CN203793602U - Top cover positioning structure on four-axis aerial vehicle - Google Patents

Abstract

The utility model discloses a top cover positioning structure on a four-axis aerial vehicle. The top cover positioning structure is characterized in that the interior of an equipment compartment (8) is separated into an upper equipment cavity and a lower liquor cavity by a diaphragm (14); a motor compartment (10) is arranged at the outer end of each cantilever (9); two positioning frames (11) parallel to each other are installed inside each cantilever (9); a fixture block (2) and two positioning seats (3) are fixed on the bottom surface of a 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 top cover positioning structure not only can effectively prevent liquor from wobbling and conveniently and rapidly open and close the top cover but also takes full advantage of the space of the cantilevers and enables an electronic speed governor to be removed and installed conveniently and rapidly and the usability to be guaranteed.

Description

Four-axle type flight instruments top cover location structure

Technical field

The utility model belongs to agricultural vehicle technology field, specifically, and the particularly top cover location structure 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 a kind of folding with convenience, is convenient to install, can effectively prevent the four-axle type flight instruments top cover location structure that liquid rocks.

The technical solution of the utility model is as follows: a kind of four-axle type flight instruments top cover location structure, comprise top cover (1) and fuselage (7), described fuselage is made up of carbon fiber composite material, and 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 axial line of the axial line of cantilever (9) and equipment compartment (8) is perpendicular, 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 described motor bin (10) and equipment compartment (8), 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), be provided with the top cover (1) adapting with it at the opening part at described equipment compartment (8) top, described top cover (1) is the spherical structure that central high rim is low, and made by carbon fiber composite material, 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 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 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 equipment compartment top end opening, top cover is carried out on equipment compartment 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 equipment compartment top, and equipment compartment 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 equipment compartment 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.

Fuselage of the present utility model 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 fuselage.The utility model can be arranged on electronic governor cantilever inside, 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.Design of cover is become spherical structure by the utility model, 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 up of 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.

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 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 base plate (12).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.

In order to beautify outward appearance in guaranteeing product in-use performance, can and to alleviate the weight of fuselage to the greatest extent, the outline of described cantilever (9) cross-sectional plane be ellipse, and the cross-sectional plane of cantilever (9) reduces to the direction of motor bin (10) gradually from equipment compartment (8).

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.

Described base plate (12) is made up of aviation laminate, intensity is high, waterproof property and aseismicity good; On base plate (12), be evenly distributed with circular louvre, in 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 top cover and fuselage are made by carbon fiber 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; 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.Electronic governor can be arranged in cantilever inside, and the supporting construction being made up of posting and base plate positions, and can make full use of on the one hand the space of cantilever, does not affect the layout of other parts on aircraft; On the other hand, electronic governor dismounting is convenient, good heat dissipation effect, and in-use performance is secure.

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, Figure 2, Figure 3 and Figure 4, the utility model is made up of top cover 1 and fuselage 7 two large divisions, and described fuselage 7 is made up of carbon fiber composite material, and is made up of equipment compartment 8, cantilever 9 and motor bin 10.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 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.Be provided with motor bin 10 in the outer end of each cantilever 9, the axis parallel of the axial line of described 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, 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 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, and is evenly distributed with circular louvre on base plate 12.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 base plate 12.

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 the spherical structure that central high rim is low, is also preferably made up of carbon fiber composite material.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 (8)

1. a four-axle type flight instruments top cover location structure, comprise top cover (1) and fuselage (7), it is characterized in that: described fuselage is made up of carbon fiber composite material, and 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 axial line of the axial line of cantilever (9) and equipment compartment (8) is perpendicular, 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 described motor bin (10) and equipment compartment (8), 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), be provided with the top cover (1) adapting with it at the opening part at described equipment compartment (8) top, described top cover (1) is the spherical structure that central high rim is low, and made by carbon fiber composite material, 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 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 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 top cover location structure 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 top cover location 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 equipment compartment (8) phase clamping.

4. four-axle type flight instruments top cover location 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).

5. four-axle type flight instruments top cover location structure 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 base plate (12).

6. four-axle type flight instruments top cover location structure according to claim 1 or 5, it is characterized in that: the outline of described cantilever (9) cross-sectional plane is for oval, and the cross-sectional plane of cantilever (9) reduces to the direction of motor bin (10) gradually from equipment compartment (8).

7. four-axle type flight instruments top cover location structure 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.

8. four-axle type flight instruments top cover location structure according to claim 7, is characterized in that: described base plate (12) is made up of aviation laminate, and be evenly distributed with circular louvre on base plate (12).