CN203461088U - Four-shaft farm-oriented unmanned aircraft fuselage positioning structure - Google Patents
Four-shaft farm-oriented unmanned aircraft fuselage positioning structure Download PDFInfo
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- CN203461088U CN203461088U CN201320567905.8U CN201320567905U CN203461088U CN 203461088 U CN203461088 U CN 203461088U CN 201320567905 U CN201320567905 U CN 201320567905U CN 203461088 U CN203461088 U CN 203461088U
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- locating piece
- fuselage
- lower locating
- equipment compartment
- unmanned vehicle
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Abstract
The utility model discloses a four-shaft farm-oriented unmanned aircraft fuselage positioning structure. The four-shaft farm-oriented unmanned aircraft fuselage positioning structure is characterized in that an undercarriage (13) is provided with two supporting pipes (14) which are mutually parallel, an equipment bin (15) of a fuselage (12) is positioned on a middle position, and each supporting pipe (14) of the undercarriage (13) is connected with the equipment bin (15) through two fasteners; the periphery of the equipment bin (15) is provided with four cantilevers (16) which are uniformly distributed according to the circumference, an axial lead of each cantilever (16) is mutually perpendicular to an axial lead of the equipment bin (15), the outer end of each cantilever (16) is provided with a motor bin (17), and an axial lead of each motor bin (17) and the axial lead of the equipment bin (15) are parallel. The four-shaft farm-oriented unmanned aircraft fuselage positioning structure provided by the utility model has the advantages that the size is small, the process and making are easy, the firm connection of a farm-oriented aircraft undercarriage and a fuselage is realized, the undercarriage is convenient to dismount, a pesticide tank is rapidly changed, and the operation efficiency of an aircraft is effectively improved.
Description
Technical field
The utility model belongs to agricultural vehicle technology field, specifically, and the particularly fuselage location structure on the agricultural unmanned vehicle 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.Existing agricultural unmanned vehicle complex structure, bulky, weight is heavier, seriously restricted it and applied on a large scale.Take fuselage as example, and fuselage is agricultural carry-on vitals, but existing fuselage weight and volume is large, structural strength is poor, easily damage not only, and processing and fabricating is more difficult.In addition, although the connection structure between agricultural unmanned vehicle alighting gear and fuselage is comparatively firm, dismounting complex operation, and must be by instrument, not only time-consuming but also effort; Agricultural aircraft when operation, after medicine liquid spray in medicine-chest is complete, must be undertaken again by the filling exit arranging on medicine-chest filling after subjob again, will greatly reduce the operating efficiency of aircraft like this.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of lightweight, the agricultural unmanned vehicle fuselage of four axles location structure that can easy disassembly.
The technical solution of the utility model is as follows: the agricultural unmanned vehicle fuselage of a kind of four axle location structure, comprise alighting gear (13) and fuselage (12), described alighting gear (13) has two support tubes that are parallel to each other (14), described fuselage (12) is comprised of equipment compartment (15), cantilever (16) and motor bin (17), described equipment compartment (15) is positioned at midway location, this equipment compartment (15) is the cydariform of the uncovered lower end closed in upper end, and the every support tube (14) of alighting gear (13) is connected with equipment compartment (15) by two fasteners; In the periphery of described equipment compartment (15), be provided with four cantilevers (16) that distribute by even circumferential, the axial line of the axial line of this cantilever (16) and equipment compartment (15) is perpendicular, the ring wall of the inner of described cantilever (16) and equipment compartment (15) is connected as a single entity, in the outer end of each cantilever (16), be provided with motor bin (17), the axis parallel of the axial line of described motor bin (17) and equipment compartment (15).
Equipment compartment in the utility model is cydariform, handsome in appearance, and height dimension is little, and inner space is large, the electronic governor of autopilot and control Teat pipette can be installed in equipment compartment, and can distinguish mounted motor in four motor bins.The utility model adopts above technical scheme, and not only moulding is simple, processing and fabricating easy, productive costs is lower, and weight is lighter, and volume is small and exquisite.Two support tubes that are parallel to each other are fixed support to the fuselage of agricultural aircraft jointly, support the good stability of whole agricultural aircraft.
Described fastener has upper locating piece (1) and lower locating piece (2), upper locating piece (1) is secured by bolts in the bottom surface of fuselage (12), the middle part of upper locating piece (1) bottom surface is provided with positioning groove (1a), in the below of upper locating piece (1), lower locating piece (2) is set, the middle part of this lower locating piece (2) end face is provided with lower positioning groove (2a), on, lower locating piece (1, 2) upper by what cooperatively interact, lower positioning groove (1a, 2a) support tube (14) is held tightly, the corresponding end of one end of described upper locating piece (1) and lower locating piece (2) is hinged, the other end at upper locating piece (1) and lower locating piece (2) is equipped with opening, and in the opening of described upper locating piece (1), be provided with lateral pin (3), in the below of described lower locating piece (2), be provided with a handle (6), one end of this handle (6) has two collars that are arranged side by side (7), two collars (7) are all sleeved on pin (5) prejudicially, the lower end of the middle part of described pin (5) and connecting rod (4) fixes, the upper end of connecting rod (4) is through opening and the lateral pin (3) of lower locating piece (2), screw thread fit between connecting rod (4) and lateral pin (3), between the described collar (7) and lower locating piece (2), be provided with pressure ring (8), it is upper that this pressure ring (8) is sleeved on connecting rod (4), and described pressure ring (8) is subject to the compressing of the collar (7) heavy wall end, is pressed on the bottom surface of lower locating piece (2).
Adopt above technical scheme, between two support tubes of alighting gear and fuselage by all around totally four fasteners link together: the upper locating piece of fastener is secured by bolts in the bottom of fuselage, upper locating piece and lower locating piece are held the support tube of alighting gear tightly by the positioning groove up and down cooperatively interacting, and medicine-chest is fixed on alighting gear.
The utility model is to realize like this assembling: when initial, lower locating piece is connected with upper locating piece by pin jointed end, and the open end of lower locating piece naturally droops, first fuselage is positioned on alighting gear, making four of fuselage bottom upper locating pieces is that one group of upper positioning groove by separately straddles on corresponding alighting gear support tube between two, then rotate lower locating piece, the end face of lower locating piece is gone to the bottom surface of upper locating piece to be approached or laminating, the upper positioning groove of the lower positioning groove of lower locating piece and upper locating piece forms a circular hole, upper and lower locating piece is embraced the support tube of alighting gear by this circular hole, then turning handle in horizontal surface, handle drivening rod is rotated with respect to lateral pin, connecting rod is together with pressure ring upward movement, when pressure ring is pressed close to the bottom surface of lower locating piece, the handle of raising one's hand in vertical plane, the pin around connecting rod lower end rotates together with cover to make handle, due to the collar and the installation of pin employing eccentric manner, when the heavy wall end of the collar turns to vertex, can realize self-locking, make the heavy wall end of the collar by pressure ring, tightly oppress the bottom surface of lower locating piece, thereby it is loosening to prevent that lower locating piece and connecting rod from occurring.
After medicine liquid spray in operation process in medicine-chest, agricultural aircraft drop to assigned address, with hand, pull each handle downwards, handle is rotated down around pin, handle turns over after 180 °, the thin-walled end of the collar turns to extreme higher position, unclamp the compressing to pressure ring, turning handle in horizontal surface again, handle drivening rod is rotated with respect to lateral pin, connecting rod moves downward together with pressure ring, until pressure ring gets out of the way the bottom surface of lower locating piece open end, this at present the open end of locating piece naturally droop, unclamp holding tightly alighting gear, alighting gear can be pulled down from fuselage together with empty medicine-chest downwards, and can on fuselage, change the outfit at once and fill medicine-chest and the alighting gear of liquid according to mounting means.
In sum, the utility model can be realized being connected between alighting gear and fuselage, and not only fixing is good, and easy accessibility, quick, need to can not complete by instrument, not only simply but also laborsaving, change like this medicine-chest very convenient, can greatly improve the operating efficiency of agricultural aircraft.
Described cantilever (16) is hollow structure, and the direction of the cross section of this cantilever (16) from equipment compartment (15) to motor bin (17) reduces gradually, and this structure can guarantee the in-use performance of product, can alleviate again the weight of product.
Middle part in described motor bin (17) upper end has a via hole (18), and eight louvres (19) that distribute by even circumferential are looped around the periphery of described via hole (18); The lower end of described motor bin (17) has the in-flanges (20) of annular arrangement, at the center of this in-flanges (20), is formed with knock hole (21).Above structure can facilitate motor assembling and power output; Eight louvres are conducive to distribute the heat producing in machine operation process, to guarantee the in-use performance of motor.
In order to facilitate selection, and on the basis that guarantees product in-use performance expendable weight, cost-saving, described support tube (14) is made by aviation aluminum pipe, the external diameter of this support tube (14) is 28mm, wall thickness is 1～1.5mm.
In order to beautify outward appearance on the basis guaranteeing in-use performance, strengthen resistance to abrasion, to save production cost, the outside face of described support tube (14) is formed with protective layer by plastic-blasting, and the thickness of protective layer is 0.1mm.
For wear prevention and increase friction, further to improve the reliability of self-locking, between the described collar (7) and pressure ring (8), be provided with packing ring (9), this packing ring (9) is made by rubber, and is located on connecting rod (4).
In order to make structure compacter, and convenience and the fastness of increase connection, one side of described upper locating piece (1) end is formed with the first journal stirrup (10), the opposite side of described lower locating piece (2) corresponding end is formed with the second journal stirrup (11), described the first journal stirrup (10) fits together side by side with the second journal stirrup (11), and is hinged by bolt.
Described upper locating piece (1) and lower locating piece (2) are made by aviation aluminium, and selection is convenient like this, and cost is low, and lightweight, intensity is reliable.
Beneficial effect: the utility model volume is little, weight is light, processing and fabricating is easy, can realize firm connection the between agricultural unmanned vehicle alighting gear and fuselage, and by alighting gear is carried out to easy disassembly, can to medicine-chest, change fast, thereby effectively improved the operating efficiency of aircraft, have simple in structure, dismounting simple operation, transformation easily, the feature such as improvement cost is low.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is the schematic diagram that alighting gear is connected with fuselage by fastener.
Fig. 4 is the lateral plan of Fig. 3.
Fig. 5 is the structural representation of fastener.
Fig. 6 is the lateral plan of Fig. 5.
Fig. 7 is the structural representation of upper locating piece.
Fig. 8 is the upward view of Fig. 7.
Fig. 9 is the structural representation of lower locating piece.
Figure 10 is the birds-eye view of Fig. 9.
The specific embodiment
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 comprised of alighting gear 13, fuselage 12 and fastener three parts, and described alighting gear 13 has two support tubes that are parallel to each other 14, and each support tube 14 is supported by corresponding bottom tube.Described fuselage 12 is comprised of equipment compartment 15, cantilever 16 and motor bin 17, and described equipment compartment 15 is positioned at midway location, and this equipment compartment 15 is the cydariform of the uncovered lower end closed in upper end.In the periphery of described equipment compartment 15, be provided with four cantilevers 16 that distribute by even circumferential, this cantilever 16 is hollow structure, the cross section of this cantilever 16 direction from inside to outside reduces gradually, the axial line of the axial line of described cantilever 16 and equipment compartment 15 is perpendicular, and the ring wall of the inner of described cantilever 16 and equipment compartment 15 is connected as a single entity; In the outer end of each cantilever 16, be provided with motor bin 17, the axis parallel of the axial line of described motor bin 17 and equipment compartment 15, at the middle part of described motor bin 17 upper ends, have the periphery that 18, eight louvres 19 that distribute by even circumferential of a via hole are looped around described via hole 18; The lower end of described motor bin 17 has the in-flanges 20 of annular arrangement, at this in-flanges 20 center, is formed with knock hole 21.
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, described support tube 14 is made by aviation aluminum pipe, and its external diameter is preferably 28mm, and wall thickness is 1～1.5mm.Outside face at described support tube 14 is formed with protective layer by plastic-blasting, and the thickness of protective layer is 0.1mm.Described fuselage 12 is positioned at the top of support tube 14, and every support tube 14 is connected with fuselage 12 by two fasteners, four fasteners in same level by the rectangular distribution.
As shown in Figures 3 to 10, described fastener has upper locating piece 1 and lower locating piece 2, upper locating piece 1 is secured by bolts in the bottom surface of fuselage 12, upper locating piece 1 and lower locating piece 2 are all block structures of being made by aviation aluminium, upper locating piece 1 is positioned at the top of lower locating piece 2, middle part in upper locating piece 1 bottom surface is provided with positioning groove 1a, and on this, positioning groove 1a is arc top half slot upward.At the middle part of lower locating piece 2 end faces, be provided with lower positioning groove 2a, this lower positioning groove 2a is arc top half slot down, and lower positioning groove 2a and upper positioning groove 1a can form a circular hole, upper and lower locating piece 1,2 is held support tube 14 tightly by the upper and lower positioning groove 1a, the formed circular hole of 2a that cooperatively interact.
As shown in Figures 3 to 10, a side in upper locating piece 1 end is formed with the first journal stirrup 10, the opposite side of lower locating piece 2 corresponding end is formed with the second journal stirrup 11, and described the first journal stirrup 10 and the second journal stirrup 11 fit together side by side, and are hinged by bolt.At upper locating piece 1, away from one end of the first journal stirrup 10, have the first opening 1b, lower locating piece 2 has the second opening 2b away from one end of the second journal stirrup 11, and the second opening 2b is corresponding with the first opening 1b, and both width are substantially equal.On described, in the first opening 1b of locating piece 1, be provided with lateral pin 3, two of this lateral pin 3 is stretched into and is fixed in locating piece 1.
As shown in Figures 3 to 10, be provided with a handle 6 below described lower locating piece 2, one end of this handle 6 is formed with 7, two collars 7 of two collars that are arranged side by side and is all sleeved on prejudicially on pin 5, and the bottom of two collars 7 is connected as a single entity.The lower end of the middle part of described pin 5 and connecting rod 4 fixes, and the axial line of the axial line of pin 5 and connecting rod 4 is perpendicular, and the upper end of connecting rod 4 is through the second opening 2b and the lateral pin 3 of lower locating piece 2, screw thread fit between connecting rod 4 and lateral pin 3.Between the described collar 7 and lower locating piece 2, be provided with pressure ring 8, this pressure ring 8 is sleeved on connecting rod 4, and described pressure ring 8 is subject to the compressing of the collar 7 heavy wall ends, is pressed on the bottom surface of lower locating piece 2.Between the described collar 7 and pressure ring 8, be also provided with packing ring 9, this packing ring 9 is made by rubber, and packing ring 9 is also located on connecting rod 4.
Principle of work of the present utility model is as follows:
When initial, the lower locating piece 2 of four fasteners is connected with corresponding upper locating piece 1 by pin jointed end, and the open end of lower locating piece 2 naturally droops, first fuselage 12 is positioned on alighting gear 13, making four of fuselage 12 bottoms upper locating pieces 1 is that one group of upper positioning groove 1a by separately straddles on corresponding alighting gear support tube 14 between two, then rotate lower locating piece 2, the end face of lower locating piece 2 is gone to the bottom surface of upper locating piece 1 to be approached or laminating, the upper positioning groove 1a of the lower positioning groove 2a of lower locating piece 2 and upper locating piece 1 forms a circular hole, upper and lower locating piece is embraced the support tube of alighting gear 14 by this circular hole, then turning handle 6 in horizontal surface, make handle 6 drivening rods 4 with respect to lateral pin 3 rotations, connecting rod 4 is together with pressure ring 8 upward movements, when pressure ring 8 is pressed close to the bottom surface of lower locating piece 2, the handle 6 of raising one's hand in vertical plane, the pin 5 around connecting rod 4 lower ends rotates together with the collar 7 to make handle 6, because the collar 7 and pin 5 adopt eccentric manner to install, when the heavy wall end of the collar 7 turns to vertex, can realize self-locking, make the heavy wall end of the collar 7 pass through the bottom surface that pressure ring 8 is tightly oppressed lower locating piece 2, thereby prevent that lower locating piece 2 and connecting rod 4 from occurring loosening, complete the assembling of alighting gear 13 and fuselage 12.
After medicine liquid spray in operation process in medicine-chest, agricultural unmanned vehicle drop to assigned address, with hand, pull each handle 6 downwards, handle 6 is rotated down around pin 5, handle 6 turns over after 180 °, the thin-walled end of the collar 7 turns to extreme higher position, unclamp the compressing to pressure ring 8, turning handle 6 in horizontal surface again, make handle 6 drivening rods 4 with respect to lateral pin 3 rotations, connecting rod 4 moves downward together with pressure ring 8, until pressure ring 8 gets out of the way the bottom surface of lower locating piece 2 open ends, this at present the open end of locating piece 2 naturally droop, unclamp holding tightly alighting gear 14, alighting gear 14 can be pulled down from fuselage 12 together with empty medicine-chest downwards, and can on fuselage 12, change the outfit at once and fill medicine-chest and the alighting gear of liquid according to mounting means.
Claims (9)
1. the agricultural unmanned vehicle fuselage of an axle location structure, comprise alighting gear (13) and fuselage (12), described alighting gear (13) has two support tubes that are parallel to each other (14), it is characterized in that: described fuselage (12) is comprised of equipment compartment (15), cantilever (16) and motor bin (17), described equipment compartment (15) is positioned at midway location, this equipment compartment (15) is the cydariform of the uncovered lower end closed in upper end, and the every support tube (14) of alighting gear (13) is connected with equipment compartment (15) by two fasteners; In the periphery of described equipment compartment (15), be provided with four cantilevers (16) that distribute by even circumferential, the axial line of the axial line of this cantilever (16) and equipment compartment (15) is perpendicular, the ring wall of the inner of described cantilever (16) and equipment compartment (15) is connected as a single entity, in the outer end of each cantilever (16), be provided with motor bin (17), the axis parallel of the axial line of described motor bin (17) and equipment compartment (15).
2. the agricultural unmanned vehicle fuselage of four axle according to claim 1 location structure, it is characterized in that: described fastener has upper locating piece (1) and lower locating piece (2), upper locating piece (1) is secured by bolts in the bottom surface of fuselage (12), the middle part of upper locating piece (1) bottom surface is provided with positioning groove (1a), in the below of upper locating piece (1), lower locating piece (2) is set, the middle part of this lower locating piece (2) end face is provided with lower positioning groove (2a), on, lower locating piece (1, 2) upper by what cooperatively interact, lower positioning groove (1a, 2a) support tube (14) is held tightly, the corresponding end of one end of described upper locating piece (1) and lower locating piece (2) is hinged, the other end at upper locating piece (1) and lower locating piece (2) is equipped with opening, and in the opening of described upper locating piece (1), be provided with lateral pin (3), in the below of described lower locating piece (2), be provided with a handle (6), one end of this handle (6) has two collars that are arranged side by side (7), two collars (7) are all sleeved on pin (5) prejudicially, the lower end of the middle part of described pin (5) and connecting rod (4) fixes, the upper end of connecting rod (4) is through opening and the lateral pin (3) of lower locating piece (2), screw thread fit between connecting rod (4) and lateral pin (3), between the described collar (7) and lower locating piece (2), be provided with pressure ring (8), it is upper that this pressure ring (8) is sleeved on connecting rod (4), and described pressure ring (8) is subject to the compressing of the collar (7) heavy wall end, is pressed on the bottom surface of lower locating piece (2).
3. the agricultural unmanned vehicle fuselage of four axle according to claim 1 location structure, is characterized in that: described cantilever (16) is hollow structure, and the direction of the cross section of this cantilever (16) from equipment compartment (15) to motor bin (17) reduces gradually.
4. the agricultural unmanned vehicle fuselage of four axle according to claim 1 location structure, it is characterized in that: the middle part in described motor bin (17) upper end has a via hole (18), eight louvres (19) that distribute by even circumferential are looped around the periphery of described via hole (18); The lower end of described motor bin (17) has the in-flanges (20) of annular arrangement, at the center of this in-flanges (20), is formed with knock hole (21).
5. the agricultural unmanned vehicle fuselage of four axle according to claim 1 location structure, is characterized in that: described support tube (14) is made by aviation aluminum pipe, and the external diameter of this support tube (14) is 28mm, and wall thickness is 1～1.5mm.
6. the agricultural unmanned vehicle fuselage of four axles location structure according to claim 1 or 5, is characterized in that: the outside face of described support tube (14) is formed with protective layer by plastic-blasting, and the thickness of protective layer is 0.1mm.
7. the agricultural unmanned vehicle fuselage of four axle according to claim 2 location structure, is characterized in that: between the described collar (7) and pressure ring (8), be provided with packing ring (9), this packing ring (9) is made by rubber, and is located on connecting rod (4).
8. the agricultural unmanned vehicle fuselage of four axle according to claim 2 location structure, it is characterized in that: a side of described upper locating piece (1) end is formed with the first journal stirrup (10), the opposite side of described lower locating piece (2) corresponding end is formed with the second journal stirrup (11), described the first journal stirrup (10) fits together side by side with the second journal stirrup (11), and is hinged by bolt.
9. according to the agricultural unmanned vehicle fuselage of the four axles location structure described in claim 2 or 7 or 8, it is characterized in that: described upper locating piece (1) and lower locating piece (2) are made by aviation aluminium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320567905.8U CN203461088U (en) | 2013-09-13 | 2013-09-13 | Four-shaft farm-oriented unmanned aircraft fuselage positioning structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320567905.8U CN203461088U (en) | 2013-09-13 | 2013-09-13 | Four-shaft farm-oriented unmanned aircraft fuselage positioning structure |
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| Publication Number | Publication Date |
|---|---|
| CN203461088U true CN203461088U (en) | 2014-03-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320567905.8U Expired - Fee Related CN203461088U (en) | 2013-09-13 | 2013-09-13 | Four-shaft farm-oriented unmanned aircraft fuselage positioning structure |
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| CN (1) | CN203461088U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105547366A (en) * | 2015-12-30 | 2016-05-04 | 东北农业大学 | Miniaturized unmanned aerial vehicle crop information obtaining and fertilization irrigation guiding apparatus |
| CN106043673A (en) * | 2016-08-12 | 2016-10-26 | 成都恒胜达科技有限公司 | Unmanned plane landing in random terrain |
-
2013
- 2013-09-13 CN CN201320567905.8U patent/CN203461088U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105547366A (en) * | 2015-12-30 | 2016-05-04 | 东北农业大学 | Miniaturized unmanned aerial vehicle crop information obtaining and fertilization irrigation guiding apparatus |
| CN106043673A (en) * | 2016-08-12 | 2016-10-26 | 成都恒胜达科技有限公司 | Unmanned plane landing in random terrain |
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Granted publication date: 20140305 Termination date: 20170913 |