CN206750160U - A kind of quick-disassembly structure for being used for aircraft motor and blade - Google Patents
A kind of quick-disassembly structure for being used for aircraft motor and blade Download PDFInfo
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- CN206750160U CN206750160U CN201720314176.3U CN201720314176U CN206750160U CN 206750160 U CN206750160 U CN 206750160U CN 201720314176 U CN201720314176 U CN 201720314176U CN 206750160 U CN206750160 U CN 206750160U
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- blade
- self
- motor
- locking module
- locking
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- 230000000694 effects Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000002002 slurry Substances 0.000 description 3
- 229920002472 Starch Polymers 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 235000019698 starch Nutrition 0.000 description 2
- 230000002950 deficient Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a kind of for aircraft motor and the quick-disassembly structure of blade, including motor and the self-locking module corresponding with the cavity size shape of blade of blade, one and a spring, self-locking module is provided with a through hole, self-locking module is nested with the motor shaft of motor by its through hole set, and is fixed by screw and motor locking；Spring sets in the through hole of self-locking module and is nested with the motor shaft of motor；The cavity medial surface of blade is provided with convex clamping point, and the lateral surface of self-locking module is additionally provided with corresponding clip fastening slot structure, is connected between blade and self-locking module by corresponding convex clamping point and clip fastening slot structure.The utility model is rapidly assembled and disassembled by self-locking module to motor and blade, blade motor and blade in operation have self-locking so as to ensure safety, reliably, it is stable etc..The effect of Quick Release dismounting blade is can reach, reduces subsidiary operation time.Add the flexibility of the fastness of Quick Release blade fixed form, reliability and assembling.
Description
Technical field
Machinery equipment field is the utility model is related to, more particularly to it is a kind of for aircraft motor and the Quick Release of blade
Structure.
Background technology
In the prior art, it is general between the motor of unmanned plane and blade to be connected through a screw thread all using being threadedly coupled, due to
Blade at work, and by motor drive rotate, helicitic texture can cause blade in work run easily occur take off
Oar phenomenon, fastness is relatively low, and less important work efficiency is low.
Therefore, the prior art is defective, it is necessary to improve.
Utility model content
Technical problem to be solved in the utility model is：There is provided can with Quick Release and fast-assembling blade, blade fixed form
Fastness is strong, the quick-disassembly structure for being used for aircraft motor and blade that reliability is high and the flexibility of assembling is good.
The technical solution of the utility model is as follows：A kind of quick-disassembly structure for being used for aircraft motor and blade, including motor
And blade, in addition to a self-locking module corresponding with the cavity size shape of blade and a spring, it is logical that self-locking module is provided with one
Hole, self-locking module is nested with the motor shaft of motor by its through hole set, and is fixed by screw and motor locking；Spring
Set in the through hole of self-locking module and be nested with the motor shaft of motor；Also, the cavity medial surface of blade is provided with convex clamping point,
The lateral surface of self-locking module is additionally provided with corresponding clip fastening slot structure, between blade and self-locking module by corresponding convex clamping point and
Clip fastening slot structure is connected.
Applied to above-mentioned technical proposal, in the quick-disassembly structure of described motor and blade, the self-locking module is and blade
Cavity size shape corresponding to a cylindrical self-locking module, the clip fastening slot structure slips into buckle slot and convex clip including convex clamping point
Point clamping stopper.
Applied to above-mentioned technical proposal, in the quick-disassembly structure of described motor and blade, the cylindrical self-locking module
Lateral surface, which is uniformly distributed, is provided with three clip fastening slot structures, the cavity medial surface of the blade be provided with one-to-one three it is convex
Stuck point.
Using such scheme, the utility model is rapidly assembled and disassembled by self-locking module to motor and blade,
Blade motor and blade in operation have self-locking so as to ensure safety, reliably, it is stable etc..It can reach the effect of Quick Release dismounting blade
Fruit, reduce subsidiary operation time.Add the flexibility of the fastness of Quick Release blade fixed form, reliability and assembling.
Brief description of the drawings
Fig. 1 is Structure explosion diagram of the present utility model；
Fig. 2 is the structure chart of self-locking module in the utility model；
Fig. 3 starches schematic diagram for lock of the present utility model；
Fig. 4 starches schematic diagram for solution of the present utility model.
Embodiment
Below in conjunction with the drawings and specific embodiments, the utility model is described in detail.
A kind of quick-disassembly structure for being used for aircraft motor and blade is present embodiments provided, as shown in figure 1, motor and blade
Quick-disassembly structure includes motor 107 and blade 101, also, also includes self-locking module 105 and spring 106, self-locking module 105 and oar
The cavity size shape of leaf 101 is correspondingly arranged, and as illustrated in fig. 1 and 2, self-locking module is provided with a through hole 203, self-locking module 105
It is nested with the motor shaft 108 of motor 107 by the through hole 203 of its setting, and is locked by screw 103 and motor 107；
Also, the fixed placement of spring 103 is in the through hole 203 of self-locking module 105, also, spring 103 is equally also nested with motor 107
Motor shaft 108 on.
Also, the cavity medial surface of blade 101 is provided with convex clamping point 102, the lateral surface of self-locking module 105 is additionally provided with pair
The clip fastening slot structure 104 answered, pass through corresponding convex clamping point 102 and clip fastening slot structure 104 between blade 101 and self-locking module 105
It is connected.
The self-locking module is a cylindrical self-locking module corresponding with the cavity size shape of blade, as shown in Fig. 2 institute
State clip fastening slot structure and slip into buckle slot 202 and convex clamping point clamping stopper 201 including convex clamping point, in this way, when locking slurry, will be certainly
Lock module 105 is inserted in the cavity of blade 101, and the convex clamping point 102 of the cavity medial surface of blade 101 is along self-locking module lateral surface
Slip into convex clamping point to slip into buckle slot 202, and blade is rotated by turning right, blade compression spring 103 during slip, lead to
Cross the tension force of spring 103 and locked by the clamping of convex clamping point clamping stopper 201, so as to be starched up to lock, as shown in Figure 3.
When solving slurry, down press blade and carry out compression spring, and blade is rotated by turning left, leave its convex clamping point 102
Convex clamping point clamping stopper 201, and in the presence of the compressive tension of spring up, blade is separated with self-locking module, so as to
Reach solution slurry, as shown in Figure 4.
Or can be uniformly distributed in the lateral surface of the cylindrical self-locking module and be provided with three clip fastening slot structures, and
And the cavity medial surface of the blade is provided with three convex clamping points one by one, by designing three clamping keyed ends, can consolidate
Self-locking module is locked with blade, so that motor is locked with blade.
In this way, self-locking block the active force of neck and spring so as to ensured blade in work is run not take off oar.Motor
It is that fast quick-mounting oar is by being positioned by blade by motor shaft with blade quick-disassembly structure mode, pressing blade is under spring action
Knob certain angle and be self-locking on motor, similarly quickly unload oar be also exited under active force of the blade by pressing spring neck rotation
Turn an opposite angles, so as to which this operating process is exactly a kind of mode of self-locking and unblock.And oar is ensured by self-locking block enclosure wall
Leaf is more firm, and buckle is more solid.
The quick-disassembly structure mode of this motor and blade, the effect of Quick Release dismounting blade is can reach, when reducing less important work
Between.Add the fastness of Quick Release blade fixed form, reliability, and the flexibility of assembling.
Preferred embodiment of the present utility model is these are only, is not limited to the utility model, it is all in this practicality
All any modification, equivalent and improvement made within new spirit and principle etc., should be included in guarantor of the present utility model
Within the scope of shield.
Claims (3)
- It is 1. a kind of for aircraft motor and the quick-disassembly structure of blade, including motor and blade, it is characterised in that：Corresponding with the cavity size shape of blade a self-locking module and a spring, self-locking module is also provided with a through hole, Self-locking module is nested with the motor shaft of motor by its through hole set, and is fixed by screw and motor locking；Spring is arranged in the through hole of self-locking module and is nested with the motor shaft of motor；Also, the cavity medial surface of blade is provided with convex clamping point, the lateral surface of self-locking module is additionally provided with corresponding buckle slot knot Structure, it is connected between blade and self-locking module by corresponding convex clamping point and clip fastening slot structure.
- 2. the quick-disassembly structure of motor according to claim 1 and blade, it is characterised in that：The self-locking module is and blade Cavity size shape corresponding to a cylindrical self-locking module, the clip fastening slot structure slips into buckle slot and convex clip including convex clamping point Point clamping stopper.
- 3. the quick-disassembly structure of motor according to claim 2 and blade, it is characterised in that：The cylindrical self-locking module Lateral surface, which is uniformly distributed, is provided with three clip fastening slot structures, the cavity medial surface of the blade be provided with one-to-one three it is convex Stuck point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720314176.3U CN206750160U (en) | 2017-03-28 | 2017-03-28 | A kind of quick-disassembly structure for being used for aircraft motor and blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720314176.3U CN206750160U (en) | 2017-03-28 | 2017-03-28 | A kind of quick-disassembly structure for being used for aircraft motor and blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206750160U true CN206750160U (en) | 2017-12-15 |
Family
ID=60611670
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720314176.3U Active CN206750160U (en) | 2017-03-28 | 2017-03-28 | A kind of quick-disassembly structure for being used for aircraft motor and blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206750160U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108082479A (en) * | 2017-12-18 | 2018-05-29 | 中山市雅乐思商住电器有限公司 | A kind of portable agricultural formula unmanned plane |
| CN108454817A (en) * | 2018-03-07 | 2018-08-28 | 芜湖翼讯飞行智能装备有限公司 | A kind of unmanned plane rotor protective cover Fast Installation structure |
-
2017
- 2017-03-28 CN CN201720314176.3U patent/CN206750160U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108082479A (en) * | 2017-12-18 | 2018-05-29 | 中山市雅乐思商住电器有限公司 | A kind of portable agricultural formula unmanned plane |
| CN108454817A (en) * | 2018-03-07 | 2018-08-28 | 芜湖翼讯飞行智能装备有限公司 | A kind of unmanned plane rotor protective cover Fast Installation structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 518000, 1st Floor, 16th Building, Zhiheng Industrial Park, Nantou Street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Shenzhen Pegasus Robotics Co.,Ltd. Country or region after: China Address before: 518000, 1st Floor, 16th Building, Zhiheng Industrial Park, Nantou Street, Nanshan District, Shenzhen City, Guangdong Province Patentee before: SHENZHEN FEIMA ROBOTICS Co.,Ltd. Country or region before: China |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 518000, 13th Floor, Building A4, Nanshan Zhiyuan, No. 1001 Xueyuan Avenue, Changyuan Community, Taoyuan Street, Nanshan District, Shenzhen, Guangdong Province Patentee after: Shenzhen Pegasus Robotics Co.,Ltd. Country or region after: China Address before: 518000, 1st Floor, 16th Building, Zhiheng Industrial Park, Nantou Street, Nanshan District, Shenzhen City, Guangdong Province Patentee before: Shenzhen Pegasus Robotics Co.,Ltd. Country or region before: China |