CN203793616U - Body assembly on four-axis aerial vehicle - Google Patents
Body assembly on four-axis aerial vehicle Download PDFInfo
- Publication number
- CN203793616U CN203793616U CN201420138745.XU CN201420138745U CN203793616U CN 203793616 U CN203793616 U CN 203793616U CN 201420138745 U CN201420138745 U CN 201420138745U CN 203793616 U CN203793616 U CN 203793616U
- Authority
- CN
- China
- Prior art keywords
- cantilever
- equipment compartment
- top cover
- block assembly
- axle type
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a body assembly on a four-axis aerial vehicle. The body assembly 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); 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 body assembly has the beneficial effects that the body assembly has simple body shape, small volume and reliable strength, is easy to machine and is light; a medicine kit for containing liquor is integrated in a body, so that the cost can be reduced, the height of the body can be reduced, the liquor can be prevented from wobbling, and the balance of the aerial vehicle can be ensured.
Description
Technical field
The utility model belongs to agricultural vehicle technology field, specifically, and the particularly block assembly 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, 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.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; When 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, it is firm to connect, can effectively prevent that liquid from rocking four-axle type flight instruments block assembly.
The technical solution of the utility model is as follows: a kind of four-axle type flight instruments block assembly, 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, 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), this dividing plate (16) is separated into nine chambers by liquid cavity, laterally and longitudinally going up the through hole of offering by dividing plate (16) bottom between two adjacent chamber is communicated with, in the periphery of described 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 equipment cavity 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 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 medicine-chest like this, 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 normally pumping of liquid so on the one hand, 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 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.
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.
Described dividing plate (16) is made by 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.
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 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.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.
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, 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 by cellular composite material, thickness is 3-5mm, and this dividing plate 16 is separated into nine chambers by liquid cavity, laterally and longitudinally goes up the through hole of offering by dividing plate 16 bottoms between two adjacent chamber and is communicated with.
As shown in Figure 1 and Figure 2, in the periphery of described 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, the inside of motor bin 10 communicates with the equipment cavity 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 (9)
1. a four-axle type flight instruments block assembly, 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, 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), this dividing plate (16) is separated into nine chambers by liquid cavity, laterally and longitudinally going up the through hole of offering by dividing plate (16) bottom between two adjacent chamber is communicated with, in the periphery of described 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 equipment cavity 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.
2. four-axle type flight instruments block assembly according to claim 1, is characterized in that: described dividing plate (16) is made by cellular composite material, and thickness is 3-5mm.
3. four-axle type flight instruments block assembly 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. four-axle type flight instruments block assembly 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 block assembly 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. four-axle type flight instruments block assembly according to claim 1 or 5, 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.
7. four-axle type flight instruments block assembly 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.
8. four-axle type flight instruments block assembly according to claim 7, is characterized in that: described base plate (12) is made by aviation laminate, and be evenly distributed with circular louvre on base plate (12).
9. four-axle type flight instruments block assembly according to claim 1, 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 |
|---|---|---|---|
| CN201420138745.XU CN203793616U (en) | 2014-03-26 | 2014-03-26 | Body assembly on four-axis aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420138745.XU CN203793616U (en) | 2014-03-26 | 2014-03-26 | Body assembly on four-axis aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203793616U true CN203793616U (en) | 2014-08-27 |
Family
ID=51375856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420138745.XU Expired - Fee Related CN203793616U (en) | 2014-03-26 | 2014-03-26 | Body assembly on four-axis aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203793616U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863552A (en) * | 2014-03-26 | 2014-06-18 | 重庆金泰航空工业有限公司 | Four-shaft type flight device body assembly |
-
2014
- 2014-03-26 CN CN201420138745.XU patent/CN203793616U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863552A (en) * | 2014-03-26 | 2014-06-18 | 重庆金泰航空工业有限公司 | Four-shaft type flight device body assembly |
| CN103863552B (en) * | 2014-03-26 | 2016-08-24 | 重庆金泰航空工业有限公司 | A kind of four-axle type flight instruments block assembly |
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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 |