CN203461116U - Combined propeller structure of four-axis agricultural aircraft - Google Patents
Combined propeller structure of four-axis agricultural aircraft Download PDFInfo
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- CN203461116U CN203461116U CN201320547118.7U CN201320547118U CN203461116U CN 203461116 U CN203461116 U CN 203461116U CN 201320547118 U CN201320547118 U CN 201320547118U CN 203461116 U CN203461116 U CN 203461116U
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- positioning table
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Abstract
The utility model discloses a combined propeller structure of a four-axis agricultural aircraft. The combined propeller structure is provided with a first blade (1) and a second blade (2) which are uniformly distributed along the circumferential direction, wherein the roots of the first blade (1) and the second blade (2) are staggered and connected in a clamping way; the first blade (1) and the second blade (2) are respectively made of a carbon fiber composite; each blade is divided into an inner layer and an outer layer, the inner layer is formed by overlaying 90-110 layers of carbon fiber sheets, and the outer layer is coated outside the inner layer and is made of a carbon fiber sheet. The combined propeller structure is not only attractive in appearance, relatively light in weight as well as convenient and rapid in dismounting and mounting, but also reliable in structural strength, durable and long in service life, has the characteristics such as novel design, easiness for improvement, low improvement cost and the like and is applicable to various types of aircrafts.
Description
Technical field
The utility model belongs to agricultural vehicle technology field, specifically, and the particularly agricultural carry-on complex and spiral paddle structure 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 carry-on screw propeller as example, and two blades on existing screw propeller are structure as a whole, packing and the space that takies of transport point is large, cost is high, 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.In addition, propeller blade mostly is metallic material and makes, and metallic material not only weight is large, can increase the weight of whole screw propeller and aircraft, and to the having relatively high expectations of equipment and processing technology, difficulty of processing is larger.
Utility model content
Technical problem to be solved in the utility model is to provide that a kind of weight is light, the agricultural aircraft complex and spiral of the four axles paddle structure of easy installation and removal.
The technical solution of the utility model is as follows: the agricultural aircraft complex and spiral of a kind of four axle paddle structure, there is the first blade (1) and the second blade (2) that by even circumferential, distribute, its key is: staggered being connected together of root of described the first blade (1) and the second blade (2), and the first blade (1) and the second blade (2) are made by carbon fiber composite material, each blade is divided into inside and outside two-layer, wherein internal layer is overrided to form by 90～110 layers of carbon cloth, skin is coated on the outside of internal layer, and this skin is made by carbon cloth.
The screw propeller of the agricultural aircraft of the utility model four axle is set to split-type structural, between the root of two blades, by staggered clamping, can realize the assembling of screw propeller, installs and dismantle not only convenient but also quick; 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.Two blades are made by carbon fiber composite material, and this material weight is lighter, can effectively alleviate the weight of propeller blade and whole aircraft.In addition, this material is hardness and good rigidly not only, has stronger endurance life, is difficult for deforming or damaging, and has good acid and alkali-resistance and decay resistance, durable in use, long service life.
Root at described the first blade (1) offers the first opening (3) along its length, this first opening (3) by the root of the first blade (1) be divided into up and down dislocation first on positioning table (4) and first time positioning table (5), root at described the second blade (2) offers the second opening (3 ') along its length, this second opening (3 ') by the root of the second blade (2) be divided into up and down dislocation second on positioning table (4 ') and second time positioning table (5 '), described the first blade (1) first on positioning table (4) be superimposed upon the second blade (2) second time positioning table (5 ') above, the second blade (2) second on positioning table (4 ') be superimposed upon the first blade (1) first time positioning table (5) 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 and assembling, on the opposite face of positioning table on described first (4) and first time positioning table (5), all offer semi-round first breach (6), on second, on the opposite face of positioning table (4 ') and second time positioning table (5 '), all offer semi-round second breach (6 '), the first breach (6) and the second breach (6 ') on two blades have formed a knock hole jointly, on positioning table on described first (4) and first time positioning table (5), be respectively arranged with a plurality of the first mounting holes (7), on second, on positioning table (4 ') and second time positioning table (5 '), be respectively arranged with a plurality of the second mounting holes (7 '), the first mounting hole (7) on positioning table on first (4) lay respectively at the second mounting hole (7 ') on second time positioning table (5 ') directly over, the second mounting hole (7 ') on second on positioning table (4 ') lay respectively at the first mounting hole (7) on first time positioning table (5) directly over, mounting hole site on each positioning table is on same circumference above, and the center of circle of this circumference is on the line of centers of knock hole.
Described the first blade (1) and the second blade (2) are sabre shape, and this designs not only good looking appearance, and have good in-use performance.
In order to save production cost as far as possible when guaranteeing in-use performance, the thickness of described carbon cloth is 0.2mm.
Beneficial effect: the utility model not only handsome in appearance, weight is lighter, convenient to disassembly, and structural strength is reliable, durable in use, long service life, there is the features such as design is ingenious, transformation is easy, improvement cost is low, all applicable on various types of aircraft.
Accompanying drawing explanation
Fig. 1 is layout schematic diagram of the present utility model.
Fig. 2 is the structural representation of the first blade.
Fig. 3 is the structural representation of the second blade.
Fig. 4 is the A-A cutaway view of Fig. 2.
Fig. 5 is the B-B cutaway view of Fig. 3.
Fig. 6 is the schematic diagram of the staggered clamping of two roots of blade.
The specific embodiment
Below in conjunction with drawings and Examples, the utility model is described in further detail:
As shown in Figures 1 to 6, the screw propeller of the agricultural aircraft of four axles has the first blade 1 and the second blade 2 distributing by even circumferential, and described the first blade 1 and the second blade 2 are all preferably sabre shape, and make by carbon fiber composite material.The first blade 1 and the second blade 2 are divided into inside and outside two-layer, and wherein internal layer is overrided to form by 90～110 layers of carbon cloth, and skin is coated on the outside of internal layer, and this skin is made by carbon cloth.The thickness of above carbon cloth is 0.2mm.Root at described the first blade 1 offers the first opening 3 along its length, this first opening 3 by the root of the first blade 1 be divided into up and down dislocation first on positioning table 4 and first time positioning table 5.Root at described the second blade 2 offers the second opening 3 ' along its length, this second opening 3 ' by the root of the second blade 2 be divided into up and down dislocation second on positioning table 4 ' and second time positioning table 5 ', described the first blade 1 first on positioning table 4 be superimposed upon the second blade 2 second time positioning table 5 ' above, the second blade 2 second on positioning table 4 ' be superimposed upon above first time positioning table 5 of the first blade 1, make staggered being connected together of root of two blades.Described the first blade 1 first on the bottom surface of positioning table 4 and the end face of first time positioning table 5 substantially concordant, described the second blade 2 second on the bottom surface of positioning table 4 ' and the end face of second time positioning table 5 ' substantially concordant.
As shown in Figures 1 to 6, on described first, on the opposite face of positioning table 4 and first time positioning table 5, all offer semi-round first breach 6, the first breach 6 and the second breach 6 ' that on second, on the opposite face of positioning table 4 ' and second time positioning table 5 ', all offer on 6 ', two blades of semi-round second breach have formed a knock hole jointly.On described first, on positioning table 4 and first time positioning table 5, be respectively arranged with a plurality of the first mounting holes 7, in the present embodiment, on first, on positioning table 4 and first time positioning table 5,3 mounting holes 7 be preferably set respectively; On second, on positioning table 4 ' and second time positioning table 5 ', be respectively arranged with a plurality of the second mounting holes 7 ', in the present embodiment, on positioning table 4 ' and second time positioning table 5 ', 3 mounting holes 7 ' be preferably set respectively on second.The first mounting hole 7 on first on positioning table 4 lay respectively at the second mounting hole 7 ' on second time positioning table 5 ' directly over, the second mounting hole 7 ' on second on positioning table 4 ' lay respectively at the first mounting hole 7 on first time positioning table 5 directly over; Distance on same positioning table between two adjacent mounting holes 7 is equal, and the mounting hole site on above each positioning table is on same circumference, and the center of circle of this circumference is on the line of centers of knock hole.
As shown in Figure 6, after the staggered clamping of the root of two blades, be formed with a knock hole, so that the locating dowel pin on motor output shaft stretches in this knock hole, when assembling, locate; And form 6 assembly openings that formed by mounting hole in the outside of knock hole, so that bolt passes assembly opening and stretches in the tapped bore on motor output shaft, screw propeller is fixed on the output shaft of motor.
Claims (5)
1. the agricultural aircraft complex and spiral of an axle paddle structure, there is the first blade (1) and the second blade (2) that by even circumferential, distribute, it is characterized in that: staggered being connected together of root of described the first blade (1) and the second blade (2), and the first blade (1) and the second blade (2) are made by carbon fiber composite material, each blade is divided into inside and outside two-layer, wherein internal layer is overrided to form by 90～110 layers of carbon cloth, skin is coated on the outside of internal layer, and this skin is made by carbon cloth.
2. the agricultural aircraft complex and spiral of four axle according to claim 1 paddle structure, it is characterized in that: the root at described the first blade (1) offers the first opening (3) along its length, this first opening (3) by the root of the first blade (1) be divided into up and down dislocation first on positioning table (4) and first time positioning table (5), root at described the second blade (2) offers the second opening (3 ') along its length, this second opening (3 ') by the root of the second blade (2) be divided into up and down dislocation second on positioning table (4 ') and second time positioning table (5 '), described the first blade (1) first on positioning table (4) be superimposed upon the second blade (2) second time positioning table (5 ') above, the second blade (2) second on positioning table (4 ') be superimposed upon the first blade (1) first time positioning table (5) above, make staggered being connected together of root of two blades.
3. the agricultural aircraft complex and spiral of four axle according to claim 2 paddle structure, it is characterized in that: on the opposite face of positioning table on described first (4) and first time positioning table (5), all offer semi-round first breach (6), on second, on the opposite face of positioning table (4 ') and second time positioning table (5 '), all offer semi-round second breach (6 '), the first breach (6) and the second breach (6 ') on two blades have formed a knock hole jointly, on positioning table on described first (4) and first time positioning table (5), be respectively arranged with a plurality of the first mounting holes (7), on second, on positioning table (4 ') and second time positioning table (5 '), be respectively arranged with a plurality of the second mounting holes (7 '), the first mounting hole (7) on positioning table on first (4) lay respectively at the second mounting hole (7 ') on second time positioning table (5 ') directly over, the second mounting hole (7 ') on second on positioning table (4 ') lay respectively at the first mounting hole (7) on first time positioning table (5) directly over, mounting hole site on each positioning table is on same circumference above, and the center of circle of this circumference is on the line of centers of knock hole.
4. according to the agricultural aircraft complex and spiral of the four axles paddle structure described in claim 1 or 2 or 3, it is characterized in that: described the first blade (1) and the second blade (2) are sabre shape.
5. according to the agricultural aircraft complex and spiral of the four axles paddle structure described in claim 1 or 2 or 3, it is characterized in that: the thickness of described carbon cloth is 0.2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320547118.7U CN203461116U (en) | 2013-09-04 | 2013-09-04 | Combined propeller structure of four-axis agricultural aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320547118.7U CN203461116U (en) | 2013-09-04 | 2013-09-04 | Combined propeller structure of four-axis agricultural aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203461116U true CN203461116U (en) | 2014-03-05 |
Family
ID=50173495
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320547118.7U Expired - Fee Related CN203461116U (en) | 2013-09-04 | 2013-09-04 | Combined propeller structure of four-axis agricultural aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203461116U (en) |
-
2013
- 2013-09-04 CN CN201320547118.7U patent/CN203461116U/en not_active Expired - Fee Related
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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 |