CN109850131A - A kind of unmanned plane undercarriage Quick-disassembling mechanism - Google Patents
A kind of unmanned plane undercarriage Quick-disassembling mechanism Download PDFInfo
- Publication number
- CN109850131A CN109850131A CN201910236755.4A CN201910236755A CN109850131A CN 109850131 A CN109850131 A CN 109850131A CN 201910236755 A CN201910236755 A CN 201910236755A CN 109850131 A CN109850131 A CN 109850131A
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- CN
- China
- Prior art keywords
- elastic component
- undercarriage
- upper casing
- unmanned plane
- insertion section
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Abstract
This application discloses a kind of unmanned plane undercarriage Quick-disassembling mechanism and unmanned plane, described undercarriage one end is equipped with insertion section, and the Quick-disassembling mechanism includes: upper casing, and the upper casing end face is equipped with through-hole corresponding with the insertion section；Lower casing is snapped together with the upper casing, can be rotated relative to the upper casing；First elastic component fastens in the space to be formed positioned at the upper casing and the lower casing, and one end is against on the upper casing, and the other end is against on the lower casing；Second elastic component is located in the space, is fixed on unmanned aerial vehicle body；When the insertion section, which passes through the through-hole, to be against on second elastic component, under the action of first elastic component and second elastic component, by the through-hole backstop after the insertion section rotation, to realize the fixation of the undercarriage Yu the fuselage；When rotating the upper casing to certain angle, the insertion section is deviate under the action of second elastic component from the through-hole, to realize the separation of the undercarriage Yu the fuselage.Entire mechanism keeps undercarriage disassembly simple, improves the disassembly efficiency of unmanned plane undercarriage, is readily transported.
Description
Technical field
This application involves unmanned plane field more particularly to a kind of undercarriage Quick-disassembling mechanisms.
Background technique
Now with the maturation of technology, the application range of unmanned plane constantly expands, and traditional unmanned plane undercarriage assembly is usual
It is to be fixed by screw, such fixed form causes undercarriage that cannot quickly disassemble and install, can not be according to using
It needs to be convenient for changing.Therefore, a kind of Quick-disassembling mechanism that can be used in unmanned plane undercarriage is designed, being that industry is urgently to be resolved asks
Topic.
Summary of the invention
The application provides a kind of unmanned plane undercarriage Quick-disassembling mechanism, and one end of mechanism is fixed on main support, the other end
By stirring rotation upper casing handle, undercarriage can be dismounted；The disassembly efficiency that can be improved unmanned plane undercarriage facilitates installation,
Facilitate dismantling, and adapts to the installation of a variety of undercarriages.In order to achieve the above object, the application provides the following technical solutions:
A kind of unmanned plane undercarriage Quick-disassembling mechanism, which is characterized in that described undercarriage one end is equipped with insertion section, the Quick Release
Mechanism includes: upper casing, and the upper casing end face is equipped with through-hole corresponding with the insertion section；Lower casing is fastened on the upper casing
Together, it can be rotated relative to the upper casing；First elastic component fastens in the space to be formed positioned at the upper casing and the lower casing,
One end is against on the upper casing, and the other end is against on the lower casing；Second elastic component is located in the space, is fixed on nobody
On machine fuselage；When the insertion section, which passes through the through-hole, to be against on second elastic component, in first elastic component and institute
Under the action of stating the second elastic component, by the through-hole backstop after the insertion section rotation, to realize the undercarriage and the machine
The fixation of body；When rotating the upper casing to certain angle, the insertion section is under the action of second elastic component from described logical
Hole abjection, to realize the separation of the undercarriage Yu the fuselage.
Further, the insertion section includes the protrusion being arranged above the undercarriage end, the through-hole include with
The corresponding long hole of the protrusion, when the insertion section, which passes through the through-hole, to be against on second elastic component, described first
Under the action of elastic component and second elastic component, the protrusion is by the through-hole backstop after the insertion section rotation.
Further, the upper casing, the lower casing are in hollow cylinder, are equipped in the lower casing and mutually fit with the first elastic component
The fixed part matched, and the first limiting slot compatible with the first elastic component；The lower casing is removably connected to by connector
Chassis.
Further, first elastic component is reduction torsion spring, and the torsional spring is placed on the fixed part.
Further, the upper casing and described consistent one end of undercarriage direction of insertion are equipped with handle；The upper casing bottom surface
Equipped with the second limiting slot compatible with the first elastic component.
Further, described shorter one end of first elastic component inserts in the first limiting slot；First elastic component is longer by one
End inserts in the second limiting slot.
Further, the mechanism further includes chassis, is removably connected to unmanned aerial vehicle body by connector.
Further, the upper casing and the lower casing are equipped with a becket, are removably connected to lower casing by connector, when
By the becket backstop when handle rotating down pressing, to realize the limit to the upper casing, the lower casing.
Further, the fixed part is equipped with jack compatible with the insertion section.
The application also provides a kind of unmanned plane, including undercarriage and fuselage, further includes above-mentioned unmanned plane undercarriage Quick Release
Mechanism, the undercarriage and the fuselage realize fixed and Quick Release by the unmanned plane undercarriage Quick-disassembling mechanism.
Compared with prior art, the beneficial effects of the present invention are: the present invention provides a kind of unmanned plane undercarriage Quick Release machines
Structure and unmanned plane containing this mechanism, the unmanned plane undercarriage Quick-disassembling mechanism includes upper casing, lower casing, the first elastic component, the second bullet
Property part, upper casing and lower casing be rotatablely connected, and undercarriage insertion section passes through upper casing through-hole and is against on the second elastic component, passes through external force
In upper casing, upper casing acts on the first elastic component, and the tight of limiting section can be automatically performed during the inserting of undercarriage and shell
Lock is fixed；Under the action of external force, the first elastic component and the second elastic component, after undercarriage can be detached from the position-limiting action of shell
Separation, whole process only with the hands achieve that the dismounting of unmanned aerial vehicle body and undercarriage；This programme facilitates installation, conveniently tears open
Solution, and the installation of a variety of undercarriages is adapted to, improve the disassembly efficiency of unmanned plane undercarriage.
Detailed description of the invention
In order to illustrate the technical solutions in the embodiments of the present application or in the prior art more clearly, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of application for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 is the explosive view of undercarriage installing mechanism provided by the embodiment of the present invention.
Fig. 2 is the sectional view of undercarriage installing mechanism provided by the embodiment of the present invention.
Fig. 3 is the torsional spring screenshot of undercarriage installing mechanism provided by the embodiment of the present invention.
Fig. 4 is the principle explanatory diagram of undercarriage installing mechanism provided by the embodiment of the present invention.
Fig. 5 is the scene application drawing of undercarriage installing mechanism provided by the embodiment of the present invention.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present application, technical solutions in the embodiments of the present application carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of embodiments of the present application, instead of all the embodiments.It is based on
Embodiment in the application, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall in the protection scope of this application.
It should also be noted that, herein, relational terms such as first and second and the like are used merely to one
Entity or operation are distinguished with another entity or operation, without necessarily requiring or implying between these entities or operation
There are any actual relationship or orders.Moreover, the terms "include", "comprise" or its any other variant are intended to contain
Lid non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also including other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.In the absence of more restrictions, the element limited by sentence "including a ...", it is not excluded that
There is also other identical elements in process, method, article or equipment including the element.
Fig. 1-Fig. 5, a kind of unmanned plane undercarriage Quick-disassembling mechanism are please referred to, 1 one end of undercarriage is equipped with insertion section 11, described fast
Tearing mechanism open includes: upper casing 2, and 2 end face of upper casing is equipped with through-hole 13 corresponding with the insertion section 11；Lower casing 5, on described
Shell 2 snaps together, and can be rotated relative to the upper casing 2；First elastic component 4 is located at the upper casing 2 and fastens with the lower casing 5
In the space of formation, one end is against on the upper casing 2, and the other end is against on the lower casing 5；Second elastic component 6 is located at the sky
In, it is fixed on unmanned aerial vehicle body；When the insertion section 11, which passes through the through-hole 13, to be against on second elastic component 6,
Under the action of first elastic component 4 and the second elastic component 6, the insertion section 11 is stopped after rotating by the through-hole 13
Gear, to realize the fixation of the undercarriage 1 and the fuselage；When rotating the upper casing 2 to certain angle, the insertion section is in institute
It states to deviate from from the through-hole 13 under the action of the second elastic component 6, to realize the separation of the undercarriage 1 and the fuselage.
Specifically, the insertion section 11 includes the protrusion being arranged above 1 end of undercarriage, the through-hole 13 includes
Long hole corresponding with the protrusion, when the insertion section 11, which passes through the through-hole 13, to be against 6 on second elastic component, in institute
Under the action of stating the first elastic component 4 and second elastic component 6, the insertion section 11 is described raised by the through-hole 13 after rotating
Backstop.
Specifically, the upper casing 2, the lower casing 5 are in hollow cylinder, it is equipped with and 4 phase of the first elastic component in the lower casing 5
The fixed part 9 of adaptation, and first limiting slot compatible with the first elastic component 4；The lower casing 5 is detachably connected by connector
It is connected to unmanned aerial vehicle body；The fixed part 9 is solid cylinder, jack compatible with undercarriage 1 is equipped with, under the jack is
Shell undercarriage through-hole.
Specifically, the upper casing 2 is equipped with handle 12 with the consistent one end of 1 direction of insertion of undercarriage；2 bottom of upper casing
Face is equipped with second limiting slot compatible with the first elastic component 4.
Specifically, first elastic component 4 is reduction torsion spring, the torsional spring is placed on the fixed part 9.First bullet
Property shorter one end of part 4 inserts in the first limiting slot；The longer one end of first elastic component 4 inserts in the second limiting slot.
Specifically, the mechanism further includes chassis 7, the chassis 7 is in disk form, is fixed on unmanned plane by connector 8
Organism bottom, second elastic component 6 are connected to chassis 7 by connector 8, and the lower casing 5 is connected to chassis by connector 8
7.Second elastic component 6 can be elastic slice.Above-mentioned connector 8 all can be bolted, so that it is detachable therebetween, with
Reach disassembly, replacement, technical effect easy to maintenance.
Specifically, being equipped with a becket 3 between the upper casing 2 and the lower casing 5, it is removably connected to by connector 8
Lower casing 5, when 12 rotating down pressing of handle by 3 backstop of becket, to realize the limit to the upper casing 2, the lower casing 5
Position.
Specifically, the undercarriage 1 can be fabricated to any appropriate shape using any materials in the prior art, it is
The weight for reducing unmanned plane body, promotes the power performance of unmanned plane, and undercarriage 1 can be used during carbon fibre material is fabricated to
Empty rod-like structure, or production become the rod-like structure for offering lightening hole.
Specifically, toggle handle 12 is rotated by 90 °, and the undercarriage jack of upper casing 2 is under at this time when assembly undercarriage 1
The undercarriage jack of shell 5 is alignment, assembles undercarriage 1, firmly lower to squeeze the second elastic component 6 by the bottom end of undercarriage 1, described
Second elastic component 6 can be elastic slice, and the plug-in unit 11 on undercarriage 1 does not interfere upper casing 2 to have rotated at this time；Then upper casing is decontroled
2 handle 12, upper casing 2 are rotated by 90 ° with the power of the second elastic component 4, are limited by becket 3, set back automatically, restore former
Behind position, the through-hole 13 and undercarriage 1 of upper casing 2 just limit 1 insertion section 11 of undercarriage, play fixed landing gear 1 at an angle of 90 degrees degree
Effect.
Specifically, disassembly undercarriage 1 and same principle, then toggle handle 12, it is rotated by 90 °, undercarriage 1 passes through bottom end
The second elastic component 6 elastic force, can automatic spring.
The application also provides a kind of unmanned plane, including undercarriage and fuselage, further includes above-mentioned unmanned plane undercarriage Quick Release
Mechanism, the undercarriage and the fuselage realize fixed and Quick Release by the unmanned plane undercarriage Quick-disassembling mechanism.
Above embodiments are only to illustrate the technical solution of the application, rather than its limitations；Although with reference to the foregoing embodiments
The application is described in detail, those skilled in the art should understand that: it still can be to aforementioned each implementation
Technical solution documented by example is modified or equivalent replacement of some of the technical features；And these modification or
Replacement, the spirit and scope of each embodiment technical solution of the application that it does not separate the essence of the corresponding technical solution.
Claims (10)
1. a kind of unmanned plane undercarriage Quick-disassembling mechanism, which is characterized in that described undercarriage one end is equipped with insertion section, the Quick Release machine
Structure includes:
Upper casing, the upper casing end face are equipped with through-hole corresponding with the insertion section；
Lower casing is snapped together with the upper casing, can be rotated relative to the upper casing；
First elastic component fastens in the space to be formed positioned at the upper casing and the lower casing, and one end is against on the upper casing, another
End is against on the lower casing；
Second elastic component is located in the space, is fixed on unmanned aerial vehicle body；
When the insertion section, which passes through the through-hole, to be against on second elastic component, in first elastic component and described second
Under the action of elastic component, by the through-hole backstop after the rotation of the insertion section, to realize consolidating for the undercarriage and the fuselage
It is fixed；When rotating the upper casing to certain angle, the insertion section is deviate under the action of second elastic component from the through-hole,
To realize the separation of the undercarriage Yu the fuselage.
2. unmanned plane undercarriage Quick-disassembling mechanism according to claim 1, which is characterized in that the insertion section is included in described
The protrusion being arranged above undercarriage end, the through-hole includes long hole corresponding with the protrusion, when the insertion section passes through institute
It is described to insert under the action of first elastic component and second elastic component when stating through-hole and being against on second elastic component
The protrusion is by the through-hole backstop after entering portion's rotation.
3. unmanned plane undercarriage Quick-disassembling mechanism according to claim 1, which is characterized in that the upper casing, the lower casing are in
Hollow cylinder, the lower casing is interior to be equipped with the fixed part compatible with the first elastic component, and compatible with the first elastic component
First limiting slot；The lower casing is removably connected to unmanned aerial vehicle body by connector.
4. unmanned plane undercarriage Quick-disassembling mechanism according to claim 1, which is characterized in that first elastic component is to reset
Torsional spring, the torsional spring are placed on the fixed part.
5. unmanned plane undercarriage Quick-disassembling mechanism according to claim 1, which is characterized in that the upper casing and the undercarriage
The consistent one end of direction of insertion is equipped with handle；The upper casing bottom surface is equipped with the second limiting slot compatible with the first elastic component.
6. unmanned plane undercarriage Quick-disassembling mechanism according to claim 4, which is characterized in that first elastic component is shorter by one
End inserts in the first limiting slot；Described longer one end of first elastic component inserts in the second limiting slot.
7. unmanned plane undercarriage Quick-disassembling mechanism according to claim 1, which is characterized in that the mechanism further includes chassis,
It is removably connected to unmanned aerial vehicle body by connector, second elastic component is located on the chassis.
8. unmanned plane undercarriage Quick-disassembling mechanism according to claim 1, which is characterized in that the upper casing and the lower casing it
Between be equipped with a becket, lower casing is removably connected to by connector, is stopped when the handle rotating down pressing by the becket
Gear, to realize the limit to the upper casing, the lower casing.
9. unmanned plane undercarriage Quick-disassembling mechanism according to claim 3, which is characterized in that the fixed part is equipped with and institute
State the compatible jack in insertion section.
10. a kind of unmanned plane, which is characterized in that further include any described nobody of claim 1-9 including undercarriage and fuselage
Machine undercarriage Quick-disassembling mechanism, the undercarriage and the fuselage are realized fixed and fast by the unmanned plane undercarriage Quick-disassembling mechanism
It tears open.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910236755.4A CN109850131A (en) | 2019-03-27 | 2019-03-27 | A kind of unmanned plane undercarriage Quick-disassembling mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910236755.4A CN109850131A (en) | 2019-03-27 | 2019-03-27 | A kind of unmanned plane undercarriage Quick-disassembling mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109850131A true CN109850131A (en) | 2019-06-07 |
Family
ID=66902133
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910236755.4A Pending CN109850131A (en) | 2019-03-27 | 2019-03-27 | A kind of unmanned plane undercarriage Quick-disassembling mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109850131A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115180125A (en) * | 2022-09-09 | 2022-10-14 | 致导创新(天津)科技有限公司 | Unmanned aerial vehicle foot rest connection structure |
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| CN105297853A (en) * | 2015-10-10 | 2016-02-03 | 厦门倍洁特建材有限公司 | Quick-installed joint structure |
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| CN206552247U (en) * | 2016-11-26 | 2017-10-13 | 山东天禧航空科技有限公司 | A kind of aircraft landing gear Quick Release connection component |
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| WO2018027685A1 (en) * | 2016-08-10 | 2018-02-15 | 张琬彬 | Cushioning leg support for small unmanned aerial vehicle |
| CN108583851A (en) * | 2018-06-29 | 2018-09-28 | 拓攻（南京）机器人有限公司 | A kind of Quick Release undercarriage and the multi-rotor unmanned aerial vehicle containing it |
| CN108820188A (en) * | 2018-06-20 | 2018-11-16 | 上海歌尔泰克机器人有限公司 | A kind of Quick-dismantle component and unmanned plane |
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- 2019-03-27 CN CN201910236755.4A patent/CN109850131A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173072A (en) * | 2015-07-23 | 2015-12-23 | 广州飞米电子科技有限公司 | Power device and aircraft |
| CN105297853A (en) * | 2015-10-10 | 2016-02-03 | 厦门倍洁特建材有限公司 | Quick-installed joint structure |
| WO2018027685A1 (en) * | 2016-08-10 | 2018-02-15 | 张琬彬 | Cushioning leg support for small unmanned aerial vehicle |
| CN206552247U (en) * | 2016-11-26 | 2017-10-13 | 山东天禧航空科技有限公司 | A kind of aircraft landing gear Quick Release connection component |
| CN106628125A (en) * | 2016-12-28 | 2017-05-10 | 中国航天电子技术研究院 | Quick-disassembling energy absorption undercarriage for multi-rotor unmanned aerial vehicle |
| CN107416189A (en) * | 2017-07-26 | 2017-12-01 | 深圳市科卫泰实业发展有限公司 | A kind of aircraft landing gear component of quick assembling |
| CN108820188A (en) * | 2018-06-20 | 2018-11-16 | 上海歌尔泰克机器人有限公司 | A kind of Quick-dismantle component and unmanned plane |
| CN108583851A (en) * | 2018-06-29 | 2018-09-28 | 拓攻（南京）机器人有限公司 | A kind of Quick Release undercarriage and the multi-rotor unmanned aerial vehicle containing it |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115180125A (en) * | 2022-09-09 | 2022-10-14 | 致导创新(天津)科技有限公司 | Unmanned aerial vehicle foot rest connection structure |
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Application publication date: 20190607 |