CN208897306U - Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure - Google Patents
Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure Download PDFInfo
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- CN208897306U CN208897306U CN201821604729.XU CN201821604729U CN208897306U CN 208897306 U CN208897306 U CN 208897306U CN 201821604729 U CN201821604729 U CN 201821604729U CN 208897306 U CN208897306 U CN 208897306U
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- fuselage
- fast assembling
- spring catch
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Abstract
The utility model discloses a kind of unmanned aerial vehicle bodies and wing fast assembling-disassembling connection structure, belong to air vehicle technique field, assemble and dismantle solving the problems, such as unmanned plane in the prior art there are fuselage and wing and is slower.Unmanned aerial vehicle body described in the utility model and wing fast assembling-disassembling connection structure, including fuselage and wing, the fuselage and wing are detachably linked by bindiny mechanism, the bindiny mechanism includes the first connector and the second connector, it is provided with slot on the first connector, is provided with inserted block on the second connector；It is provided with spring catch on first connector, pin hole is provided on inserted block.The utility model is by using corresponding mating structure, fast assembling-disassembling is carried out by spring catch simultaneously, in disassembly process, it only needs to lift corresponding spring catch and carries out corresponding mating, the dismounting speed between unmanned plane wing and fuselage can be greatlyd improve, realizes the technical effect of fast assembling-disassembling.
Description
Technical field
The utility model relates to air vehicle technique fields more particularly to a kind of unmanned aerial vehicle body to connect with wing fast assembling-disassembling
Structure.
Background technique
In recent years, with the fast development of domestic fixed wing unmanned aircraft, unmanned aerial vehicle is in the task of execution, especially field
When execution task, it is desirable that quick assembly and disassembly can be carried out to unmanned plane, it is ensured that execute the timeliness of task.Fixed-wing nobody
Aircraft product itself is more complicated, and fuselage and wing are generally attached assembling, therefore its group with attachment screw and by tool
ETL estimated time of loading is relatively long, is unfavorable for fast assembling-disassembling.
Utility model content
The utility model solve the technical issues of be: existing unmanned plane, fuselage and wing assemble and dismantle compared with
Slow problem.
The technical scheme adopted by the utility model to solve the technical problem is as follows: unmanned aerial vehicle body and wing fast assembling-disassembling connect
Binding structure, including fuselage and wing, the fuselage and wing are detachably linked by bindiny mechanism, and the bindiny mechanism includes the
A connection piece and the second connector, first connector are fixedly installed on fuselage, and second connector is fixedly installed on
On wing, it is provided with slot on the first connector, inserted block is provided on the second connector, the inserted block and the slot are inserted
Connect cooperation；Spring catch is provided on first connector, one end of the spring catch is lift end, the other end of spring catch
It extends telescopically into the slot；It is provided with pin hole on inserted block, is extend into slot on the pin hole and spring catch
One end is mating.
Further, first connector and the second connector are metalwork.
Further, first connector is embedded on fuselage, second connector is fixedly mounted by screw
On wing.
Further, the lift end in spring catch is provided with pull ring.
It is installed on the first connector further, the spring catch is connected through a screw thread.
Further, first connector and the second connector exchange installation site: first connector is fixed
It is set on wing, second connector is fixedly installed on fuselage.
Further, single wing is connect by least two groups bindiny mechanism with fuselage.
The beneficial effects of the utility model are:, by using corresponding mating structure, being borrowed simultaneously in the utility model
Spring catch is helped to carry out fast assembling-disassembling, in disassembly process, it is only necessary to lift corresponding spring catch and carry out corresponding mating
, the dismounting speed between unmanned plane wing and fuselage can be greatlyd improve, realizes the technical effect of fast assembling-disassembling.
Detailed description of the invention
Fig. 1 is the schematic diagram of unmanned aerial vehicle body described in the utility model and wing fast assembling-disassembling connection structure；
Fig. 2 is the schematic diagram of bindiny mechanism；
Fig. 3 is the perspective view of the explosion of bindiny mechanism；
Fig. 4 is the schematic diagram of spring catch under natural conditions；
Fig. 5 is the schematic diagram when lift end of spring catch is pulled up；
In the figure, it is marked as fuselage 1, wing 2, the first connector 3, the second connector 4, slot 5, inserted block 6, spring catch 7, pin
Hole 8, pull ring 9.
Specific embodiment
The present invention will be further described below with reference to the accompanying drawings and specific embodiments.
Unmanned aerial vehicle body described in the utility model and wing fast assembling-disassembling connection structure as shown in Fig. 1 to Fig. 5, including
Fuselage 1 and wing 2, the fuselage 1 and wing 2 are detachably linked by bindiny mechanism, and the bindiny mechanism includes the first connection
Part 3 and the second connector 4, first connector 3 are fixedly installed on fuselage 1, and second connector 4 is fixedly installed on machine
On the wing 2, it is provided with slot 5 on the first connector 3, inserted block 6 is provided on the second connector 4, the inserted block 6 is inserted with described
Slot 5 is mating；Spring catch 7 is provided on first connector 3, one end of the spring catch 7 is lift end, spring catch
7 other end extends telescopically into the slot 5；Be provided with pin hole 8 on inserted block 6, the pin hole 8 on spring catch 7
The one end extending into slot 5 is mating.
After bindiny mechanism described in the utility model, the installation process between fuselage 1 and wing 2 is as follows: firmly mentioning
Then machine will be installed on so that one end that spring catch 7 is extend into slot 5 is retracted out of slot 5 by drawing the lift end of spring catch 7
The inserted block 5 of the second connector 4 on the wing 2 is inserted into the slot 5 of the first link block 3 of installation on the fuselage 1 with merging alignment；
Spring catch 7 is unclamped again after alignment, makes that spring catch 7 extend into one end in slot 5 and the pin hole 8 on inserted block 6 is mating, in turn
Realize that positioning is fixed；So far the Fast Installation between fuselage 1 and wing 2 is completed.Corresponding disassembly process then only needs firmly to mention
The lift end of spring catch 7 is drawn, then directly removes wing 2；It is very convenient.
More specifically, in the utility model, the first connector 3 and the second connector 4 are due to needing to guarantee fuselage 1 and wing
2 structural strengths for effectively connecting and connecting, therefore further preferably first connector 3 and the second connector 4 are metal
Part, to guarantee the structural strength of the part；The higher metal of structural strength should be used using metalwork, for example, by using high intensity
Stainless steel material or aluminum alloy materials of aviation grade etc..
More specifically, further that the first connector 3 is embedded on the fuselage 1 in the utility model；Specifically, then can be in machine
Corresponding position is provided with mounting groove on body 1, and then the first connector 3 is installed in the mounting groove；Certainly, the first connector 3
On slot 5 should be located at fuselage 1 on and wing 2 be cooperatively connected end face in.And for the second connector 4, then it can pass through spiral shell
Nail is fixedly mounted on wing 2, while the end face for making inserted block 6 be cooperatively connected from wing 2 with fuselage 1 is protruded, so as to 6 energy of inserted block
It is conveniently plugged into the slot 5 of corresponding first connector 3.
In addition, the spring catch 7 in the utility model, can be used threaded connection and is installed on corresponding first connector 3,
After spring catch 7 is by applying corresponding lifting effect to its lift end, the one end protruded into slot 5 can be stretched,
It is as shown in Fig. 4 spring catch 7 under natural conditions, and is then the shape when lift end applies lifting effect shown in attached drawing 5
State.More specifically, for the ease of exerting a force to lift end, the utility model is further provided with pull ring in the lift end of spring catch 7
9。
Without loss of generality, bindiny mechanism described in the utility model, can be by the first connector 3 and the second connector 4
First connector 3, i.e., be fixedly installed on wing 2, second connector 4 be fixedly installed on by installation site exchange
On the fuselage 1.Theoretically, substantive shadow is not generated to the connection effect between fuselage 1 and wing 2 after exchanging installation site
It rings, therefore the fast assembling-disassembling effect being also able to achieve between fuselage 1 and wing 2.
It is attached in addition, may be provided at least two groups bindiny mechanism for single wing 2 in the utility model.Such as attached drawing
Shown in 1, Liang Zu bindiny mechanism is as provided with for single wing 2 to be attached installation with fuselage 1.
Claims (7)
1. unmanned aerial vehicle body and wing fast assembling-disassembling connection structure, including fuselage (1) and wing (2), it is characterised in that: the machine
Body (1) and wing (2) are detachably linked by bindiny mechanism, and the bindiny mechanism includes the first connector (3) and the second connection
Part (4), first connector (3) are fixedly installed on fuselage (1), and second connector (4) is fixedly installed on wing (2)
On, it is provided with slot (5) on the first connector (3), is provided on the second connector (4) inserted block (6), the inserted block (6)
It is mating with the slot (5)；It is provided with spring catch (7) on first connector (3), the one of the spring catch (7)
End is lift end, and the other end of spring catch (7) extends telescopically into the slot (5)；Pin hole is provided on inserted block (6)
(8), the one end extending into slot (5) on the pin hole (8) and spring catch (7) is mating.
2. unmanned aerial vehicle body as described in claim 1 and wing fast assembling-disassembling connection structure, it is characterised in that: described first connects
Fitting (3) and the second connector (4) are metalwork.
3. unmanned aerial vehicle body as described in claim 1 and wing fast assembling-disassembling connection structure, it is characterised in that: described first connects
Fitting (3) is embedded on fuselage (1), and second connector (4) is fixedly mounted on wing (2) by screw.
4. unmanned aerial vehicle body as described in claim 1 and wing fast assembling-disassembling connection structure, it is characterised in that: in spring catch
(7) lift end is provided with pull ring (9).
5. unmanned aerial vehicle body as described in claim 1 and wing fast assembling-disassembling connection structure, it is characterised in that: the spring catch
(7) it is connected through a screw thread and is installed on the first connector (3).
6. unmanned aerial vehicle body as described in claim 1 and wing fast assembling-disassembling connection structure, it is characterised in that: described first connects
Fitting (3) and the second connector (4) exchange installation site: first connector (3) is fixedly installed on wing (2), described
Second connector (4) is fixedly installed on fuselage (1).
7. unmanned aerial vehicle body and wing fast assembling-disassembling connection structure as described in any one of claim 1 to 6, feature exist
In: single wing (2) is connect by least two groups bindiny mechanism with fuselage (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821604729.XU CN208897306U (en) | 2018-09-29 | 2018-09-29 | Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821604729.XU CN208897306U (en) | 2018-09-29 | 2018-09-29 | Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208897306U true CN208897306U (en) | 2019-05-24 |
Family
ID=66574419
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821604729.XU Active CN208897306U (en) | 2018-09-29 | 2018-09-29 | Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure |
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| CN (1) | CN208897306U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588947A (en) * | 2019-10-11 | 2019-12-20 | 成都纵横大鹏无人机科技有限公司 | Connection structure and unmanned aerial vehicle |
| WO2021078265A1 (en) * | 2019-10-23 | 2021-04-29 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN113899252A (en) * | 2021-10-21 | 2022-01-07 | 上海机电工程研究所 | Connecting device for missile wing and missile body and missile |
| CN114455064A (en) * | 2022-01-25 | 2022-05-10 | 航天时代飞鸿技术有限公司 | Locking device and unmanned aerial vehicle |
| US20220234717A1 (en) * | 2019-09-05 | 2022-07-28 | Autel Robotics Co., Ltd. | Wing detachment assembly and aerial vehicle |
-
2018
- 2018-09-29 CN CN201821604729.XU patent/CN208897306U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220234717A1 (en) * | 2019-09-05 | 2022-07-28 | Autel Robotics Co., Ltd. | Wing detachment assembly and aerial vehicle |
| CN110588947A (en) * | 2019-10-11 | 2019-12-20 | 成都纵横大鹏无人机科技有限公司 | Connection structure and unmanned aerial vehicle |
| WO2021078265A1 (en) * | 2019-10-23 | 2021-04-29 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN113899252A (en) * | 2021-10-21 | 2022-01-07 | 上海机电工程研究所 | Connecting device for missile wing and missile body and missile |
| CN114455064A (en) * | 2022-01-25 | 2022-05-10 | 航天时代飞鸿技术有限公司 | Locking device and unmanned aerial vehicle |
| WO2023142702A1 (en) * | 2022-01-25 | 2023-08-03 | 航天时代飞鸿技术有限公司 | Locking device and unmanned aerial vehicle |
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