CN207791128U - A kind of small drone wing Quick assembling-disassembling structure - Google Patents
A kind of small drone wing Quick assembling-disassembling structure Download PDFInfo
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- CN207791128U CN207791128U CN201720940545.XU CN201720940545U CN207791128U CN 207791128 U CN207791128 U CN 207791128U CN 201720940545 U CN201720940545 U CN 201720940545U CN 207791128 U CN207791128 U CN 207791128U
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- wing
- girder
- fuselage
- carbon pipe
- auxiliary girder
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
A kind of small drone wing Quick assembling-disassembling structure, including wing, wing girder, wing auxiliary girder, fuselage, fuselage girder, fuselage auxiliary girder, screw, it is characterized in that：The wing does exterior skin by composite material, is internally provided with reinforcing rib, and wing includes wing girder, wing auxiliary girder, and wing girder is run through by a carbon pipe, and wing auxiliary girder uses the carbon pipe of one section of 200mm；The fuselage equally does exterior skin by composite material, is internally provided with reinforcing rib, which includes fuselage girder, fuselage auxiliary girder, and is respectively run through using a carbon pipe；The fuselage girder, fuselage auxiliary girder are equipped with the hole for fixing the screw；It is connected by above-mentioned carbon pipe between the fuselage and wing.The structure easy disassembly, it is easy to carry, it is light-weight, built-up time is drastically reduced, unmanned plane is made to rapidly enter working condition.
Description
Technical field
The present invention relates to the technical field of structures of unmanned plane, and in particular to a kind of quick peace speed of small drone wing is torn open
Unload structure.
Background technology
Currently, unmanned plane be it is a kind of by radio robot or itself program control its fly it is unpiloted
Flight equipment, it comes across earliest in the 1920s, the target drone as training used at that time, and the purposes of unmanned plane is very wide
General and cost is relatively low, during use, casualties situation will not occurs encountering unexpected.The survival ability of unmanned plane
By force, mobility is good, easy to use, there is extremely important effect in modern war, or even also possesses in civil field wide
Foreground.
Due to the light weight of small drone, it can case take away at any time, so needing fuselage energy quickly attaching and fractionation, together
It is also to take into account wing to have enough installation strengths, otherwise accident occurs in unmanned plane, causes economic loss.
Utility model content
Technical problem to be solved in the utility model is to overcome existing defect, provides a kind of small drone wing
Structure quickly is disconnected, its technical solution is as follows.
A kind of small drone wing quickly disconnects structure, including wing, wing girder, wing auxiliary girder, fuselage, fuselage
Girder, fuselage auxiliary girder, screw, it is characterized in that：The fuselage does exterior skin by composite material, is internally provided with reinforcing rib, the machine
Body includes fuselage girder, fuselage auxiliary girder, and is respectively run through using a carbon pipe；The wing equally does outer illiteracy by composite material
Skin is internally provided with reinforcing rib, and wing includes wing girder, wing auxiliary girder, and wing girder is run through by a carbon pipe, and wing auxiliary girder is adopted
With the carbon pipe of one section of 200mm；The fuselage girder, fuselage auxiliary girder are equipped with the hole for fixing the screw；The fuselage with
It is connected by above-mentioned carbon pipe between wing.
Preferably：The carbon pipe outside diameter of the fuselage girder is 14mm, and the carbon pipe outside diameter of internal diameter 12mm, wing girder are
12mm, internal diameter 10mm, fuselage auxiliary girder outer diameter are 8mm, and internal diameter 6mm, wing auxiliary girder outer diameter is 6mm, internal diameter 4mm.
Preferably：It is described fuselage girder carbon Guan Shangshe there are one a diameter of 3mm hole, apart from fuselage edge 30mm away from
From；Wing girder stretches out wing 100mm, and a diameter of 3mm is arranged in the position for the top 70mm that distance is stretched out on wing girder
Hole.
Advantageous effect：Its easy disassembly, it is easy to carry, built-up time is drastically reduced, unmanned plane is made to rapidly enter work
Make state, only needs a screw in entire assembling and dissembling process, you can realize locking.After fuselage and wing are finished, need to only it match
A screw hole is made a call to, fuselage wing can realize grafting, and processing is simple, and hole position is accurate.
Description of the drawings
Fig. 1 is the structural schematic diagram that the utility model wing and fuselage disconnect.
Wherein：1 is fuselage, and 2 be fuselage girder carbon pipe, and 3 be fuselage auxiliary girder carbon pipe, and 4 be M3 screws, and 5 be wing girder carbon
Pipe, 6 be wing auxiliary girder carbon pipe, and 7 be wing
Specific implementation mode
Unmanned plane includes fuselage, both sides wing group, tail supporting rod, empennage group.Wing group includes two wings, respectively in fuselage
The both sides of front end, empennage group is in the end of tail supporting rod.The light weight of small drone, so most of multiple using glass fibre etc.
Condensation material makes, and wing is also to have added reinforced structure in this way, because wing desired strength is relatively high in inside, strengthened knot
Structure includes piece auxiliary girder of reinforcing rib and a girder, and the Quick assembling-disassembling structure that we do is exactly on girder.
The composition of wing is to do exterior skin by composite material, and reinforcing rib is done in inside, in order to ability cost is saved, in addition wing
Section it is larger, so primary structure beam runs through wing using one whole carbon pipe inside wing, the carbon pipe outside diameter of fuselage girder is
The carbon pipe outside diameter of 14mm, internal diameter 12mm, wing girder are 12mm, and internal diameter 10mm, fuselage auxiliary girder outer diameter is 8mm, internal diameter 6mm, machine
Wing auxiliary girder outer diameter is 6mm, and internal diameter 4mm could realize grafting in this way.
Because of the no locking device of connection after grafting, using screw lock, beaten on the girder carbon pipe of fuselage
The hole of one a diameter of 3mm, the distance apart from fuselage edge 30mm.The girder of wing will be plugged in fuselage, so wing master
Beam will stretch out wing 100mm, the position of the top 70mm that equally distance is stretched out on the girder that wing stretches out make a call to one it is a diameter of
The hole of 3mm, could realization screw lock in this way after grafting.
Embodiment 1：
The girder of wing is generally made at the peak of airfoil lift face, and auxiliary girder is made in probably away from up-front 50%-70%'s
Within the scope of one, need to depend on the circumstances.The girder of same fuselage and auxiliary girder position, be with the girder of wing and the position of auxiliary girder
Corresponding ability grafting is entered.So the carbon pipe of the carbon pipe of outer diameter 14mm and outer diameter 8mm is made the required length of fuselage.
Equally, wing girder and auxiliary girder are also that carbon pipe is directly made in the inside, the carbon pipe of wing girder outer diameter 12mm, machine
Wing auxiliary girder makes the length as wing with the carbon pipe of 6mm.Since the shape of wing has different samples on different types
Formula, so the shape of the wing of this diagram is trapezoidal, (right side in Fig. 1) air-foil is narrower more outward, so wing
Auxiliary girder can not make whole, so one section can only be made, herein using the carbon pipe of overall length 200mm, half is made in wing
Inside, half are exposed.
Mating after fuselage and wing are finished, after having worked good, in open locking screw hole, screw hole is opened in
On girder apart from fuselage outer 30mm, seen if pulled out, exactly it is opened in the exposed carbon pipe distance top outside of wing girder
On the position for holding 70mm.
It is waited when mounted after finishing in this way, only need to can complete to connect to inserting, be then directly inserted in hole with a screw
Achieve the purpose that locking, prevents wing from deviating from.
It is noted here that when carrying out wing punching, it is accurate that the cooperation of hole position is had to, and otherwise hole position is inaccurate, screw
It inserts not enter.
Many details are elaborated in the above description in order to fully understand the utility model.But above description
Only it is the preferred embodiment of the utility model, the utility model can be much to come different from other manner described here
Implement, therefore the utility model is not limited by specific implementation disclosed above.Any those skilled in the art exist simultaneously
It does not depart under technical solutions of the utility model ambit, it is all new to this practicality using the methods and technical content of the disclosure above
Type technical solution makes many possible changes and modifications, or is revised as the equivalent embodiment of equivalent variations.It is every without departing from this
The content of utility model technical solution any is simply repaiied according to the technical essence of the utility model is made to the above embodiment
Change, equivalent variations and modification, in the range of still falling within technical solutions of the utility model protection.
Claims (3)
1. a kind of small drone wing Quick assembling-disassembling structure, including wing, wing girder, wing auxiliary girder, fuselage, fuselage master
Beam, fuselage auxiliary girder, screw, it is characterized in that：The wing does exterior skin by composite material, is internally provided with reinforcing rib, and wing includes
Wing girder, wing auxiliary girder, wing girder are run through by a carbon pipe, and wing auxiliary girder uses the carbon pipe of one section of 200mm；The fuselage
Exterior skin is equally done by composite material, is internally provided with reinforcing rib, which includes fuselage girder, fuselage auxiliary girder, and is respectively adopted
Run through with a carbon pipe；The fuselage girder, fuselage auxiliary girder are equipped with the hole for fixing the screw；The fuselage and wing
Between pass through above-mentioned carbon pipe connect；The wing girder is made at the peak of airfoil lift face, and wing auxiliary girder is made in away from up-front
Within the scope of one of 50%-70%.
2. a kind of small drone wing Quick assembling-disassembling structure according to claim 1, it is characterized in that：The fuselage girder
Carbon pipe outside diameter be 14mm, internal diameter 12mm, the carbon pipe outside diameter of wing girder is 12mm, internal diameter 10mm, and fuselage auxiliary girder outer diameter is
8mm, internal diameter 6mm, wing auxiliary girder outer diameter are 6mm, internal diameter 4mm.
3. a kind of small drone wing Quick assembling-disassembling structure according to claim 1, it is characterized in that：In the fuselage master
Beam carbon Guan Shangshe is there are one the hole of a diameter of 3mm, the distance apart from fuselage edge 30mm；Wing girder stretches out wing 100mm, and
The hole of a diameter of 3mm is arranged in the position for the top 70mm that distance is stretched out on wing girder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720940545.XU CN207791128U (en) | 2017-07-31 | 2017-07-31 | A kind of small drone wing Quick assembling-disassembling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720940545.XU CN207791128U (en) | 2017-07-31 | 2017-07-31 | A kind of small drone wing Quick assembling-disassembling structure |
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| Publication Number | Publication Date |
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| CN207791128U true CN207791128U (en) | 2018-08-31 |
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| CN201720940545.XU Active CN207791128U (en) | 2017-07-31 | 2017-07-31 | A kind of small drone wing Quick assembling-disassembling structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109808868A (en) * | 2018-11-22 | 2019-05-28 | 成都飞机工业（集团）有限责任公司 | A kind of interior outer wing docking structure of small drone |
| CN112098035A (en) * | 2020-11-19 | 2020-12-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft test system |
| CN113716018A (en) * | 2021-08-24 | 2021-11-30 | 航天时代飞鹏有限公司 | Large-load wing adopting 3D printing |
-
2017
- 2017-07-31 CN CN201720940545.XU patent/CN207791128U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109808868A (en) * | 2018-11-22 | 2019-05-28 | 成都飞机工业（集团）有限责任公司 | A kind of interior outer wing docking structure of small drone |
| CN112098035A (en) * | 2020-11-19 | 2020-12-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft test system |
| CN113716018A (en) * | 2021-08-24 | 2021-11-30 | 航天时代飞鹏有限公司 | Large-load wing adopting 3D printing |
| CN113716018B (en) * | 2021-08-24 | 2024-06-11 | 航天时代飞鹏有限公司 | Large-load wing adopting 3D printing |
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