Defense Securite | Aircraft Wing Including a Plurality of Dismountable Members |
| WO2016141742A1 (en) * | 2015-03-12 | 2016-09-15 | 杨华东 | Fixed-wing unmanned aircraft capable of being quickly disassembled and installed |
| CN106005369A (en) * | 2016-07-24 | 2016-10-12 | 尹鸿俊 | Unmanned aerial vehicle |
| CN107215451A (en) * | 2017-06-16 | 2017-09-29 | 中电科芜湖通用航空产业技术研究院有限公司 | A kind of wing attachment structure of general-purpose aircraft |
| CN207242001U (en) * | 2017-07-28 | 2018-04-17 | 中科机器人科技有限公司 | A kind of small drone wing Quick assembling-disassembling structure |
| CN207536118U (en) * | 2017-11-28 | 2018-06-26 | 天津天航智远科技有限公司 | A kind of small drone wing and fuselage fast assembling disassembling structure |
| CN208882098U (en) * | 2018-07-23 | 2019-05-21 | 上海歌尔泰克机器人有限公司 | Quick Release wing and unmanned vehicle |
-
2018
- 2018-07-23 CN CN201810812704.7A patent/CN108910016A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090302159A1 (en) * | 2007-01-16 | 2009-12-10 | Sagem Defense Securite | Aircraft Wing Including a Plurality of Dismountable Members |
| WO2016141742A1 (en) * | 2015-03-12 | 2016-09-15 | 杨华东 | Fixed-wing unmanned aircraft capable of being quickly disassembled and installed |
| CN106005369A (en) * | 2016-07-24 | 2016-10-12 | 尹鸿俊 | Unmanned aerial vehicle |
| CN107215451A (en) * | 2017-06-16 | 2017-09-29 | 中电科芜湖通用航空产业技术研究院有限公司 | A kind of wing attachment structure of general-purpose aircraft |
| CN207242001U (en) * | 2017-07-28 | 2018-04-17 | 中科机器人科技有限公司 | A kind of small drone wing Quick assembling-disassembling structure |
| CN207536118U (en) * | 2017-11-28 | 2018-06-26 | 天津天航智远科技有限公司 | A kind of small drone wing and fuselage fast assembling disassembling structure |
| CN208882098U (en) * | 2018-07-23 | 2019-05-21 | 上海歌尔泰克机器人有限公司 | Quick Release wing and unmanned vehicle |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110282113A (en) * | 2019-06-25 | 2019-09-27 | 西安爱生技术集团公司 | A kind of fast assembly and disassembly mechanism of unmanned plane Wing-fuselage |
| CN110920884A (en) * | 2019-12-05 | 2020-03-27 | 中国特种飞行器研究所 | Ground effect aircraft wing structure that can dismantle fast |
| CN110920884B (en) * | 2019-12-05 | 2024-01-12 | 中国特种飞行器研究所 | Quick detachable ground effect aircraft wing structure |
| CN112520011A (en) * | 2020-12-14 | 2021-03-19 | 中宇航通(北京)航空集团有限公司 | Quick-release quick-lock structure and method and unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN208882098U (en) | Quick Release wing and unmanned vehicle | |
| US11267556B2 (en) | Method of using a split winglet | |
| CN108910016A (en) | Quick Release wing and unmanned vehicle | |
| CN106541363B (en) | Locking nut tighten and back off tool | |
| CN109250067B (en) | Quick Release Wings and Unmanned Aerial Vehicles | |
| CN111824393B (en) | Aircraft main landing gear drag bracket spare parts assembly and related methods | |
| CN111824447B (en) | Aircraft wing and assembly method thereof | |
| CN210707854U (en) | Novel wing connection structure | |
| CN107010244B (en) | A kind of split type unmanned plane | |
| CN105275286B (en) | Pulled outside integrated car handle | |
| CA3021413A1 (en) | Tail tie-down | |
| CN202506125U (en) | Quick-dismounting structure for wings | |
| CN106828870A (en) | A kind of multi-rotor unmanned aerial vehicle | |
| CN205010465U (en) | Unmanned aerial vehicle | |
| CN204197267U (en) | A kind of fixed-wing unmanned plane body two sectional type rapid dismounting apparatus | |
| US12179906B2 (en) | Propeller provided with interchangeable blades and a method of mounting interchangeable blades on a propeller | |
| EP4223635A1 (en) | Compact propeller blade retention assembly | |
| US20230257103A1 (en) | Control surface support for an aircraft | |
| CN107074340B (en) | Rack connection component and unmanned vehicle for unmanned vehicle | |
| CN113002763B (en) | Aircraft subassembly with main landing gear assembly and tab | |
| CN114248946A (en) | Unmanned aerial vehicle helps and separating mechanism | |
| CN205891219U (en) | Foot rest mechanism and aircraft of aircraft | |
| CN223404401U (en) | A structure for quickly disassembling and assembling the main wing and fuselage of a model aircraft | |
| CN116142451B (en) | Unmanned aerial vehicle and rudder face dismouting structure | |
| US12050092B2 (en) | Mechanism for attachment and detachment of an airfoil to an airframe |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |