CN203793632U - Composite top cover opening and closing structure on agricultural unmanned aerial vehicle - Google Patents
Composite top cover opening and closing structure on agricultural unmanned aerial vehicle Download PDFInfo
- Publication number
- CN203793632U CN203793632U CN201420139019.XU CN201420139019U CN203793632U CN 203793632 U CN203793632 U CN 203793632U CN 201420139019 U CN201420139019 U CN 201420139019U CN 203793632 U CN203793632 U CN 203793632U
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- top cover
- closing structure
- agricultural unmanned
- cover opening
- unmanned vehicle
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Abstract
The utility model discloses a composite top cover opening and closing structure on an agricultural unmanned aerial vehicle. The composite top cover opening and closing structure is characterized in that a top cover (1) comprises an aerial alkali-free glass cloth layer (1a), a high-density glass cloth layer (1b), a first carbon fiber layer (1c), a PPC (polypropylene carbonate) foam layer (1d) and a second carbon fiber layer (1e); a fixture block (2) and two positioning seats (3) are fixed on the bottom surface of the top cover (1), close to the edge; an inner lug (3a) and an outer lug (3b) are respectively arranged at the inner and outer ends of the bottom of each positioning seat (3); a bolt (4) penetrates through both the inner and outer lugs of the same positioning seat (3); a driving lever (5) is vertically fixed on the bolt (4); the bolt (4) is sleeved with a spring (6). The composite top cover opening and closing structure has the beneficial effects that the top cover and a body are made from composite materials, not only are light but also have good structural strength; the top cover can be conveniently and rapidly opened and closed by arranging the fixture block and the two telescopic bolts at the edge of the bottom surface of the top cover.
Description
Technical field
The utility model belongs to agricultural vehicle technology field, specifically, and the particularly combined type top cover opening-closing structure on agricultural unmanned vehicle.
Background technology
Along with social development, the progress of science and technology, the work such as spray insecticide on a large scale in farmland, fertilising are progressively completed by unmanned vehicle.Top cover is the vitals on agricultural unmanned vehicle, plays closed fuselage upper port.Existing top cover is convertible structure, and locks by lockset.In use, top cover not only weight greatly, easily damage; And very inconvenience of the folding of top cover, not only complex operation, and waste time and energy, the convenience that very impact is used.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of agricultural unmanned vehicle combined type top cover opening-closing structure of folding with convenience.
The technical solution of the utility model is as follows: a kind of agricultural unmanned vehicle combined type top cover opening-closing structure, be provided with the top cover (1) adapting with it at the opening part at fuselage (7) top, described top cover (1) is made up of the aviation alkali-free glass layer of cloth (1a) of arranging successively from top to bottom, high-density glass layer of cloth (1b), the first carbon fiber layer (1c), PPC froth bed (1d) and the second carbon fiber layer (1e), be fixed with a fixture block (2) and two positioning seats (3) at described top cover (1) the bottom surface place of keeping to the side, described fixture block (2) is connected to the open-topped edge of fuselage (7), and described fixture block (2) and two positioning seats (3) are uniformly distributed at circumferencial direction, interior outer end in each positioning seat (3) bottom is respectively arranged with interior journal stirrup (3a) and outer journal stirrup (3b), in same positioning seat (3), on outer journal stirrup, jointly wear latch (4), the outer end of this latch (4) exceeds the outer of top cover (1), and the inwall of the outer end of latch (4) and fuselage (7) top ports connects, at the upper vertical fixing driving lever (5) of described latch (4), the upper end of this driving lever (5) is through positioning seat (3) and the corresponding bar shaped via hole arranging of top cover (1), on described latch (4), be set with spring (6), one end of this spring (6) and interior journal stirrup (3a) connect, the other end of spring (6) and driving lever (5) connect.
The utility model top cover is made up of carbon fiber composite material, and not only weight is lighter, can effectively reduce the weight of whole agricultural aircraft, and structural strength is good, is difficult for damagedly, can increase service life of top cover and fuselage.
The utility model is in closing top cover, first the gap between crosspiece under fixture block and top cover is snapped in to the edge of fuselage top end opening, top cover is carried out on fuselage to Primary Location, then stir two driving levers simultaneously, make the direction motion of two driving levers to top cover center, now spring is compressed, when driving lever motion, together with the latch that drive is fixedly connected with driving lever, move, make in the retraction top cover edge, outer end of latch, like this top cover completely spiral-lock at the opening part on fuselage top, and fuselage top end opening is sealed, finally unclamp driving lever, under the effect of recoil of spring power, driving lever and latch reset, the inwall of the outer end of latch and fuselage top end opening pushes against, under the combined action of two latches and a fixture block, top cover tightly spiral-lock at fuselage top, can not occur loosening or come off.In the time that top cover need to be opened, only need stir driving lever according to above operating mode, make latch retract, then around upwards flip top cover of fixture block.
Between the each adjacent layer of described top cover (1), by being adhesively fixed, can reduce production costs like this, it is fixing more firm to make again.
In order to beautify outward appearance, and strengthen resistance to abrasion and the anti-corrosive properties of product, be coated with epoxy enamelled coating (1f) at the end face of described aviation alkali-free glass layer of cloth (1a).
In guaranteeing properties of product, save as much as possible material, the thickness of described epoxy enamelled coating (1f) is 0.05mm.
For the ease of drawing materials, the thickness of described aviation alkali-free glass layer of cloth (1a) is 0.08mm.
In order conveniently to draw materials, the thickness of described high-density glass layer of cloth (1b) is 0.1mm.
Described fuselage (7) is made up of carbon fiber composite material, and fuselage is lightweight like this, and structural strength is good, can not deform or damage, and long service life.
Described fixture block (2) is " Z " shape, and the bottom surface of the upper crosspiece of fixture block (2) and top cover (1) fits, and fixes by bonding or screw, between the lower crosspiece of fixture block (2) and the bottom surface of top cover (1), forms bayonet socket, this bayonet socket and fuselage (7) phase clamping.Above structure on the one hand between fixture block and top cover area of contact large, connect not only firmly but also reliable; On the other hand, the gap under fixture block between crosspiece and top cover bottom surface can conveniently be located, and is conducive to top cover and fuselage clamping is firm.
For the end face of positioning seat is firmly connected with the bottom surface of top cover, the end face of described positioning seat (3) fits fixing by bottom surface bonding or screw and top cover (1).
For simplified structure, facilitate processing and fabricating, prevent that latch from coming off, the inner of described latch (4) is bulb, this bulb is spacing by interior journal stirrup (3a).
Beneficial effect: the utility model fuselage and top cover are made up of composite material, not only lightweight, and also structural strength is good; The utility model is by a fixture block and two telescopic latches are set at the edge of top cover bottom surface, and closely cooperates by mode and the fuselage of clamping and butt respectively, folding top cover quickly and easily.
Brief description of the drawings
Fig. 1 is birds-eye view of the present utility model.
Fig. 2 is the A-A cutaway view of Fig. 1.
Fig. 3 is the scheme of installation of telescopic latch.
Fig. 4 is the stratiform schematic diagram of top cover.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is described in further detail:
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, fuselage 7 is made up of carbon fiber composite material, be provided with the top cover 1 adapting with it at the opening part at fuselage 7 tops, described top cover 1 is made up of aviation alkali-free glass layer of cloth 1a, the high-density glass layer of cloth 1b, the first carbon fiber layer 1c, PPC froth bed 1d and the second carbon fiber layer 1e that arrange successively from top to bottom, between two adjacent layers by being adhesively fixed.The thickness of described aviation alkali-free glass layer of cloth 1a is preferably 0.08mm, is coated with epoxy enamelled coating 1f at the end face of aviation alkali-free glass layer of cloth 1a, and the thickness of this epoxy enamelled coating 1f is preferably 0.05mm.The thickness of described high-density glass layer of cloth 1b is preferably 0.1mm.
As shown in Figure 1, Figure 2 and Figure 3, at described top cover, the 1 bottom surface place of keeping to the side is provided with a fixture block 2 and two positioning seats 3, and fixture block 2 and two positioning seats 3 are uniformly distributed at circumferencial direction.Described fixture block 2 is " Z " shape, and the bottom surface of the upper crosspiece of fixture block 2 and top cover 1 fits, and by fixing by bonding or screw, between the lower crosspiece of fixture block 2 and the bottom surface of top cover 1, forms bayonet socket, this bayonet socket and the phase clamping of the open-topped edge of fuselage 7.
As shown in Figure 1, Figure 2 and Figure 3, the end face of positioning seat 3 fits fixing by bottom surface bonding or screw and top cover 1, be respectively arranged with interior journal stirrup 3a and outer journal stirrup 3b in the interior outer end of each positioning seat 3 bottoms, interior journal stirrup 3a and outer journal stirrup 3b and positioning seat 3 are structure as a whole.On inside and outside journal stirrup 3a, the 3b of same positioning seat 3, jointly wear a latch 4, the inner of described latch 4 is bulb, this bulb is outwards spacing by interior journal stirrup 3a, and the outer end of described latch 4 exceeds the outer of top cover 1, and the inwall of the outer end of latch 4 and fuselage 7 top ports connects.Vertical fixing driving lever 5 on described latch 4, the upper end of this driving lever 5, through positioning seat 3 and the corresponding bar shaped via hole arranging of top cover 1, is set with spring 6 on described latch 4, and one end of this spring 6 and interior journal stirrup 3a connect, and the other end of spring 6 and driving lever 5 connect.
Claims (10)
1. an agricultural unmanned vehicle combined type top cover opening-closing structure, be provided with the top cover (1) adapting with it at the opening part at fuselage (7) top, it is characterized in that: described top cover (1) is made up of the aviation alkali-free glass layer of cloth (1a) of arranging successively from top to bottom, high-density glass layer of cloth (1b), the first carbon fiber layer (1c), PPC froth bed (1d) and the second carbon fiber layer (1e), be fixed with a fixture block (2) and two positioning seats (3) at described top cover (1) the bottom surface place of keeping to the side, described fixture block (2) is connected to the open-topped edge of fuselage (7), and described fixture block (2) and two positioning seats (3) are uniformly distributed at circumferencial direction, interior outer end in each positioning seat (3) bottom is respectively arranged with interior journal stirrup (3a) and outer journal stirrup (3b), in same positioning seat (3), on outer journal stirrup, jointly wear latch (4), the outer end of this latch (4) exceeds the outer of top cover (1), and the inwall of the outer end of latch (4) and fuselage (7) top ports connects, at the upper vertical fixing driving lever (5) of described latch (4), the upper end of this driving lever (5) is through positioning seat (3) and the corresponding bar shaped via hole arranging of top cover (1), on described latch (4), be set with spring (6), one end of this spring (6) and interior journal stirrup (3a) connect, the other end of spring (6) and driving lever (5) connect.
2. agricultural unmanned vehicle combined type top cover opening-closing structure according to claim 1, is characterized in that: between the each adjacent layer of described top cover (1) by being adhesively fixed.
3. agricultural unmanned vehicle combined type top cover opening-closing structure according to claim 1, is characterized in that: be coated with epoxy enamelled coating (1f) at the end face of described aviation alkali-free glass layer of cloth (1a).
4. agricultural unmanned vehicle combined type top cover opening-closing structure according to claim 3, is characterized in that: the thickness of described epoxy enamelled coating (1f) is 0.05mm.
5. according to the agricultural unmanned vehicle combined type top cover opening-closing structure described in claim 1 or 2 or 3 or 4, it is characterized in that: the thickness of described aviation alkali-free glass layer of cloth (1a) is 0.08mm.
6. according to the agricultural unmanned vehicle combined type top cover opening-closing structure described in claim 1 or 2 or 3 or 4, it is characterized in that: the thickness of described high-density glass layer of cloth (1b) is 0.1mm.
7. agricultural unmanned vehicle combined type top cover opening-closing structure according to claim 1, is characterized in that: described fuselage (7) is made up of carbon fiber composite material.
8. agricultural unmanned vehicle combined type top cover opening-closing structure according to claim 1, it is characterized in that: described fixture block (2) is " Z " shape, the bottom surface of the upper crosspiece of fixture block (2) and top cover (1) fits, and by fixing by bonding or screw, between the bottom surface of the lower crosspiece of fixture block (2) and top cover (1), form bayonet socket, this bayonet socket and fuselage (7) phase clamping.
9. agricultural unmanned vehicle combined type top cover opening-closing structure according to claim 1, is characterized in that: the end face of described positioning seat (3) fits fixing by bottom surface bonding or screw and top cover (1).
10. agricultural unmanned vehicle combined type top cover opening-closing structure according to claim 1, is characterized in that: the inner of described latch (4) is bulb, and this bulb is spacing by interior journal stirrup (3a).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420139019.XU CN203793632U (en) | 2014-03-26 | 2014-03-26 | Composite top cover opening and closing structure on agricultural unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420139019.XU CN203793632U (en) | 2014-03-26 | 2014-03-26 | Composite top cover opening and closing structure on agricultural unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203793632U true CN203793632U (en) | 2014-08-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420139019.XU Expired - Fee Related CN203793632U (en) | 2014-03-26 | 2014-03-26 | Composite top cover opening and closing structure on agricultural unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN203793632U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109109400A (en) * | 2016-06-13 | 2019-01-01 | 亿航智能设备（广州）有限公司 | A kind of composite material and aircraft |
-
2014
- 2014-03-26 CN CN201420139019.XU patent/CN203793632U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109109400A (en) * | 2016-06-13 | 2019-01-01 | 亿航智能设备（广州）有限公司 | A kind of composite material and aircraft |
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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: 20140827 Termination date: 20170326 |