CN205602087U - Unmanned aerial vehicle fuselage and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle fuselage and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN205602087U CN205602087U CN201521085647.5U CN201521085647U CN205602087U CN 205602087 U CN205602087 U CN 205602087U CN 201521085647 U CN201521085647 U CN 201521085647U CN 205602087 U CN205602087 U CN 205602087U
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- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- section
- cabin
- fuselage
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Abstract
The utility model discloses an unmanned aerial vehicle fuselage and unmanned aerial vehicle, the unmanned aerial vehicle fuselage includes two at least cabin sections, and adjacent cabin section is spliced or the spiro union, and the cabin section is one side opening at least, and the opening part is equipped with the matched with flap, still is equipped with the interface with airborne equipment matched with in the section of cabin. Unmanned aerial vehicle includes above -mentioned unmanned aerial vehicle fuselage. The unmanned aerial vehicle fuselage adopts a plurality of cabins section, and this kind designs not only light in weight, assemble small in quantityly, and intensity is high, bears efficiently, when the increase airborne equipment, also can guarantee the reliability of fuselage.
Description
Technical field
This utility model relates to unmanned plane field, particularly to a kind of unmanned aerial vehicle body and unmanned plane.
Background technology
Along with the lifting of Consumer's Experience, the playability of unmanned plane requires day by day to increase, correspondingly, with peculiar
The airborne equipment of function is the most all increasing, and these necessarily increase the load-carrying requirement of aircraft, therefore to airframe structure
Reliability, stability etc. all bring no small challenge.
It is known that fuselage is extremely important part in unmanned plane overall structure, be unmanned plane dynamical system,
The airborne equipment such as flight control system, task system, and the peace of the unmanned plane construction package such as wing, empennage
Assembling platform, it may be said that the stability of airframe structure and reliability are the basis of unmanned plane, therefore, airframe structure
For unmanned plane particularly important.
At present, unmanned plane needs balance-seeking on own wt and structural reliability, and airframe structure is wherein
Key, on market, the plate construction such as commonly used foam, laminate, cork wood is used as airframe structure, for
The less demanding unmanned plane of load capacity can meet requirement, but increases once airborne equipment, has caused
Fly weight amount increases, and can be substantially reduced the reliability of plate construction, thus it is more airborne to limit unmanned plane carrying
The ability of equipment, if increase the thickness of sheet material or use the material that metal equal strength is high to do sheet material, meeting
It is greatly improved unmanned plane own wt, causes the waste of load-carrying efficiency and flight efficiency, and, plate construction
Parts too many, pretty troublesome during installation and too much junction point can cause product strength to reduce.
Further, for large-scale unmanned plane, fuselage forming frock is the biggest so that frock processing needs use bigger
The machine of stroke adds lathe, and the course of processing needs clamping repeatedly, significantly increases the consumption of fund and time,
And the circulation of frock is the most very inconvenient.
Utility model content
Based on this, this utility model provides one can carry more airborne equipment and keep fuselage intensity and just
Unmanned aerial vehicle body in processing.
The concrete technical scheme solving above-mentioned technical problem is as follows:
A kind of unmanned aerial vehicle body, including at least two cabin section, adjacent compartment section is gluedd joint or is spirally connected, cabin section at least
Side opening, opening part is provided with the lid matched, is additionally provided with the interface matched with airborne equipment in the section of cabin.
As further improvement of the utility model, described lid is provided with installing hole, and bolt passes through installing hole will
Lid is fixed on the opening part of cabin section.
As further improvement of the utility model, the number of described cabin section is 3-5.
As further improvement of the utility model, described cabin section is by composite material integral formed；Described compound
Material is the material that two or more material of different nature is prepared from by combination process.
As further improvement of the utility model, described composite is carbon fibre composite, glass fibers
Dimension composite.
As further improvement of the utility model, described cabin section outer surface also covers enhancement Layer.
Another object of the present utility model is to provide one can carry more airborne equipment and keep fuselage intensity
Unmanned plane, described unmanned plane includes above-mentioned unmanned aerial vehicle body.
Advantage of the present utility model and having the beneficial effect that:
1, unmanned aerial vehicle body described in the utility model uses multiple cabins section, and corresponding forming frock has been also divided into many
Individual, so significantly reduce the size of frock, reduce the range demands to machining tool, decrease repeatedly
The number of times of clamping, the great convenience circulation of frock；This kind of design is the most lightweight, and assembling quantity is few,
And intensity is high, load-carrying efficiency is high, when increasing airborne equipment, also can guarantee that the reliability of fuselage.
2, the cabin section of unmanned aerial vehicle body described in the utility model or is spirally connected by splicing by multiple " boxlike " cabin section
Mode be attached forming, although bonding mode adds the quantity in splicing face, but reduces single glue
The area of junction, the least bonding quality in splicing face is more easily controlled；Airborne equipment is set in mounting box, when needing
When increasing more airborne equipment, only need to increase cabin section, not interfere with the intensity of other cabin sections；?
During fuselage assembling, the cooperation face of cabin section is plane or simple curved surface, and fit system is easily achieved, due to warp
Glueing joint or after being spirally connected, fuselage can be considered an entirety, thus this structure be remarkably improved in flight course pneumatic
Load, vibration, tired equivalent-load efficiency；When cabin section is damaged or needs to change, it is only necessary to change target cabin
Section, it is not necessary to integral demounting or replacing.
3, each cabin section of unmanned aerial vehicle body described in the utility model is box shaped, and manufacturing process is simple.
4, the cabin section of unmanned aerial vehicle body described in the utility model has opening at least side, and is entered by lid
Row is closed, so that install airborne equipment to become simple, lid can also protect the airborne equipment of cabin section.
5, unmanned aerial vehicle body described in the utility model also uses high-performance composite materials to cover reinforcement at cabin section surface
Layer, further adds the intensity of fuselage, it is ensured that its reliability.
Accompanying drawing explanation
Fig. 1 is the stereochemical structure principle schematic of this utility model unmanned aerial vehicle body.
Fig. 2 is the plan structure principle schematic of this utility model unmanned aerial vehicle body.
Fig. 3 is the Fig. 2 sectional view along A-A.
Description of reference numerals
1, fuselage；2, cabin section；3, lid；4, enhancement Layer；5, installing hole.
Detailed description of the invention
Below with reference to specific embodiment, this utility model is described further.
As shown in Figure 1-Figure 3, a kind of unmanned aerial vehicle body 1 described in the utility model, including at least two cabin section
2, adjacent compartment section is gluedd joint or is spirally connected, and a cabin section at least side opening, opening part is provided with the lid matched, cabin section
The interface matched with airborne equipment it is additionally provided with in 2.Unmanned aerial vehicle body 1 described in the present embodiment uses multiple cabins section
2, corresponding forming frock has been also divided into multiple, so significantly reduces the size of frock, reduces processing
The range demands of lathe, decrease repeatedly the number of times of clamping, the great convenience circulation of frock；And this sets
Counting the most lightweight, assembling quantity is few, and intensity is high, and load-carrying efficiency is high, when increasing airborne equipment, also
Can guarantee that the reliability of fuselage 1；Also have between cabin section 2 and be attached forming by the way of glueing joint or being spirally connected,
Although bonding mode adds the quantity in splicing face, but reduces the area in single splicing face, glued joint face more
Little bonding quality is more easily controlled；Airborne equipment is set in mounting box, when needs increase more airborne equipment
Time, only need to increase cabin section 2, not interfere with the intensity of other cabin sections 2；When fuselage 1 assembles, cabin
The cooperation face of section 2 is plane or simple curved surface, and fit system is easily achieved, due to after glueing joint or being spirally connected,
Fuselage 1 can be considered an entirety, thus this structure be remarkably improved in flight course aerodynamic loading, vibration,
Tired equivalent-load efficiency；When cabin section 2 is damaged or needs to change, it is only necessary to change target cabin section 2,
Without integral demounting or replacing.
Further, described lid 3 is provided with installing hole 5, and lid 3 is fixed on cabin by installing hole 5 by bolt
The opening part of section 2, described bolt can be ears plate nut.Due to technical grade aircraft working environment and work
Load is general more severe, and reliability is excellent.
Further, the number of described cabin section 2 is 3-5.
Further, described cabin section 2 is by composite material integral formed；Described composite is two kinds or two kinds
The material that material the most of different nature is prepared from by combination process；Described in concrete application example again
Condensation material is carbon fibre composite, glass fiber compound material.
Further, section 2 outer surface in described cabin also covers enhancement Layer 4.Fuselage also covers in a particular embodiment
There are high-performance composite materials to cover enhancement Layer 4 on cabin section 2 surface, further add the intensity of fuselage,
Ensure that its reliability.
Below being only preferred implementation of the present utility model, protection domain of the present utility model also not only limits to
In above-described embodiment, all technical schemes belonged under this utility model thinking belong to protection of the present utility model
Scope.It should be pointed out that, for those skilled in the art, without departing from this utility model
Some improvements and modifications under principle premise, should be regarded as protection domain of the present utility model.
Claims (6)
1. a unmanned aerial vehicle body, it is characterised in that include at least two cabin section, adjacent compartment section is gluedd joint or spiral shell
Connecing, a cabin section at least side opening, opening part is provided with the lid matched, is additionally provided with and airborne equipment in the section of cabin
The interface matched.
Unmanned aerial vehicle body the most according to claim 1, it is characterised in that described lid is provided with installing hole,
Lid is fixed on the opening part of cabin section by bolt by installing hole.
Unmanned aerial vehicle body the most according to claim 1 and 2, it is characterised in that the number of described cabin section
For 3-5.
Unmanned aerial vehicle body the most according to claim 1 and 2, it is characterised in that described cabin section is by being combined
Material is one-body molded.
Unmanned aerial vehicle body the most according to claim 1 and 2, it is characterised in that described cabin section outer surface
Also cover enhancement Layer.
6. a unmanned plane, it is characterised in that described unmanned plane includes described in any one of claim 1-5
Unmanned aerial vehicle body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521085647.5U CN205602087U (en) | 2015-12-23 | 2015-12-23 | Unmanned aerial vehicle fuselage and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521085647.5U CN205602087U (en) | 2015-12-23 | 2015-12-23 | Unmanned aerial vehicle fuselage and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205602087U true CN205602087U (en) | 2016-09-28 |
Family
ID=56959951
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521085647.5U Expired - Fee Related CN205602087U (en) | 2015-12-23 | 2015-12-23 | Unmanned aerial vehicle fuselage and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205602087U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108539326A (en) * | 2018-03-16 | 2018-09-14 | 清远市巨劲科技有限公司 | One kind being used for unmanned plane power battery winter job attemperator |
| CN108791868A (en) * | 2018-07-31 | 2018-11-13 | 刘浩然 | A kind of new transport unmanned plane of safety and stability |
| CN109110133A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of plural serial stage shipping unmanned aerial vehicle body |
| CN110155304A (en) * | 2019-01-25 | 2019-08-23 | 北京机电工程研究所 | Anti- side knock big opening cargo tank structure and the aircraft with it |
-
2015
- 2015-12-23 CN CN201521085647.5U patent/CN205602087U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108539326A (en) * | 2018-03-16 | 2018-09-14 | 清远市巨劲科技有限公司 | One kind being used for unmanned plane power battery winter job attemperator |
| CN108791868A (en) * | 2018-07-31 | 2018-11-13 | 刘浩然 | A kind of new transport unmanned plane of safety and stability |
| CN109110133A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of plural serial stage shipping unmanned aerial vehicle body |
| CN110155304A (en) * | 2019-01-25 | 2019-08-23 | 北京机电工程研究所 | Anti- side knock big opening cargo tank structure and the aircraft with it |
| CN110155304B (en) * | 2019-01-25 | 2021-11-12 | 北京机电工程研究所 | Anti-transverse-impact large-opening cabin section structure and aircraft with same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160928 Termination date: 20171223 |