CN113821889A - Screen sheet bionic design method based on structural features of pigeon feather wings - Google Patents
Screen sheet bionic design method based on structural features of pigeon feather wings Download PDFInfo
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Abstract
The invention discloses a sieve sheet bionic design method based on structural characteristics of a pigeon wing, which comprises the following steps: firstly, selecting a pigeon right wing as a biological model, and obtaining a three-dimensional numerical model thereof by adopting a reverse engineering technology; secondly, establishing a three-dimensional rectangular coordinate system of the right wing of the domestic pigeon; and thirdly, extracting wing-shaped structure parameters according to the entity model of the right wing of the pigeon established in the first step, and optimizing the wing-shaped structure. According to the bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon, the wing-shaped structure of the sieve sheet enables the total pressure difference in the crushing chamber to be reduced, so that materials can be discharged out of the sieve in time, and meanwhile, violent vortex motion is generated in an airflow field, so that the original regular motion track of a circulation layer is destroyed, and the motion which is beneficial to discharging the materials is generated. In addition, the violent vortex motion continuously consumes energy, increases the relative speed between the materials and the hammer pieces, and enables the materials to be damaged and crushed more quickly.
Description
Technical Field
The invention belongs to the technical field of design and manufacture of screen pieces of a pulverizer, and particularly relates to a screen piece bionic design method based on structural characteristics of a pigeon wing.
Background
The crushing processing is one of indispensable important processes in the feed processing, the economic benefit and the feed quality of enterprises are directly influenced by the performance of the crusher, and the hammer type crusher is widely applied to the feed processing industry due to the advantages of strong applicability to raw materials, simple structure, simple and convenient operation and the like.
The sieve piece is the core component of hammer mill, when hammer mill operation, can produce the material circulation layer at the sieve piece inner wall, has seriously reduced hammer mill's efficiency.
When the pigeon flies, the wings are unfolded, so that the motion trail of the local airflow field can be destroyed, and the material circulation layer is destroyed by the sieve pieces, and the great similarity exists. Therefore, the bionic design of the wing structure of the domestic pigeon is more and more important to improve the capability of the sieve sheet to damage the material circulation layer.
Disclosure of Invention
The invention aims to solve the problems and provides a bionic design method of a sieve sheet based on structural characteristics of a pigeon wing, which can improve the sieving efficiency of a crusher.
In order to solve the technical problems, the technical scheme of the invention is as follows: a sieve sheet bionic design method based on structural characteristics of a pigeon wing comprises the following steps:
s1, selecting the right wing of the pigeon as a biological model, and obtaining a three-dimensional numerical model of the pigeon by adopting a reverse engineering technology;
s2, establishing a three-dimensional rectangular coordinate system of the right wing of the pigeon;
s3, extracting wing-shaped structure parameters according to the entity model of the right wing of the pigeon established in the step S1, and optimizing the wing-shaped structure.
Further, the step S3 further includes the following sub-steps:
s31, uniformly intercepting the wing structure along the direction from the wing root to the wing tip by utilizing the Y-Z plane in the three-dimensional direct coordinate system in the step S2 to obtain profile curves of 7 different positions;
s32, optimizing the curve obtained in the step S31 through curvature sampling, reducing the number of points in a smooth area, reducing the fitting difficulty, and reserving the number of points in a high curvature area to reserve more details;
s33, analyzing the 7 groups of curves, abandoning unsuitable curves, and finally selecting the 2 nd, 3 rd and 4 th groups of curves;
s34, establishing a curve coordinate system, and extracting 200 to 300 points on the curve;
and S35, fitting the upper curve obtained in the S34 by adopting a least square method to obtain an upper curve characteristic equation.
S36, comparing the obtained 2, 3 and 4 groups of curves, and selecting the 2 nd group of curves as a final curve, wherein compared with the rest curves, the 2 nd group of curves has the largest protruding degree and the largest impact area on materials;
s37, obtaining wing-shaped parameters based on the characteristic curve in S34;
s38, combining the structure of the crushing chamber, considering the processing convenience and cost, evenly dividing the sieve sheet into 6 equal parts along the circumferential direction, and designing 6 groups of wing-shaped structures;
s39, selecting the maximum relative camber f and the maximum camber relative position x of the airfoil profile according to the design specification principle of the airfoilfMaximum thickness relative position xtAnd (3) optimizing the wing shape according to the 3 parameters, setting the optimization range of the 3 parameters, and designing a corresponding response surface test design scheme to further optimize the parameters.
Further, the step S39 of designing the response surface test scheme further optimizes the bionic structure for the parameters, specifically, using the maximum relative curvature f and the maximum relative curvature position xfMaximum thickness relative position xtTaking the pressure difference in the crushing chamber as an efficiency evaluation index as an independent variable, and designing a Box-Behnken-based response surface test scheme; and (4) verifying the response surface test scheme by using finite element analysis software, and determining the optimal bionic parameter combination.
Further, the three-dimensional rectangular coordinate system in step S2 is a three-dimensional rectangular coordinate system established with the fin root-fin tip direction as the X axis, the upper airfoil surface-lower airfoil surface direction as the Y axis, and the wing flight-wing plume recovery direction as the Z axis.
Further, when the reverse engineering is adopted in step S1, the pigeon wing is scanned in a non-contact manner by using the handheld 3D scan to obtain point cloud data, and the point cloud data is subjected to preprocessing such as simplification and noise reduction, packaging, perfecting a triangular patch polygon model, constructing a NURBS curved surface, and completing the reverse reconstruction of the three-dimensional solid model by using the reverse engineering software geologic Studio.
Further, in the step S34, the contour curve is imported into Getdata software to extract coordinate points.
Further, in step S35, the outline curve is fitted by using Origin software to obtain a curve characteristic equation.
Further, in the S39, the maximum relative curvature is 7% -11%, the maximum relative position of the curvature is 40% -60%, and the maximum relative position of the thickness is 10% -20%.
The invention has the beneficial effects that: according to the bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon, the wing-shaped structure of the sieve sheet enables the total pressure difference in the crushing chamber to be reduced, so that materials can be discharged out of the sieve in time, and meanwhile, violent vortex motion is generated in an airflow field, so that the original regular motion track of a circulation layer is destroyed, and the motion which is beneficial to discharging the materials is generated. In addition, the violent vortex motion continuously consumes energy, increases the relative speed between the materials and the hammer pieces, and enables the materials to be damaged and crushed more quickly.
Drawings
FIG. 1 is a step diagram of a bionic design method of a sieve plate based on structural characteristics of a pigeon wing according to the invention;
FIG. 2 is a schematic diagram showing the comparison between the wing structure and characteristic curve of the pigeon according to the present invention;
FIG. 3 is a schematic view of a sieve sheet according to the present invention
Detailed Description
The invention is further described with reference to the following figures and specific embodiments:
as shown in fig. 1 to 3, the bionic design method of the sieve sheet based on the structural characteristics of the pigeon wing provided by the invention is characterized by comprising the following steps:
and S1, selecting the right wing of the pigeon as a biological model, and obtaining a three-dimensional numerical model of the pigeon by adopting a reverse engineering technology.
When reverse engineering is adopted in the step S1, the pigeon wing is scanned in a non-contact manner by using handheld 3D scanning to obtain point cloud data, and preprocessing such as simplification and noise reduction, packaging processing, perfecting a triangular patch polygonal model, constructing a NURBS curved surface, and completing reverse reconstruction of a three-dimensional solid model are sequentially performed on the point cloud data by using reverse engineering software geologic Studio.
In this embodiment, the right wing of the pigeon is used as a biological model, the feather wing is scanned in a non-contact manner by using a handheld three-dimensional scanner to obtain point cloud data, and the point cloud data is subjected to preprocessing such as simplification and noise reduction, packaging processing, perfecting a triangular patch polygonal model, constructing a NURBS curved surface and the like in sequence by using reverse engineering software geologic Studio to complete the reverse reconstruction of the maxillary solid model. And performing fitting precision judgment analysis and model adjustment to meet the requirement of feature extraction. The reverse engineering technology is the prior art, and is adopted in the present embodiment to implement a specific function.
And S2, establishing a three-dimensional rectangular coordinate system of the right wing of the pigeon.
The three-dimensional rectangular coordinate system in this step is: and a three-dimensional rectangular coordinate system is established by taking the wing root-wing tip direction as an X axis, the upper wing surface-lower wing surface direction as a Y axis and the wing flying-wing feathering direction as a Z axis. Specifically, a three-dimensional rectangular coordinate system is established by taking the wing root-wing tip direction as an X axis, the upper wing surface-lower wing surface direction as a Y axis and the wing flying-wing plume restoring direction as a Z axis, as shown in fig. 2, a Y-Z plane is used for uniformly intercepting the section of the wing to form a side profile diagram, an applicable curve is selected, the profile diagram is led into Getdata software, 200 points on the curve are extracted, and then the upper curve is fitted by Origin software to obtain a curve characteristic equation.
S3, extracting wing-shaped structure parameters according to the entity model of the right wing of the pigeon established in the step S1, and optimizing the wing-shaped structure.
Step S3 further includes the following sub-steps:
s31, uniformly intercepting the wing structure along the direction from the wing root to the wing tip by utilizing the Y-Z plane in the three-dimensional direct coordinate system in the step S2 to obtain profile curves of 7 different positions.
S32, the curve obtained in the step S31 is optimized through curvature sampling, the number of points in a smooth area is reduced, the fitting difficulty is reduced, and the number of points in a high curvature area is reserved so as to reserve more details.
And S33, analyzing the 7 sets of curves, abandoning unsuitable curves, and finally selecting the 2 nd, 3 rd and 4 th sets of curves.
And S34, establishing a curve coordinate system, and extracting 200 to 300 points on the curve.
In step S34, the points on the curve are extracted by importing the contour curve into Getdata software to extract coordinate points.
And S35, fitting the upper curve obtained in the S34 by adopting a least square method to obtain an upper curve characteristic equation.
And in the step S35, fitting the contour curve by using Origin software to obtain a curve characteristic equation.
S36, comparing the obtained 2, 3 and 4 groups of curves, and selecting the 2 nd group of curves as a final curve, wherein the 2 nd group of curves has the largest protruding degree and the largest impact area on the materials compared with other curves.
And S37, obtaining the wing-shaped parameters based on the characteristic curve in the S34.
S38, combining the structure of the crushing chamber, considering the processing convenience and cost, evenly dividing the sieve sheet into 6 equal parts along the circumferential direction, and designing 6 groups of wing-shaped structures.
S39, selecting the maximum relative camber f and the maximum camber relative position x of the airfoil profile according to the design specification principle of the airfoilfMaximum thickness relative position xtAnd (3) optimizing the wing shape according to the 3 parameters, setting the optimization range of the 3 parameters, and designing a corresponding response surface test design scheme to further optimize the parameters.
In step S39, a response surface test scheme is designed to further optimize the bionic structure for the parameters, specifically, the response surface test scheme is designed to further optimize the bionic structure for the parametersUsing the maximum relative curvature f and the maximum relative curvature position xfMaximum thickness relative position xtTaking the pressure difference in the crushing chamber as an efficiency evaluation index as an independent variable, and designing a Box-Behnken-based response surface test scheme; and (4) verifying the response surface test scheme by using finite element analysis software, and determining the optimal bionic parameter combination.
In step S39, the maximum relative curvature is 7% to 11%, the maximum relative curvature is 40% to 60%, and the maximum relative thickness is 10% to 20%.
Based on the bionic design and the screen piece design principle, parameters in the steps S2, S3 and S4 are reasonably set, and the design response surface test scheme optimizes the screen piece structure and combines the bionic design criterion and the screen piece design principle.
It will be appreciated by those of ordinary skill in the art that the embodiments described herein are intended to assist the reader in understanding the principles of the invention and are to be construed as being without limitation to such specifically recited embodiments and examples. Those skilled in the art can make various other specific changes and combinations based on the teachings of the present invention without departing from the spirit of the invention, and these changes and combinations are within the scope of the invention.
Claims (8)
1. A sieve sheet bionic design method based on structural characteristics of a pigeon wing is characterized by comprising the following steps:
s1, selecting the right wing of the pigeon as a biological model, and obtaining a three-dimensional numerical model of the pigeon by adopting a reverse engineering technology;
s2, establishing a three-dimensional rectangular coordinate system of the right wing of the pigeon;
s3, extracting wing-shaped structure parameters according to the entity model of the right wing of the pigeon established in the step S1, and optimizing the wing-shaped structure.
2. The bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon as claimed in claim 1, wherein the step S3 further comprises the following sub-steps:
s31, uniformly intercepting the wing structure along the direction from the wing root to the wing tip by utilizing the Y-Z plane in the three-dimensional direct coordinate system in the step S2 to obtain profile curves of 7 different positions;
s32, optimizing the curve obtained in the step S31 through curvature sampling, reducing the number of points in a smooth area, reducing the fitting difficulty, and reserving the number of points in a high curvature area to reserve more details;
s33, analyzing the 7 groups of curves, abandoning unsuitable curves, and finally selecting the 2 nd, 3 rd and 4 th groups of curves;
s34, establishing a curve coordinate system, and extracting 200 to 300 points on the curve;
and S35, fitting the upper curve obtained in the S34 by adopting a least square method to obtain an upper curve characteristic equation.
S36, comparing the obtained 2, 3 and 4 groups of curves, and selecting the 2 nd group of curves as a final curve, wherein compared with the rest curves, the 2 nd group of curves has the largest protruding degree and the largest impact area on materials;
s37, obtaining wing-shaped parameters based on the characteristic curve in S34;
s38, combining the structure of the crushing chamber, considering the processing convenience and cost, evenly dividing the sieve sheet into 6 equal parts along the circumferential direction, and designing 6 groups of wing-shaped structures;
s39, selecting the maximum relative camber f and the maximum camber relative position x of the airfoil profile according to the design specification principle of the airfoilfMaximum thickness relative position xtAnd (3) optimizing the wing shape according to the 3 parameters, setting the optimization range of the 3 parameters, and designing a corresponding response surface test design scheme to further optimize the parameters.
3. The bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon as claimed in claim 2, which is characterized in that: step S39, designing a response surface test scheme to further optimize the bionic structure for parameters, specifically, using the maximum relative curvature f and the maximum relative curvature position xfMaximum thickness relative position xtIndependent variables, namely a Box-Behnken-based response surface test scheme is designed by taking the pressure difference in the crushing chamber as an efficiency evaluation index; using finite element analysis softwareAnd verifying the response surface test scheme to determine the optimal bionic parameter combination.
4. The bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon as claimed in claim 1, which is characterized in that: the three-dimensional rectangular coordinate system in step S2 is a three-dimensional rectangular coordinate system established with the fin root-fin tip direction as the X axis, the upper airfoil surface-lower airfoil surface direction as the Y axis, and the wing flight-wing plume recovery direction as the Z axis.
5. The bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon as claimed in claim 1, which is characterized in that: when reverse engineering is adopted in the step S1, the pigeon wing is scanned in a non-contact manner by using handheld 3D scanning to obtain point cloud data, and preprocessing such as simplification and noise reduction, packaging processing, perfecting a triangular patch polygonal model, constructing a NURBS curved surface, and completing reverse reconstruction of a three-dimensional solid model are sequentially performed on the point cloud data by using reverse engineering software geologic Studio.
6. The bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon as claimed in claim 2, which is characterized in that: in step S34, the contour curve is imported into Getdata software to extract coordinate points.
7. The bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon as claimed in claim 1, which is characterized in that: and in the step S35, fitting the contour curve by using Origin software to obtain a curve characteristic equation.
8. The bionic design method of the sieve sheet based on the structural characteristics of the feather wing of the pigeon as claimed in claim 1, which is characterized in that: in the S39, the maximum relative curvature is 7-11%, the maximum relative curvature position is 40-60%, and the maximum relative thickness position is 10-20%.
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