CN203793597U - Integrated fuselage of agricultural unmanned aerial device - Google Patents
Integrated fuselage of agricultural unmanned aerial device Download PDFInfo
- Publication number
- CN203793597U CN203793597U CN201420138540.1U CN201420138540U CN203793597U CN 203793597 U CN203793597 U CN 203793597U CN 201420138540 U CN201420138540 U CN 201420138540U CN 203793597 U CN203793597 U CN 203793597U
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- top cover
- cantilever
- equipment compartment
- fixture block
- fuselage
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Abstract
The utility model discloses an integrated fuselage of an agricultural unmanned aerial device. Four cantilevers (9) which are circumferentially and uniformly distributed are arranged on the periphery of an equipment bin (8), a motor bin (10) is arranged at the outer end of each cantilever (9), a bottom plate (12) is fixedly arranged in a positioning frame (11) in each cantilever (9) by interpenetration, and an electronic speed adjuster (7) is mounted on the bottom plate (12). A top cover (1) is arranged at an opening in the top of the equipment bin (8), a fixture block (2) and two positioning seats (3) are fixedly arranged on the bottom surface of the top cover (1), which is close to the edge, and a bolt (4) is jointly arranged on an inner supporting lug and an outer supporting lug of the same positioning seat (3). The integrated fuselage disclosed by the utility model has the advantages of simple shape, easiness in processing and manufacturing, light weight and good structural strength; the fixture block and two telescopic bolts are arranged on the edge of the bottom surface of the top cover, the top cover is respectively in close fit with the fuselage in clamping and abutting ways, and the top cover can be conveniently and fast opened and closed.
Description
Technical field
The utility model belongs to agricultural vehicle technology field, specifically, and the particularly integrated form fuselage on agricultural unmanned flight instruments.
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 and electronic governor are all the vitals on agricultural unmanned vehicle, and wherein, top cover 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 folding, complex operation not only, and waste time and energy, the convenience that very impact is used.And existing electronic governor is arranged in equipment compartment, this kind of arrangement not only greatly takies equipment compartment space, affects the layout of other parts in equipment compartment; And very inconvenience of dismounting, heat dispersion is not good, and in-use performance does not ensure.In addition, the fuselage weight of existing agricultural unmanned vehicle and volume are large, structural strength is poor, easy damage, processing and fabricating are more difficult.
Utility model content
Technical problem to be solved in the utility model is to provide the agricultural unmanned flight instruments integrated form fuselage that a kind of moulding is simple, volume is small and exquisite.
The technical solution of the utility model is as follows: a kind of agricultural unmanned flight instruments integrated form fuselage, comprise fuselage, top cover (1) and electronic governor (7), described fuselage is comprised of equipment compartment (8), cantilever (9) and motor bin (10), described equipment compartment (8) is positioned at midway location, in the periphery of equipment compartment (8), be provided with four cantilevers (9) that distribute by even circumferential, this cantilever (9) is hollow structure, the perisporium of the inner of described cantilever (9) and equipment compartment (8) is connected as a single entity, and in the outer end of each cantilever (9), is provided with motor bin (10), described equipment compartment (8), cantilever (9) and motor bin (10) are structure as a whole, by aviation alkali-free glass layer of cloth, high-density glass layer of cloth, the first carbon fiber layer, PPC froth bed and the second carbon fiber layer arranged successively from outside to inside, formed, the inner position near equipment compartment (8) of cantilever described in each (9) is all provided with two postings that are parallel to each other (11), in these two postings (11), intert and be fixed with a base plate (12), electronic governor (7) is installed on this base plate (12), opening part at equipment compartment (8) top is provided with the top cover (1) adapting with it, and described top cover (1) is circular, and the outside one of end face at top cover (1) edge is extended, and forms a circle shirt rim, makes the edge of top cover (1) be ledge structure, at described top cover (1) place of keeping to the side, bottom surface, be fixed with a fixture block (2) and two positioning seats (3), described fixture block (2) is connected to the open-topped edge of equipment compartment (8), 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 inwall of the outer end of this latch (4) and equipment compartment (8) top ports connects, at the upper vertical fixedly 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 whole fuselage model of the utility model is simple, and processing and fabricating is easy, and volume is small and exquisite; Fuselage is made by multilayer materials, and not only weight is lighter, can effectively alleviate the weight of aircraft, and structural strength reliable, be difficult for being damaged.The utility model is arranged on cantilever inside by electronic governor, and the supporting construction being comprised of posting and base plate is accurately located, can guarantee the steadiness that electronic governor is supported, loosening to prevent that electronic governor from occurring, take full advantage of so on the one hand the space of cantilever, do not affect the layout of other parts on agricultural unmanned vehicle; On the other hand, the dismounting of electronic governor is very convenient.
The utility model is when 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 two driving levers to the direction motion at top cover center, now spring is compressed, in the time of 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.When top cover need to be opened, only need stir driving lever according to above operating mode, make latch retract, then around the fixture block flip top cover that makes progress.Top cover edge forms a circle shirt rim, and the edge of top cover is ledge structure like this, forms seam location between this step and fuselage, and not only locating effect is better, and can effectively strengthen the leak tightness of top cover.
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 equipment compartment (8) 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 equipment compartment 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).
The end face of cantilever described in each (9) is distributed with two row's thermovents (13), and this two row's thermovent (13) is arranged in the bilateral symmetry of cantilever (9) axial line, and thermovent (13) is positioned at the oblique upper of corresponding electronic governor (7).Above structure can be fully, distribute heat effectively, greatly ensured the in-use performance of electronic governor; Thermovent is at the oblique upper of electronic governor, even meet with during aircraft operation, rains, and rainwater yet can directly not waft and splash on electronic governor, thereby has effectively prevented electronic governor inefficacy.
In order to beautify outward appearance when guaranteeing product in-use performance, can also to alleviate the weight of fuselage to the greatest extent, the outline of described cantilever (9) cross-sectional plane is oval, and the direction of the cross-sectional plane of cantilever (9) from equipment compartment (8) to motor bin (10) reduces gradually.
Described posting (11) is elliptical annular sheet body structure, and is made by aviation laminate, and the thickness of posting (11) is 2-4mm.Posting adopts above structure, is combined closely with cantilever, and it is firm to connect; Posting is made by aviation laminate, and intensity is high, not yielding or damage; And angle of bend is little, aseismicity is good.
Described base plate (12) is made by aviation laminate, intensity is high, waterproof property and aseismicity good; On base plate (12), be evenly distributed with circular louvre, when electronic governor being carried out to effectively support, be conducive to the bottom heat radiation of electronic governor like this.
Beneficial effect: the utility model moulding is simple, and processing and fabricating is easy, lightweight, structural strength is good; A fixture block and two telescopic latches are set at the edge of top cover bottom surface, and top cover closely cooperates by mode and the fuselage of clamping and butt respectively, quickly and easily folding top cover.
Accompanying drawing explanation
Fig. 1 is the structural representation of fuselage.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is the birds-eye view after top cover is installed.
Fig. 4 is the A-A cutaway view of Fig. 3.
Fig. 5 is the scheme of installation of telescopic latch.
The specific embodiment
Below in conjunction with drawings and Examples, the utility model is described in further detail:
As shown in Figure 1 and Figure 2, fuselage is comprised of equipment compartment 8, cantilever 9 and motor bin 10, described equipment compartment 8, cantilever 9 and motor bin 10 are structure as a whole, and aviation alkali-free glass layer of cloth, high-density glass layer of cloth, the first carbon fiber layer, PPC froth bed and the second carbon fiber layer arranged successively from outside to inside, consist of.Wherein, equipment compartment 8 is positioned at midway location, and equipment compartment 8 upper ends have circular port lower end closed, in the periphery of equipment compartment 8, be provided with four cantilevers 9 that distribute by even circumferential, this cantilever 9 is hollow structure, the axial line of the axial line of cantilever 9 and equipment compartment 8 is perpendicular, and the perisporium of the inner of described cantilever 9 and equipment compartment 8 is connected as a single entity.In the outer end of each cantilever 9, be provided with motor bin 10, the axis parallel of the axial line of this motor bin 10 and equipment compartment 8.The outline of described cantilever 9 cross-sectional planes is oval, and the direction of the cross-sectional plane of cantilever 9 from equipment compartment 8 to motor bin 10 reduces gradually.
As shown in Figure 1 and Figure 2, described in each, the inner position near equipment compartment 8 of cantilever 9 is all provided with two postings that are parallel to each other 11, described posting 11 is elliptical annular sheet body structure, and the inwall of the external annulus of posting 11 and cantilever 9 fits, and by being adhesively fixed.Described posting 11 is made by aviation laminate, and the thickness of posting 11 is 2-4mm.Interior interting of two postings 11 in same cantilever 9 is fixed with a base plate 12, and base plate 12 is positioned on horizontal surface, and has gap between base plate 12 and the interior diapire of cantilever 9.Described base plate 12 is made by aviation laminate, is evenly distributed with circular louvre on base plate 12, and on this base plate 12, electronic governor 7 is installed.Described in each, the end face of cantilever 9 is distributed with two platoon leader's bar shaped thermovents 13, and described thermovent 13 is strip shape structure, and this two rows thermovent 13 is arranged in the bilateral symmetry of cantilever 9 axial lines, and thermovent 13 is positioned at the oblique upper of corresponding electronic governor 7.
As shown in Fig. 3, Fig. 4 and Fig. 5, the opening part at equipment compartment 8 tops is provided with the top cover 1 adapting with it, and top cover 1 is preferably made by carbon fiber composite material.Described top cover 1 is circular, and the outside one of end face at top cover 1 edge is extended, and forms a circle shirt rim, makes the edge of top cover 1 be ledge structure, and top cover 1 fastens by the step at edge and the opening at equipment compartment 8 tops.At described top cover, 1 place of keeping to the side, bottom surface 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 equipment compartment 8.
As shown in Fig. 3, Fig. 4 and Fig. 5, the end face of positioning seat 3 fits fixing by bottom surface bonding or screw and top cover 1, in the interior outer end of each positioning seat 3 bottom, be respectively arranged with interior journal stirrup 3a and outer journal stirrup 3b, 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 equipment compartment 8 top ports connects.Vertical fixedly 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 (6)
1. an agricultural unmanned flight instruments integrated form fuselage, comprise fuselage, top cover (1) and electronic governor (7), it is characterized in that: described fuselage is comprised of equipment compartment (8), cantilever (9) and motor bin (10), described equipment compartment (8) is positioned at midway location, in the periphery of equipment compartment (8), be provided with four cantilevers (9) that distribute by even circumferential, this cantilever (9) is hollow structure, the perisporium of the inner of described cantilever (9) and equipment compartment (8) is connected as a single entity, and in the outer end of each cantilever (9), is provided with motor bin (10), described equipment compartment (8), cantilever (9) and motor bin (10) are structure as a whole, by aviation alkali-free glass layer of cloth, high-density glass layer of cloth, the first carbon fiber layer, PPC froth bed and the second carbon fiber layer arranged successively from outside to inside, formed, the inner position near equipment compartment (8) of cantilever described in each (9) is all provided with two postings that are parallel to each other (11), in these two postings (11), intert and be fixed with a base plate (12), electronic governor (7) is installed on this base plate (12), opening part at equipment compartment (8) top is provided with the top cover (1) adapting with it, and described top cover (1) is circular, and the outside one of end face at top cover (1) edge is extended, and forms a circle shirt rim, makes the edge of top cover (1) be ledge structure, at described top cover (1) place of keeping to the side, bottom surface, be fixed with a fixture block (2) and two positioning seats (3), described fixture block (2) is connected to the open-topped edge of equipment compartment (8), 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 inwall of the outer end of this latch (4) and equipment compartment (8) top ports connects, at the upper vertical fixedly 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 flight instruments integrated form fuselage 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 fix 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 equipment compartment (8) phase clamping.
3. agricultural unmanned flight instruments integrated form fuselage 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).
4. agricultural unmanned flight instruments integrated form fuselage 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).
5. agricultural unmanned flight instruments integrated form fuselage according to claim 1, it is characterized in that: the end face of cantilever described in each (9) is distributed with two row's thermovents (13), this two row's thermovent (13) is arranged in the bilateral symmetry of cantilever (9) axial line, and thermovent (13) is positioned at the oblique upper of corresponding electronic governor (7).
6. agricultural unmanned flight instruments integrated form fuselage according to claim 1, is characterized in that: described posting (11) is elliptical annular sheet body structure, and is made by aviation laminate, and the thickness of posting (11) is 2-4mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420138540.1U CN203793597U (en) | 2014-03-26 | 2014-03-26 | Integrated fuselage of agricultural unmanned aerial device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420138540.1U CN203793597U (en) | 2014-03-26 | 2014-03-26 | Integrated fuselage of agricultural unmanned aerial device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203793597U true CN203793597U (en) | 2014-08-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420138540.1U Expired - Fee Related CN203793597U (en) | 2014-03-26 | 2014-03-26 | Integrated fuselage of agricultural unmanned aerial device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203793597U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863550A (en) * | 2014-03-26 | 2014-06-18 | 重庆金泰航空工业有限公司 | Integrated body of agricultural unmanned aircraft |
-
2014
- 2014-03-26 CN CN201420138540.1U patent/CN203793597U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863550A (en) * | 2014-03-26 | 2014-06-18 | 重庆金泰航空工业有限公司 | Integrated body of agricultural unmanned aircraft |
| CN103863550B (en) * | 2014-03-26 | 2016-08-24 | 重庆金泰航空工业有限公司 | A kind of agricultural unmanned flight's device integrated form fuselage |
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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 |
Granted publication date: 20140827 Termination date: 20170326 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |