CN203461117U - Rotor wing of four-axis agricultural aircraft - Google Patents
Rotor wing of four-axis agricultural aircraft Download PDFInfo
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- CN203461117U CN203461117U CN201320548101.3U CN201320548101U CN203461117U CN 203461117 U CN203461117 U CN 203461117U CN 201320548101 U CN201320548101 U CN 201320548101U CN 203461117 U CN203461117 U CN 203461117U
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- blade
- positioning table
- motor
- root
- time positioning
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Abstract
The utility model discloses a rotor wing of a four-axis agricultural aircraft. Four cantilevers (4) which are uniformly distributed along the circumferential direction are arranged at the periphery of an equipment chamber (3); the outer end of each cantilever (4) is provided with a motor chamber (5); a central hole is formed in the center of an inner flanging (7) at the lower end of each motor chamber (5); a locating plate (9) is arranged at the bottom of a motor (6) arranged in each motor chamber (5); four supporting lugs (10) are uniformly distributed at the periphery of the locating plate (9); each supporting lug (9) is fixed together with the bottom of the inner flanging (7) through a first screw (8); a first blade (1) and a second blade (2) are arranged above each motor chamber (5), the roots of the two blades are staggered and connected in a clamping way, and the blades are fixedly arranged on output shafts of the motors (6). The rotor wing is simple in model and reliable in strength on one hand as well as convenient and rapid in mounting and dismounting on the other hand and has the characteristics of novel design, easiness for improvement, low improvement cost and the like.
Description
Technical field
The utility model belongs to agricultural vehicle technology field, specifically, and the particularly agricultural carry-on rotor 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.The agricultural carry-on rotor of take is example, and existing rotor not only assembles complexity, waste time and energy, and the space that rotor motor takies is large, can increase the height dimension of whole aircraft.In addition, screw propeller and electric motor mounting structure are complicated, and mounting process is loaded down with trivial details, and installation process wastes time and energy, and is unfavorable for saving production cost; Two blades of screw propeller are structure as a whole conventionally, packing and the space that takies of transport point is large, cost is high, and when there is the impaired situation of blade, screw propeller can only integral body be scrapped, thereby brings the waste of resource, has increased use cost.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of agricultural aircraft rotor of four axles convenient to disassembly.
The technical solution of the utility model is as follows: the agricultural aircraft rotor of a kind of four axle, comprise the first blade (1), the second blade (2), equipment compartment (3), cantilever (4), motor bin (5) and motor (6), described equipment compartment (3) is positioned at midway location, this equipment compartment (3) is the cydariform of the uncovered lower end closed in upper end, in the periphery of described equipment compartment (3), be provided with four cantilevers (4) that distribute by even circumferential, the axial line of the axial line of this cantilever (4) and equipment compartment (3) is perpendicular, the ring wall of the inner of described cantilever (4) and equipment compartment (3) is connected as a single entity, in the outer end of each cantilever (4), be provided with motor bin (5), the axis parallel of the axial line of described motor bin (5) and equipment compartment (3), the lower end of this motor bin (5) has the in-flanges (7) of annular arrangement, center at in-flanges (7) is formed with centre hole, in motor bin described in each (5), be provided with motor (6), the bottom of this motor (6) has dowel disc (9), the periphery of described dowel disc (9) is evenly distributed with four journal stirrups (10), each journal stirrup (10) fits with the bottom surface of in-flanges (7), and fixing by the first screw (8), in the top of each motor bin (5), be provided with the first blade (1) and the second blade (2) that by even circumferential, distribute, staggered being connected together of root of two blades, and be fixedly mounted on the output shaft of motor (6).
Equipment compartment in the utility model is cydariform, and cantilever is hollow structure, and this design is not only handsome in appearance, and height dimension is little, volume and weight is light, and inner space is large, and the electronic governor of autopilot and control Teat pipette can be installed in equipment compartment.The utility model is by motor arrangement in the motor bin of special setting, and motor is fixed by four screws, and mounting process is simple on the one hand, easy accessibility, quick; On the other hand, motor and motor bin compact conformation, take up room little, can effectively reduce the volume of aircraft.The utility model moulding is simple, and processing and fabricating is easy, and volume is small and exquisite; Not only light, the weight that can effectively alleviate aircraft of weight, and structural strength is reliable, be difficult for being damaged.
The utility model blade is set to split-type structural, after the staggered clamping of root of two blades, is arranged on the output shaft of motor, installs so on the one hand and dismantle not only convenient but also quick; On the other hand, can simplify the technique that two blades are connected with motor, make installation process time saving and energy saving, and can guarantee the fixing of connection.In addition, monolithic vane shared space in packing and transportation is less, and the cost of packing and transportation is lower; If in use certain piece blade is damaged, only needs this blade exchanging, and needn't scrap by whole screw propeller, thereby effectively reduce use cost.
Root at described the first blade (1) offers the first opening (11) along its length, this first opening (11) by the root of the first blade (1) be divided into up and down dislocation first on positioning table (12) and first time positioning table (13), root at described the second blade (2) offers the second opening (11 ') along its length, this second opening (11 ') by the root of the second blade (2) be divided into up and down dislocation second on positioning table (12 ') and second time positioning table (13 '), described the first blade (1) first on positioning table (12) be superimposed upon the second blade (2) second time positioning table (13 ') above, the second blade (2) second on positioning table (12 ') be superimposed upon the first blade (1) first time positioning table (13) above, make staggered being connected together of root of two blades.Above structure not only moulding is simple, and processing and fabricating is easy, and two blade pass cross positioning table dislocation clamping, and dismounting is convenient, connects not only firmly but also reliable.
For convenient location, make to assemble faster, on the opposite face of positioning table on described first (12) and first time positioning table (13), all offer semi-round first breach (14), on second, on the opposite face of positioning table (12 ') and second time positioning table (13 '), all offer semi-round second breach (14 '), the first breach (14) and the second breach (14 ') on two blades form a knock hole jointly; On the output shaft of described motor (6), set firmly a locating dowel pin (17), this locating dowel pin (17) is from lower to upper through two formed knock holees of root of blade.
In order to realize two blades, be connected with the firm of motor output shaft, on positioning table on described first (12) and first time positioning table (13), be respectively arranged with a plurality of the first mounting holes (18), on second, on positioning table (12 ') and second time positioning table (13 '), be respectively arranged with a plurality of the second mounting holes (18 '), the first mounting hole (18) on positioning table on first (12) lay respectively at the second mounting hole (18 ') on second time positioning table (13 ') directly over, the second mounting hole (18 ') on second on positioning table (12 ') lay respectively at the first mounting hole (18) on first time positioning table (13) directly over, above mounting hole forms a plurality of assembly openings that distribute by even circumferential, the second screw (19) passes this assembly opening and stretches in the output shaft of motor (6), the output shaft of two blades and motor (6) is fixed together.
Top in described the first blade (1) and the second blade (2) root junction is pressed with platen (20), and the position of the corresponding assembly opening of this platen (20) is equipped with via hole, in the via hole of the second screw (19) from platen (20), passes.This design can by two blades, the output shaft with motor connects more securely.
Described the first blade (1) and the second blade (2) are sabre shape.This designs not only good looking appearance, and has good in-use performance.
In order to beautify outward appearance when guaranteeing product in-use performance, can also to alleviate the weight of fuselage to the greatest extent, described cantilever (4) is hollow structure, and the direction of the cross section of described cantilever (4) from equipment compartment (3) to motor bin (5) reduces gradually.
Described journal stirrup (10) is semicircle, and is structure as a whole with dowel disc (9).This structure can make journal stirrup more firm with being connected of dowel disc.
Beneficial effect: the utility model on the one hand light, the intensity of simple, the compact conformation of moulding, weight reliably, not fragile; On the other hand, the installing/dismounting of motor and screw propeller is not only convenient but also quick, is conducive to packed and transported and the replacing of blade, has the features such as modern design, simple in structure, transformation is easy, improvement cost is low, all applicable on various types of aircraft.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is two birds-eye vieies after blade assembling.
Fig. 3 is the layout schematic diagram of two blades.
Fig. 4 is the structural representation of the first blade.
Fig. 5 is the structural representation of the second blade.
Fig. 6 is the A-A cutaway view of Fig. 4.
Fig. 7 is the B-B cutaway view of Fig. 5.
Fig. 8 is staggered schematic diagram after two root of blade docking.
Fig. 9 is the structural representation of fuselage.
Figure 10 is the connection diagram of two blades and motor output shaft.
Figure 11 is the birds-eye view of motor bin.
Figure 12 is the upward view of Figure 10.
The specific embodiment
Below in conjunction with drawings and Examples, the utility model is described in further detail:
As shown in Fig. 1-Figure 12, the utility model consists of the first blade 1, the second blade 2, equipment compartment 3, cantilever 4, motor bin 5, motor 6, dowel disc 9 and platen 20 etc.Wherein, equipment compartment 3 is positioned at midway location, and this equipment compartment 3 is the cydariform of the uncovered lower end closed in upper end, and is comprised of ring wall and diapire.In the periphery of described equipment compartment 3, be provided with four cantilevers 4 that distribute by even circumferential, this cantilever 4 is hollow structure, and the cross section of cantilever 4 reduces gradually from the inner direction toward outer end.The axial line of the axial line of described cantilever 4 and equipment compartment 3 is perpendicular, and the ring wall of the inner of cantilever 4 and equipment compartment 3 is connected as a single entity, and in the outer end of each cantilever 4, is provided with motor bin 5, the axis parallel of the axial line of this motor bin 5 and equipment compartment 3.Described equipment compartment 3, cantilever 4 and motor bin 5 are structure as a whole, and by carbon fiber composite material, are made.The in-flanges 7 in the lower end of motor bin 5 with annular arrangement, the center of this in-flanges 7 is formed with centre hole, described in each, in motor bin 5, be provided with motor 6, the bottom of this motor 6 has dowel disc 9, the periphery of described dowel disc 9 is evenly distributed with four journal stirrups 10, and this journal stirrup 10 is semicircle, and is structure as a whole with dowel disc 9, each journal stirrup 10 fits with the bottom surface of in-flanges 7, and fixing by the first screw 8 wearing from the bottom up.
As shown in Fig. 1-Figure 12, above each motor bin 5, be provided with two blades, be respectively the first blade 1 and the second blade 2, and the first blade 1 and the second blade 2 are pressed even circumferential and are distributed.Described the first blade 1 and the second blade 2 are all preferably sabre shape, and make by carbon fiber composite material.Root at described the first blade 1 offers the first opening 11 along its length, this first opening 11 by the root of the first blade 1 be divided into up and down dislocation first on positioning table 12 and first time positioning table 13.Root at described the second blade 2 offers the second opening 11 ' along its length, this second opening 11 ' by the root of the second blade 2 be divided into up and down dislocation second on positioning table 12 ' and second time positioning table 13 ', described the first blade 1 first on positioning table 12 be superimposed upon the second blade 2 second time positioning table 13 ' above, the second blade 2 second on positioning table 12 ' be superimposed upon above first time positioning table 13 of the first blade 1, the first blade 1 and the second blade 2 are connected together by root positioning table is staggered.Described the first blade 1 first on the bottom surface of positioning table 12 and the end face of first time positioning table 13 substantially concordant, described the second blade 2 second on the bottom surface of positioning table 12 ' and the end face of second time positioning table 13 ' substantially concordant.
As shown in Fig. 1-Figure 12, on described first, on the opposite face of positioning table 12 and first time positioning table 13, all offer semi-round first breach 14, the first breach 14 and the second breach 14 ' that on second, on the opposite face of positioning table 12 ' and second time positioning table 13 ', all offer on 14 ', two blades of semi-round second breach form a knock hole jointly; At the middle part of described motor bin 5 upper ends, have the periphery that 15, eight louvres 16 that distribute by even circumferential of a via hole are looped around described via hole 15; The output shaft of motor 6 is upward through via hole 15, on the output shaft of motor 6, set firmly a locating dowel pin 17, point-blank, this locating dowel pin 17 is from lower to upper through two formed knock holees of root of blade for the axial line of the axial line of described locating dowel pin 17 and motor 6 output shafts.
As shown in Fig. 1-Figure 12, on described first, on positioning table 12 and first time positioning table 13, be respectively arranged with a plurality of the first mounting holes 18, in the present embodiment, 3 the first mounting holes 18 are preferably set respectively on positioning table 12 and first time positioning table 13 on first; On second, on positioning table 12 ' and second time positioning table 13 ', be respectively arranged with a plurality of the second mounting holes 18 ', in the present embodiment, on positioning table 12 ' and second time positioning table 18 ', 3 mounting holes be preferably set respectively on second.The first mounting hole 18 on first on positioning table 12 lay respectively at the second mounting hole 18 ' on second time positioning table 13 ' directly over, the second mounting hole 18 ' on second on positioning table 12 ' lay respectively at the first mounting hole 18 on first time positioning table 13 directly over, above 6 mounting holes form the assembly opening of press even circumferential distribution.
As shown in Figure 1, Figure 2, shown in Figure 10, at the top of described the first blade 1 and the second blade 2 root junctions, be pressed with platen 20, the position of these platen 20 corresponding assembly openings is equipped with via hole.6 the second screws 19 are corresponding one by one with 6 assembly openings that two roots of blade form, the second screw 19 is successively through the via hole on platen 20 and two assembly openings that root of blade forms, and stretch in the output shaft of motor 6, the output shaft of two blades and motor 6 is fixed together.In the corresponding two formed position of positioning hole of root of blade of platen 20, be provided with centre hole, locating dowel pin 17 passes two formed knock holees of root of blade from lower to upper, and stretches in the centre hole of platen 20.
Claims (7)
1. the agricultural aircraft rotor of axle, comprise the first blade (1), the second blade (2), equipment compartment (3), cantilever (4), motor bin (5) and motor (6), it is characterized in that: described equipment compartment (3) is positioned at midway location, this equipment compartment (3) is the cydariform of the uncovered lower end closed in upper end, in the periphery of described equipment compartment (3), be provided with four cantilevers (4) that distribute by even circumferential, the axial line of the axial line of this cantilever (4) and equipment compartment (3) is perpendicular, the ring wall of the inner of described cantilever (4) and equipment compartment (3) is connected as a single entity, in the outer end of each cantilever (4), be provided with motor bin (5), the axis parallel of the axial line of described motor bin (5) and equipment compartment (3), the lower end of this motor bin (5) has the in-flanges (7) of annular arrangement, center at in-flanges (7) is formed with centre hole, in motor bin described in each (5), be provided with motor (6), the bottom of this motor (6) has dowel disc (9), the periphery of described dowel disc (9) is evenly distributed with four journal stirrups (10), each journal stirrup (10) fits with the bottom surface of in-flanges (7), and fixing by the first screw (8), in the top of each motor bin (5), be provided with the first blade (1) and the second blade (2) that by even circumferential, distribute, staggered being connected together of root of two blades, and be fixedly mounted on the output shaft of motor (6).
2. the agricultural aircraft rotor of four axle according to claim 1, it is characterized in that: the root at described the first blade (1) offers the first opening (11) along its length, this first opening (11) by the root of the first blade (1) be divided into up and down dislocation first on positioning table (12) and first time positioning table (13), root at described the second blade (2) offers the second opening (11 ') along its length, this second opening (11 ') by the root of the second blade (2) be divided into up and down dislocation second on positioning table (12 ') and second time positioning table (13 '), described the first blade (1) first on positioning table (12) be superimposed upon the second blade (2) second time positioning table (13 ') above, the second blade (2) second on positioning table (12 ') be superimposed upon the first blade (1) first time positioning table (13) above, make staggered being connected together of root of two blades.
3. the agricultural aircraft rotor of four axle according to claim 2, it is characterized in that: on the opposite face of positioning table on described first (12) and first time positioning table (13), all offer semi-round first breach (14), on second, on the opposite face of positioning table (12 ') and second time positioning table (13 '), all offer semi-round second breach (14 '), the first breach (14) and the second breach (14 ') on two blades form a knock hole jointly; On the output shaft of described motor (6), set firmly a locating dowel pin (17), this locating dowel pin (17) is from lower to upper through two formed knock holees of root of blade.
4. the agricultural aircraft rotor of four axle according to claim 3, it is characterized in that: on positioning table on described first (12) and first time positioning table (13), be respectively arranged with a plurality of the first mounting holes (18), on second, on positioning table (12 ') and second time positioning table (13 '), be respectively arranged with a plurality of the second mounting holes (18 '), the first mounting hole (18) on positioning table on first (12) lay respectively at the second mounting hole (18 ') on second time positioning table (13 ') directly over, the second mounting hole (18 ') on second on positioning table (12 ') lay respectively at the first mounting hole (18) on first time positioning table (13) directly over, above mounting hole forms a plurality of assembly openings that distribute by even circumferential, the second screw (19) passes this assembly opening and stretches in the output shaft of motor (6), the output shaft of two blades and motor (6) is fixed together.
5. the agricultural aircraft rotor of four axle according to claim 4, it is characterized in that: the top in described the first blade (1) and the second blade (2) root junction is pressed with platen (20), the position of the corresponding assembly opening of this platen (20) is equipped with via hole, in the via hole of the second screw (19) from platen (20), passes.
6. according to the arbitrary described agricultural aircraft rotor of four axles of claim 1 to 5, it is characterized in that: described the first blade (1) and the second blade (2) are sabre shape.
7. the agricultural aircraft rotor of four axle according to claim 1, is characterized in that: described journal stirrup (10) is semicircle, and is structure as a whole with dowel disc (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320548101.3U CN203461117U (en) | 2013-09-04 | 2013-09-04 | Rotor wing of four-axis agricultural aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320548101.3U CN203461117U (en) | 2013-09-04 | 2013-09-04 | Rotor wing of four-axis agricultural aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203461117U true CN203461117U (en) | 2014-03-05 |
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ID=50173496
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320548101.3U Expired - Fee Related CN203461117U (en) | 2013-09-04 | 2013-09-04 | Rotor wing of four-axis agricultural aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203461117U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103434644B (en) * | 2013-09-04 | 2015-09-30 | 重庆金泰航空工业有限公司 | A kind of four axle agricultural aircraft combined type fuselages and rotor combine |
| CN110203406A (en) * | 2019-05-15 | 2019-09-06 | 中国科学院深圳先进技术研究院 | A kind of unmanned plane and portable power plants |
-
2013
- 2013-09-04 CN CN201320548101.3U patent/CN203461117U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103434644B (en) * | 2013-09-04 | 2015-09-30 | 重庆金泰航空工业有限公司 | A kind of four axle agricultural aircraft combined type fuselages and rotor combine |
| CN110203406A (en) * | 2019-05-15 | 2019-09-06 | 中国科学院深圳先进技术研究院 | A kind of unmanned plane and portable power plants |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| 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: 20140305 Termination date: 20170904 |