CN203793591U - Integrated type fuselage of four-axle type flying device - Google Patents
Integrated type fuselage of four-axle type flying device Download PDFInfo
- Publication number
- CN203793591U CN203793591U CN201420137917.1U CN201420137917U CN203793591U CN 203793591 U CN203793591 U CN 203793591U CN 201420137917 U CN201420137917 U CN 201420137917U CN 203793591 U CN203793591 U CN 203793591U
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- top cover
- equipment compartment
- fuselage
- cantilever
- fixture block
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Abstract
The utility model discloses an integrated type fuselage of a four-axle type flying device. An equipment compartment (8) is internally divided into an upper equipment cavity and a lower liquor cavity through a transverse plate (14); the position, which is close to an edge, of the bottom surface of a top cover (1) is fixed with a clamping block (2) and two positioning seats (3); the inner end and outer end of the bottom of each positioning seat (3) are respectively provided with an inner support lug (3a) and an outer support lug (3b); inserted pins (4) penetrate through both the inner support lug (3a) and the outer support lug (3b) of the same positioning seat (3), and the inserted pins (4) are vertically fixed with shifter levers (5). The integrated type fuselage disclosed by the utility model has the advantages of simple structure, light weight and good structural strength. According to the integrated type fuselage, a liquor box which contains liquor is integrated into the fuselage, so that the cost can be reduced, the height dimension of the fuselage can be reduced, the liquor can be prevented from rocking, and the balance of a flight vehicle is ensured; the edge of the bottom surface of the top cover (1) is provided with the clamping block (2) and two telescopic inserted pins, and the top cover (1) is in close fit with the fuselage through a clamping mode and a supporting mode respectively, so that the top cover (1) 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 four-axle type 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, not only complex operation, 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.In addition, the medicine-chest of splendid attire liquid is generally arranged on the below of fuselage, and medicine-chest needs to make separately, and difficulty had both been assembled in processing, and productive costs is higher, can increase the height of whole aircraft; In the time that the liquid in medicine-chest is less, be subject to the impact of aircraft operational vibration, liquid can agitate and rock, thereby affects the balance of aircraft, reduces the effect of spray liquid.
Utility model content
Technical problem to be solved in the utility model is to provide that a kind of moulding is simple, volume is small and exquisite, can effectively prevent that liquid from rocking four-axle type flight instruments integrated form fuselage.
The technical solution of the utility model is as follows: a kind of four-axle type flight instruments integrated form fuselage, comprise fuselage, top cover (1) and electronic governor (7), described fuselage is by equipment compartment (8), cantilever (9) and motor bin (10) composition, described equipment compartment (8) is positioned at midway location, the inside of this equipment compartment (8) is separated into the equipment cavity of top and the liquid cavity of below by transverse slat (14), middle part at transverse slat (14) has dosing mouth, the tegillum (15) that shape size adapts is with it installed at this dosing mouth place, in described liquid cavity, be fixedly installed " well " font dividing plate (16), liquid cavity is separated into nine chambers by this dividing plate (16), laterally and longitudinally going up the through hole of offering by dividing plate (16) bottom between two adjacent chamber is communicated with, be provided with four cantilevers (9) that distribute by even circumferential in the periphery of described equipment compartment (8), 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 is provided with motor bin (10) in the outer end of each cantilever (9), described equipment compartment (8), cantilever (9) and motor bin (10) are structure as a whole, formed 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, in the inner position near equipment compartment (8) of each described cantilever (9), two postings that are parallel to each other (11) are all installed, in these two postings (11), intert and be fixed with a base plate (12), electronic governor (7) is installed on this base plate (12), be provided with the top cover (1) adapting with it at the opening part at equipment compartment (8) top, 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, 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 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 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 adopts transverse slat equipment compartment bottom to be separated out to the cavity of splendid attire liquid, needn't make separately and assemble like this medicine-chest, has both reduced productive costs, has effectively reduced again the height dimension of fuselage; Liquid cavity is become nine chambers by baffle for separating, and peripheral chamber is all communicated with intermediate cavity, can not affect so on the one hand normally pumping of liquid, on the other hand, when liquid is less by uniform distribution in each chamber, not affected by FLIGHT VEHICLE VIBRATION and produce to rock, thereby guarantee the balance of aircraft, effectively improve the effect of spray liquid.
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.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.
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 up of multilayer materials, and not only weight is lighter, can effectively alleviate the weight of aircraft, and structural strength reliable, be difficult for being damaged.Electronic governor is arranged on cantilever inside by the utility model, and the supporting construction being made up 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.
Described dividing plate (16) is made up of cellular composite material, and thickness is 3-5mm, and the intensity of dividing plate is reliable like this, can not deform or damage; Meanwhile, dividing plate lightweight, limited to the increase of fuselage weight.
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).
Be distributed with two row's thermovents (13) at the end face of each described cantilever (9), 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, rains even meet with when aircraft operation, and rainwater also can directly not waft and splash on electronic governor, thereby has effectively prevented electronic governor inefficacy.
Described posting (11) is elliptical annular sheet body structure, and is made up of 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, intensity high, not yielding or damage; And angle of bend is little, aseismicity is good.
Beneficial effect: the utility model moulding is simple, and processing and fabricating is easy, lightweight, structural strength is good; The medicine-chest of splendid attire liquid is integrated in fuselage, can reduce costs, and reduces the height dimension of fuselage, and can prevent that liquid from rocking, and guarantees the balance of aircraft.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.
Brief description of the drawings
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.
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 and Figure 2, fuselage is made up 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 are made up of 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.Wherein, equipment compartment 8 is positioned at midway location, and equipment compartment 8 upper ends have circular port lower end closed, the inside of this equipment compartment 8 is separated into the equipment cavity of top and the liquid cavity of below by transverse slat 14, middle part at transverse slat 14 has dosing mouth, and the tegillum 15 that shape size adapts is with it installed at this dosing mouth place.In described liquid cavity, be fixedly installed " well " font dividing plate 16, dividing plate 16 is made up of cellular composite material, thickness is 3-5mm, and liquid cavity is separated into nine chambers by this dividing plate 16, laterally and longitudinally goes up the through hole of offering by dividing plate 16 bottoms between two adjacent chamber and is communicated with.Be provided with four cantilevers 9 that distribute by even circumferential in the periphery of described equipment compartment 8, this cantilever 9 is hollow structure, and 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.Be provided with motor bin 10 in the outer end of each cantilever 9, 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 cross-sectional plane of cantilever 9 reduces to the direction of motor bin 10 gradually from equipment compartment 8.
As shown in Figure 1 and Figure 2, in the inner position near equipment compartment 8 of each described cantilever 9, two postings that are parallel to each other 11 are all installed, 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 up of 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 up of aviation laminate, is evenly distributed with circular louvre on base plate 12, and on this base plate 12, electronic governor 7 is installed.Be distributed with two platoon leader's bar shaped thermovents 13 at the end face of each described cantilever 9, 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, be provided with the top cover 1 adapting with it at the opening part at equipment compartment 8 tops, top cover 1 is preferably made up of 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 is interlocked by the step at edge and the opening at equipment compartment 8 tops.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 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, 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 equipment compartment 8 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 (7)
1. a four-axle type flight instruments integrated form fuselage, comprise fuselage, top cover (1) and electronic governor (7), it is characterized in that: described fuselage is by equipment compartment (8), cantilever (9) and motor bin (10) composition, described equipment compartment (8) is positioned at midway location, the inside of this equipment compartment (8) is separated into the equipment cavity of top and the liquid cavity of below by transverse slat (14), middle part at transverse slat (14) has dosing mouth, the tegillum (15) that shape size adapts is with it installed at this dosing mouth place, in described liquid cavity, be fixedly installed " well " font dividing plate (16), liquid cavity is separated into nine chambers by this dividing plate (16), laterally and longitudinally going up the through hole of offering by dividing plate (16) bottom between two adjacent chamber is communicated with, be provided with four cantilevers (9) that distribute by even circumferential in the periphery of described equipment compartment (8), 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 is provided with motor bin (10) in the outer end of each cantilever (9), described equipment compartment (8), cantilever (9) and motor bin (10) are structure as a whole, formed 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, in the inner position near equipment compartment (8) of each described cantilever (9), two postings that are parallel to each other (11) are all installed, in these two postings (11), intert and be fixed with a base plate (12), electronic governor (7) is installed on this base plate (12), be provided with the top cover (1) adapting with it at the opening part at equipment compartment (8) top, 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, 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 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 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. four-axle type flight instruments integrated form fuselage according to claim 1, is characterized in that: described dividing plate (16) is made up of cellular composite material, and thickness is 3-5mm.
3. four-axle type 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 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 equipment compartment (8) phase clamping.
4. four-axle type 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).
5. four-axle type 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).
6. four-axle type flight instruments integrated form fuselage according to claim 1, it is characterized in that: be distributed with two row's thermovents (13) at the end face of each described cantilever (9), 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).
7. four-axle type 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 up of aviation laminate, and the thickness of posting (11) is 2-4mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420137917.1U CN203793591U (en) | 2014-03-26 | 2014-03-26 | Integrated type fuselage of four-axle type flying device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420137917.1U CN203793591U (en) | 2014-03-26 | 2014-03-26 | Integrated type fuselage of four-axle type flying device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203793591U true CN203793591U (en) | 2014-08-27 |
Family
ID=51375831
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420137917.1U Expired - Fee Related CN203793591U (en) | 2014-03-26 | 2014-03-26 | Integrated type fuselage of four-axle type flying device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203793591U (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 CN201420137917.1U patent/CN203793591U/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 |