CN105691599B - A kind of undercarriage disassembly and assembly structure of aircraft - Google Patents
A kind of undercarriage disassembly and assembly structure of aircraft Download PDFInfo
- Publication number
- CN105691599B CN105691599B CN201610036470.2A CN201610036470A CN105691599B CN 105691599 B CN105691599 B CN 105691599B CN 201610036470 A CN201610036470 A CN 201610036470A CN 105691599 B CN105691599 B CN 105691599B
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- CN
- China
- Prior art keywords
- undercarriage
- connecting seat
- assembly structure
- disassembly
- aircraft
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Abstract
The present invention relates to vehicle technology fields, disclose a kind of undercarriage disassembly and assembly structure of aircraft, include the connecting seat for being connect with aircraft, further include undercarriage and flexible limitation strip；Utilize this disassembly and assembly structure, quickly undercarriage and connecting seat can be clamped, under restriction effect of the limitation strip to undercarriage, clamping stability is good, when needing to remove undercarriage, pressing limitation strip, undercarriage is extracted out from connecting seat, to save space, is conducive to transportation and packaging, in conclusion this undercarriage disassembly and assembly structure has the advantages that be easy to dismounting, easy to assembly and exempt from dismantling device.
Description
Technical field
The present invention relates to vehicle technology field more particularly to a kind of undercarriage disassembly and assembly structures of aircraft.
Background technology
Now, with the progress of production and manufacturing technology, a large amount of small-sized unmanned aircraft is applied in every field, example
Such as：It takes photo by plane, detect and the application etc. of airhog, these unmanned vehicles include single rotor, more rotors and four-axle aircraft
Deng these usual aircraft only execute more single task, and landing weight is small, is adopted in the junction of undercarriage and fuselage
The strength demand of landing can be met by being attached with screw or screw, but this connection type is there is also larger deficiency, one,
Assembling is more troublesome；Two, not easy to assemble, to keep the volume of carrying larger；Three, dismounting is necessarily required to tool.In view of this, hair
A person of good sense has made improvement.
Invention content
In view of the above-mentioned deficiencies in the prior art, it is an object of the present invention to a kind of undercarriage disassembly and assembly structure of aircraft is provided, this
Disassembly and assembly structure has the advantages that be easy to dismounting, easy to assembly and exempt from dismantling device.
To achieve the above object, the undercarriage disassembly and assembly structure of a kind of aircraft of the invention, including be used to connect with aircraft
The connecting seat connect further includes undercarriage and flexible limitation strip, and the undercarriage is clamped with connecting seat, the limitation card
Between connecting seat and undercarriage, the limitation strip is provided with the fixed part being connect with connecting seat and rises and falls for limiting item
The limiting unit that frame is deviate from from connecting seat.
Further, the connecting seat is provided with accommodating position and the first slot positioned at accommodating position both sides, the undercarriage
It is provided with insertion section, the insertion section is clamped with the first slot.
Further preferably, the connecting seat is additionally provided with cutting, and the undercarriage is provided with the second slot, the cutting with
Second slot connects.
Further preferably, the inlet of the accommodating position is provided with occurs elastically-deformable deformation gap D for limitation strip.
Further preferably, the top surface of the accommodating position is that arcwall face or step settle face.
Further preferably, the top surface of the accommodating position is provided with positioning guide rail, and the limitation strip is provided with guide groove, described
Limitation strip is attached by the cooperation of guide groove and positioning guide rail with connecting seat.
Further, the connecting seat is provided with the jack being inserted into for fixed part.
Further preferably, the jack is circular hole, square hole or polygonal hole.
Further, the section of the limiting unit is triangular in shape, and the limiting unit is downwardly convex to abut to be formed with undercarriage
Limitation.
Further, the undercarriage includes transverse support bar and the vibration damping arm being connect with transverse support bar.
Beneficial effects of the present invention：Compared with prior art, the undercarriage disassembly and assembly structure of a kind of aircraft of the invention, packet
The connecting seat for being connect with aircraft is included, further includes undercarriage and flexible limitation strip；It, can using this disassembly and assembly structure
To be quickly clamped undercarriage and connecting seat, under restriction effect of the limitation strip to undercarriage, clamping stability is good,
When needing to remove undercarriage, undercarriage is extracted out from connecting seat, to save space, is conducive to by pressing limitation strip
Transportation and packaging, in conclusion this undercarriage disassembly and assembly structure has the advantages that be easy to dismounting, easy to assembly and exempt from dismantling device.
Description of the drawings
Fig. 1 is the attachment structure schematic diagram of the present invention and aircraft.
Fig. 2 is the structural exploded view of the present invention.
Fig. 3 is the structural schematic diagram of connecting seat of the present invention.
Fig. 4 is the connecting seat schematic diagram of the invention with arcwall face.
Fig. 5 is the connecting seat schematic diagram that the present invention settles face using step.
Fig. 6 is the structural schematic diagram of the undercarriage of the present invention.
Fig. 7 is the structural schematic diagram of the limitation strip of the present invention.
Reference numeral：
Connecting seat -- 1, house position -- 11, the first slot -- 12,
Cutting -- 13, arcwall face -- 141, step settles face -- and 142,
Positioning guide rail -- 15, jack -- 16, undercarriage -- 2,
Insertion section -- 21, the second slot -- 22, transverse support bar -- 23,
Vibration damping arm -- 24, limit strip -- 3, fixed part -- 31,
Limiting unit -- 32, guide groove -- 33.
Specific implementation mode
The present invention will be described in detail below in conjunction with the accompanying drawings.
Referring to Fig. 1 to Fig. 7, a kind of undercarriage disassembly and assembly structure of aircraft, includes the connecting seat for being connect with aircraft
1, further include undercarriage 2 and flexible limitation strip 3, the undercarriage 2 is clamped with connecting seat 1, the limitation strip 3
Between connecting seat 1 and undercarriage 2, the limitation strip 3 is provided with the fixed part 31 being connect with connecting seat 1 and for limiting
Fall the limiting unit 32 that frame 2 is deviate from from connecting seat 1.Limitation strip 3 is first stretched into connection by 2 disassembly and assembly structure of this undercarriage in assembling
Seat 1 is simultaneously connect with connecting seat 1, and undercarriage 2, which is then inserted into connecting seat 1, forms clamped condition, and the limitation strip 3 is in connection
Between seat 1 and undercarriage 2, connecting seat 1 can be respectively formed with undercarriage 2 and be abutted, make undercarriage 2, limitation strip 3 and connection
Close-fitting connection status is mutually formed between 1 three of seat, simultaneously with this, the limiting unit 32 forms undercarriage 2 and abuts, to limit
Undercarriage 2 processed is skidded off from connecting seat 1；Using this disassembly and assembly structure, quickly undercarriage 2 and connecting seat 1 can be clamped,
Strip 3 is limited under the restriction effect of undercarriage 2, clamping stability is good, when needing to remove undercarriage 2, pressing limits strip
3, undercarriage 2 is extracted out from connecting seat 1, to save space, is conducive to transportation and packaging, in conclusion this undercarriage
Disassembly and assembly structure has the advantages that be easy to dismounting, easy to assembly and exempt from dismantling device.
Specifically, the connecting seat 1 is provided with accommodating position 11 and the first slot 12 positioned at 11 both sides of accommodating position, it is described
Undercarriage 2 is provided with insertion section 21, and the insertion section 21 and the first slot 12 are clamped.When mounted, the insertion section 21 along
First slot 12 is inserted into, and entire insertion section 21 is located in accommodating position 11, and is formed under the action of limiting strip 3 and closely supported
It connects, this slide-in type connected structure is easy to operate.
Certainly, further preferably, the connecting seat 1 is additionally provided with cutting 13, and the undercarriage 2 is provided with the second slot
22, the cutting 13 is connect with the second slot 22.While insertion section 21 and the second 22 grafting of slot, the second slot 22 with insert
Item 13 also forms grafting, in this way, dual snapping is mutually formed between undercarriage 2 and connecting seat 1, during aircraft landing,
This dual snapping has higher stability, ensures being smoothed out for landing.
In the technical scheme, it when needing to remove undercarriage 2, needs limitation strip 3 to be compressed, brings it about shape
Become, further preferably, the inlet of the accommodating position 11 is provided with occurs elastically-deformable deformation gap D for limitation strip 3.It should
Deformation gap D can make limitation strip 3 when being compressed, and limiting unit 32 is moved along deformation gap D, the limiting unit 32 with
Undercarriage 2 detaches, and elimination skids off limitation to undercarriage 2.
So, the deformation gap D can be formed in the following way, one, the top surface of the accommodating position 11 be arcwall face
141（Referring to Fig. 4）, this arcwall face 141 is integrally formed using mold, simple and convenient, and strong applicability.Two, the appearance
The top surface of set 11 is that step settles face 142（Referring to Fig. 5）, the sedimentation face only with limiting unit 32 formed deformation gap D, this
Sample can preferably ensure to limit the contact area with bigger between strip 3 and connecting seat 1, make undercarriage 2, limitation strip 3
Being completely embedded property between 1 three of connecting seat is more preferable.
In the technical scheme, described as a further improvement, the top surface of the accommodating position 11 is provided with positioning guide rail 15
Limitation strip 3 is provided with guide groove 33, and the limitation strip 3 is carried out by the cooperation of guide groove 33 and positioning guide rail 15 with connecting seat 1
Connection.When mounted, the guide groove 33 and positioning guide shaft cooperation, so as to allow limitation strip 3 accurately to be carried out with connecting seat 1
Connection.
In the technical scheme, the connecting seat 1 is provided with the jack 16 being inserted into for fixed part 31, further, described
Jack 16 is circular hole, square hole or polygonal hole.Meanwhile the fixed part 31 may be set to be cylinder or polygon cylinder, pacify
When dress, fixed part 31, which is stretched into the jack 16, can form connection with connecting seat 1, convenient for disassembly and assembly.
In the technical scheme, the section of the limiting unit 32 is triangular in shape, the limiting unit 32 it is downwardly convex with rise and fall
Frame 2, which abuts, forms limitation；When dismantling undercarriage 2, limiting unit 32 is first pressed, the restriction cancellation of limiting unit 32 and undercarriage 2 is made
That is removably undercarriage 2, and when installing, bottom is slid into along limitation strip 3, undercarriage 2 can abut shape with limiting unit 32
At restriction effect.
In the technical scheme, the undercarriage 2 includes transverse support bar 23 and the vibration damping being connect with transverse support bar 23
Arm 24.For contacting to form supporting role with ground, the vibration damping arm 24 is blocked the transverse support bar 23 with connecting seat 1
It connects, the connecting seat 1 can be integrally formed with aircraft body, and to reduce assembly process, structure is compacter.
The above content is only presently preferred embodiments of the present invention, for those of ordinary skill in the art, according to the present invention
Thought, there will be changes in the specific implementation manner and application range, and the content of the present specification should not be construed as to the present invention
Limitation.
Claims (10)
1. a kind of undercarriage disassembly and assembly structure of aircraft includes the connecting seat (1) for being connect with aircraft, it is characterised in that：
Further include undercarriage (2) and flexible limitation strip (3), the undercarriage (2) is clamped with connecting seat (1), the limitation
Strip (3) is located between connecting seat (1) and undercarriage (2), and the limitation strip (3) is provided with consolidates with what connecting seat (1) was connect
The limiting unit (32) determined portion (31) and deviate from from connecting seat (1) for limiting undercarriage (2).
2. a kind of undercarriage disassembly and assembly structure of aircraft according to claim 1, it is characterised in that：The connecting seat (1)
It is provided with accommodating position (11) and the first slot (12) positioned at accommodating position (11) both sides, the undercarriage (2) is provided with insertion section
(21), the insertion section (21) is clamped with the first slot (12).
3. a kind of undercarriage disassembly and assembly structure of aircraft according to claim 2, it is characterised in that：The connecting seat (1)
It is additionally provided with cutting (13), the undercarriage (2) is provided with the second slot (22), and the cutting (13) connects with the second slot (22)
It connects.
4. a kind of undercarriage disassembly and assembly structure of aircraft according to claim 2, it is characterised in that：The accommodating position (11)
Inlet be provided with elastically-deformable deformation gap D occur for limitation strip (3).
5. a kind of undercarriage disassembly and assembly structure of aircraft according to claim 4, it is characterised in that：The accommodating position (11)
Top surface be that arcwall face (141) or step settle face (142).
6. a kind of undercarriage disassembly and assembly structure of aircraft according to claim 5, it is characterised in that：The accommodating position (11)
Top surface be provided with positioning guide rail (15), the limitation strip (3) is provided with guide groove (33), and the limitation strip (3) is by leading
Slot (33) and the cooperation of positioning guide rail (15) are attached with connecting seat (1).
7. a kind of undercarriage disassembly and assembly structure of aircraft according to claim 1, it is characterised in that：The connecting seat (1)
It is provided with the jack (16) being inserted into for fixed part (31).
8. a kind of undercarriage disassembly and assembly structure of aircraft according to claim 7, it is characterised in that：The jack (16) is
Circular hole or polygonal hole.
9. a kind of undercarriage disassembly and assembly structure of aircraft according to claim 1, it is characterised in that：The limiting unit (32)
Section it is triangular in shape, the limiting unit (32) is downwardly convex to abut formation limitation with undercarriage (2).
10. according to a kind of undercarriage disassembly and assembly structure of aircraft of claim 1~9 any one of them, it is characterised in that：It is described
Undercarriage (2) includes transverse support bar (23) and the vibration damping arm (24) being connect with transverse support bar (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610036470.2A CN105691599B (en) | 2016-01-20 | 2016-01-20 | A kind of undercarriage disassembly and assembly structure of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610036470.2A CN105691599B (en) | 2016-01-20 | 2016-01-20 | A kind of undercarriage disassembly and assembly structure of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105691599A CN105691599A (en) | 2016-06-22 |
| CN105691599B true CN105691599B (en) | 2018-10-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610036470.2A Active CN105691599B (en) | 2016-01-20 | 2016-01-20 | A kind of undercarriage disassembly and assembly structure of aircraft |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107416189B (en) * | 2017-07-26 | 2023-07-21 | 深圳市科卫泰实业发展有限公司 | Quick-assembly aircraft landing gear assembly |
| CN208181404U (en) * | 2018-04-24 | 2018-12-04 | 深圳市大疆创新科技有限公司 | Landing gear structure and unmanned plane |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2558425Y (en) * | 2002-08-16 | 2003-07-02 | 李晓阳 | Rubber-band propeller model aircraft |
| CN203638088U (en) * | 2013-10-24 | 2014-06-11 | 深圳一电科技有限公司 | Rotor craft |
| CN104527988A (en) * | 2014-12-16 | 2015-04-22 | 湖南基石信息技术有限公司 | Unmanned aerial vehicle |
| CN205469786U (en) * | 2016-01-20 | 2016-08-17 | 广东司马航模实业有限公司 | Undercarriage dismouting structure of aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202013012547U1 (en) * | 2012-11-15 | 2017-07-03 | SZ DJI Technology Co., Ltd. | Unmanned aerial vehicle with multiple rotors |
-
2016
- 2016-01-20 CN CN201610036470.2A patent/CN105691599B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2558425Y (en) * | 2002-08-16 | 2003-07-02 | 李晓阳 | Rubber-band propeller model aircraft |
| CN203638088U (en) * | 2013-10-24 | 2014-06-11 | 深圳一电科技有限公司 | Rotor craft |
| CN104527988A (en) * | 2014-12-16 | 2015-04-22 | 湖南基石信息技术有限公司 | Unmanned aerial vehicle |
| CN205469786U (en) * | 2016-01-20 | 2016-08-17 | 广东司马航模实业有限公司 | Undercarriage dismouting structure of aircraft |
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| Publication number | Publication date |
|---|---|
| CN105691599A (en) | 2016-06-22 |
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