CN203793589U - Locating structure of top cover of four-axis agricultural aircraft - Google Patents
Locating structure of top cover of four-axis agricultural aircraft Download PDFInfo
- Publication number
- CN203793589U CN203793589U CN201420137882.1U CN201420137882U CN203793589U CN 203793589 U CN203793589 U CN 203793589U CN 201420137882 U CN201420137882 U CN 201420137882U CN 203793589 U CN203793589 U CN 203793589U
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- China
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- top cover
- cantilever
- equipment compartment
- latch
- motor bin
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Abstract
The utility model discloses a locating structure of a top cover of a four-axis agricultural aircraft. An aircraft body is made of a carbon fiber composite material and comprises an equipment bin (8), cantilevers (9) and a motor bin (10), wherein a top cover (1) matched with an opening in the top of the equipment bin (8) is arranged at the opening, a clamping block (2) and two locating bases (3) are fixed at positions, which are close to the edge, the bottom surface of the top cover (1), bolts (4) are jointly arranged on an inner support lug and an outer support lug of the same locating base (3) in a penetrating manner, a shifting lever (5) is vertically fixed on each bolt (4), and a spring (6) is arranged on each bolt (4) in a penetrating manner. The locating structure is simple in shape of the aircraft body, easy to process and fabricate, small in volume, light in weight, and reliable in strength; one clamping block and two stretchable bolts are arranged at the edge of the bottom surface of the top cover, and are respectively tightly matched with the aircraft body in a clamping and supporting manner, and the top cover can be conveniently and rapidly opened or closed, and is connected firmly and reliably.
Description
Technical field
The utility model belongs to agricultural vehicle technology field, specifically, and the particularly agricultural carry-on top cover location structure of four axles.
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 a kind of folding with convenience, connects the firm agricultural aircraft top cover of four axles location structure.
The technical solution of the utility model is as follows: the agricultural aircraft top cover of a kind of four axle location structure, comprise fuselage, top cover (1) and electronic governor (7), described fuselage is made by carbon fiber composite material, and by equipment compartment (8), cantilever (9) and motor bin (10) form, 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, in the outer end of each cantilever (9), be provided with motor bin (10), this motor bin (10) is that upper end is uncovered, the cylindrical structure of lower end closed, the inside of motor bin (10) communicates with the inside of equipment compartment (8) by cantilever (9), and the axis parallel of the axial line of motor bin (10) and equipment compartment (8), 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), interts and is fixed with a base plate (12), the upper electronic governor (7) of installing of this base plate (12) in these two postings (11), opening part at equipment compartment (8) top is provided with the top cover (1) adapting with it, described top cover (1) is the spherical structure that central high rim is low, and made by carbon fiber composite material, 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 outer end of this 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, 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 composite material, and not only weight is lighter, can effectively alleviate the weight of aircraft, and structural strength reliable, be difficult for being damaged, can increase the service life of fuselage.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.Motor bin adopts cylindrical structure, and not only moulding is simple, is conducive to processing and fabricating, and can carry out effective location to the rotor motor of aircraft, so that the installation of rotor motor, and guarantee that the installation of rotor motor is firm.
The utility model becomes spherical structure by design of cover, and not only moulding is simple, and processing and fabricating is easy, elegant in appearance, and height dimension is less, can not increase the height of whole aircraft; Top cover is made by carbon fiber composite material, lightweight on the one hand, can effectively alleviate the weight of aircraft, and on the other hand, structural strength is reliable, is difficult for being damaged.
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.
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.
On the interior diapire of described motor bin (10), be provided with circular positioning groove, be convenient to so more fast, mounted motor in motor room securely.
Beneficial effect: the utility model fuselage model is simple, and processing and fabricating is easy, and volume is small and exquisite, lightweight, and intensity is reliable; The utility model arranges a fixture block and two telescopic latches by the edge in top cover bottom surface, and mode and the fuselage by clamping and butt closely cooperates respectively, and it is firm that folding top cover, and top cover quickly and easily connects; Electronic governor is arranged in cantilever inside, can make full use of on the one hand the space of cantilever, does not affect the layout of other parts on aircraft; Make on the other hand electronic governor dismounting convenient, good heat dissipation effect, in-use performance is secure.
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 made by carbon fiber composite material, and 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, and the axial line of the axial line of described cantilever 9 and equipment compartment 8 is perpendicular, and the perisporium of the inner of 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, motor bin 10 is that upper end is uncovered, the cylindrical structure of lower end closed, and the inside of motor bin 10 communicates with the inside of equipment compartment 8 by cantilever 9, and the axis parallel of the axial line of motor bin 10 and equipment compartment 8.On the interior diapire of described motor bin 10, be provided with circular positioning groove, so that the rotor motor of aircraft is positioned.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, each 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 electronic governor 7 is installed on base plate 12.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 the spherical structure that central high rim is low, also preferably by carbon fiber composite material, is made.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 (8)
1. the agricultural aircraft top cover of an axle location structure, comprise fuselage, top cover (1) and electronic governor (7), it is characterized in that: described fuselage is made by carbon fiber composite material, and by equipment compartment (8), cantilever (9) and motor bin (10) form, 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 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), this motor bin (10) is that upper end is uncovered, the cylindrical structure of lower end closed, the inside of motor bin (10) communicates with the inside of equipment compartment (8) by cantilever (9), and the axis parallel of the axial line of motor bin (10) and equipment compartment (8), 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), the upper electronic governor (7) of installing of this base plate (12), opening part at equipment compartment (8) top is provided with the top cover (1) adapting with it, described top cover (1) is the spherical structure that central high rim is low, and made by carbon fiber composite material, 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 outer end of this 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, 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. the agricultural aircraft top cover of four axle according to claim 1 location structure, is characterized in that: the end face of described positioning seat (3) fits fixing by bottom surface bonding or screw and top cover (1).
3. the agricultural aircraft top cover of four axle according to claim 1 location structure, is characterized in that: the inner of described latch (4) is bulb, and this bulb is spacing by interior journal stirrup (3a).
4. the agricultural aircraft top cover of four axle according to claim 1 location structure, 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).
5. according to the agricultural aircraft top cover of the four axles location structure described in claim 1 or 4, it is characterized in that: the outline of described cantilever (9) cross-sectional plane is for oval, and the direction of the cross-sectional plane of cantilever (9) from equipment compartment (8) to motor bin (10) reduces gradually.
6. the agricultural aircraft top cover of four axle according to claim 1 location structure, 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.
7. the agricultural aircraft top cover of four axle according to claim 1 location structure, is characterized in that: described base plate (12) is made by aviation laminate, and be evenly distributed with circular louvre on base plate (12).
8. the agricultural aircraft top cover of four axle according to claim 1 location structure, is characterized in that: on the interior diapire of described motor bin (10), be provided with circular positioning groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420137882.1U CN203793589U (en) | 2014-03-26 | 2014-03-26 | Locating structure of top cover of four-axis agricultural aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420137882.1U CN203793589U (en) | 2014-03-26 | 2014-03-26 | Locating structure of top cover of four-axis agricultural aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203793589U true CN203793589U (en) | 2014-08-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420137882.1U Expired - Fee Related CN203793589U (en) | 2014-03-26 | 2014-03-26 | Locating structure of top cover of four-axis agricultural aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203793589U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108802280A (en) * | 2018-05-29 | 2018-11-13 | 山西天时利和智能科技有限公司 | A kind of unmanned plane atmospheric monitoring charging appliance |
-
2014
- 2014-03-26 CN CN201420137882.1U patent/CN203793589U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108802280A (en) * | 2018-05-29 | 2018-11-13 | 山西天时利和智能科技有限公司 | A kind of unmanned plane atmospheric monitoring charging appliance |
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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 |