CN113821889B - Screen piece bionic design method based on pigeon wing structural characteristics - Google Patents
Screen piece bionic design method based on pigeon wing structural characteristics Download PDFInfo
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- 238000013461 design Methods 0.000 title claims abstract description 27
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Abstract
The invention discloses a sieve plate bionic design method based on pigeon wing structural characteristics, which comprises the following steps: firstly, selecting a pigeon right wing as a biological model, and obtaining a three-dimensional value model by adopting a reverse engineering technology; secondly, establishing a three-dimensional rectangular coordinate system of the right wing of the 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 for the sieve plate based on the pigeon wing structural characteristics, the wing-shaped structure of the sieve plate enables the total pressure difference in the crushing chamber to be reduced, so that the material can be conveniently discharged out of the sieve in time, meanwhile, intense vortex motion is generated in the airflow field, the original relatively regular motion track of the circulation layer is damaged, and the motion beneficial to discharging the material out of the sieve is generated. In addition, the intense vortex motion continuously consumes energy, so that the relative speed between the material and the hammer sheet is increased, and the crushing can be quickly damaged.
Description
Technical Field
The invention belongs to the technical field of design and manufacture of sieve plates of a pulverizer, and particularly relates to a bionic design method of sieve plates based on structural characteristics of pigeon wings.
Background
The crushing processing is one of indispensable important procedures in feed processing, and the quality of the performance of the crusher directly influences the economic benefit and feed quality of enterprises, so that the hammer crusher has the advantages of strong applicability to raw materials, simple structure, simplicity and convenience in operation and the like, and is widely applied to the feed processing industry.
The sieve piece is a core component of the hammer piece crusher, and when the hammer piece crusher operates, a material circulation layer can be generated on the inner wall of the sieve piece, so that the efficiency of the hammer piece crusher is seriously reduced.
In the flying process of the pigeons, the wings are unfolded, so that the motion track of the local airflow field can be damaged, and the similarity exists between the damage material circulation layer of the sieve sheet and the motion track of the local airflow field. Therefore, the capability of the sieve sheet to destroy the material circulation layer is becoming more and more important through the bionic design of the wing structure of the pigeons.
Disclosure of Invention
The invention aims to solve the problems and provides a sieve piece bionic design method based on the structural characteristics of pigeon wings, which can improve the sieving efficiency of a pulverizer.
In order to solve the technical problems, the technical scheme of the invention is as follows: a sieve plate bionic design method based on pigeon wing structural features comprises the following steps:
s1, selecting a pigeon right wing as a biological model, and obtaining a three-dimensional value model by adopting a reverse engineering technology;
s2, establishing a three-dimensional rectangular coordinate system of the right wing of the pigeon;
s3, extracting wing structure parameters according to the entity model of the right wing of the pigeon established in the step S1, and optimizing the wing structure.
Further, the step S3 further includes the following substeps:
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 7 section curves at different positions;
s32, optimizing the curve obtained in the step S31 through curvature sampling, reducing the number of points in a smooth area, reducing fitting difficulty, and reserving the number of points in a high curvature area so as to reserve more details;
s33, analyzing the 7 groups of curves, discarding 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 step 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, wherein compared with the rest curves, the 2 nd group of curves have the greatest protrusion degree and the greatest striking area for the material, and finally selecting the 2 nd group of curves as the final curve;
s37, obtaining wing-shaped shape parameters based on the characteristic curve in the S34;
s38, combining the structure of the crushing chamber, equally dividing the sieve sheet into 6 parts along the circumferential direction in consideration of the convenience and cost of processing, and designing 6 groups of wing-shaped structures;
s39, selecting the maximum relative camber f and the maximum camber relative position x of the wing according to the design rule of the wing f Relative position x of maximum thickness t And 3 parameters are optimized for the wing shape, 3 parameter optimization ranges are set, and corresponding response surface test design schemes are designed for further optimizing the parameters.
Further, the design response surface test scheme in step S39 optimizes the bionic structure according to the parameters, specifically, the maximum relative camber f and the maximum camber relative position x f Relative position x of maximum thickness t As independent variables, taking the pressure difference in the crushing chamber as an efficiency evaluation index, and designing a response surface test scheme based on Box-Behnken; and 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 the step S2 is a three-dimensional rectangular coordinate system established by taking the fin root-fin tip direction as an X axis, the upper airfoil surface-lower airfoil surface direction as a Y axis, and the wing flying-wing re-feathering direction as a Z axis.
Further, in the step S1, when reverse engineering is adopted, non-contact scanning is performed on the pigeon wings by using handheld 3D scanning to obtain point cloud data, and reverse engineering software geomic Studio is used to sequentially perform pretreatment such as simplification, noise reduction and the like, package treatment, perfection of triangular patch polygon models, construction of NURBS curved surfaces, and finish three-dimensional entity model reverse reconstruction.
Further, in the step S34, the contour curve is imported into the Getdata software to extract the coordinate points.
Further, in the step S35, the Origin software is used to fit the contour curve, so as to obtain a curve characteristic equation.
Further, in the step S39, the maximum relative bending degree is 7% -11%, the maximum bending degree relative position is 40% -60%, and the maximum thickness relative position is 10% -20%.
The beneficial effects of the invention are as follows: according to the bionic design method for the sieve plate based on the pigeon wing structural characteristics, the wing-shaped structure of the sieve plate enables the total pressure difference in the crushing chamber to be reduced, so that the material can be conveniently discharged out of the sieve in time, meanwhile, intense vortex motion is generated in the airflow field, the original relatively regular motion track of the circulation layer is damaged, and the motion beneficial to discharging the material out of the sieve is generated. In addition, the intense vortex motion continuously consumes energy, so that the relative speed between the material and the hammer sheet is increased, and the crushing can be quickly damaged.
Drawings
FIG. 1 is a step diagram of a sieve sheet bionic design method based on pigeon wing structural features of the invention;
FIG. 2 is a comparison schematic diagram of the wing structure and characteristic curve of the pigeon according to the invention;
FIG. 3 is a schematic view of a screen plate according to the present invention
Detailed Description
The invention is further described with reference to the accompanying drawings and specific examples:
as shown in fig. 1 to 3, the bionic design method for the sieve sheet based on the structural characteristics of the pigeon wing provided by the invention is characterized by comprising the following steps:
s1, selecting a pigeon right wing as a biological model, and obtaining a three-dimensional value model by adopting a reverse engineering technology.
When reverse engineering is adopted in the step S1, non-contact scanning is carried out on pigeon wings by utilizing handheld 3D scanning to obtain point cloud data, and reverse engineering software Geomagic Studio is used for sequentially carrying out pretreatment such as simplification, noise reduction and the like on the point cloud data, packaging treatment, perfecting a triangular patch polygonal model, constructing a NURBS curved surface and completing three-dimensional entity model reverse reconstruction.
In the embodiment, a pigeon right wing is adopted as a biological model, a handheld three-dimensional scanner is utilized to carry out non-contact scanning on the wing to obtain point cloud data, reverse engineering software Geomagic Studio is used for sequentially carrying out operations such as simplification, noise reduction and the like on the point cloud data, packaging treatment, perfecting a triangular patch polygonal model, constructing a NURBS curved surface and the like, and the inverse reconstruction of the maxillary entity model is completed. And carrying out fitting precision judgment analysis and model adjustment to meet the characteristic extraction requirement. The reverse engineering technology is the prior art, and is adopted to realize specific functions in the embodiment.
S2, establishing a three-dimensional rectangular coordinate system of the right wing of the pigeon.
The three-dimensional rectangular coordinate system in the step is as follows: and a three-dimensional rectangular coordinate system is established by taking the wing root-wing tip direction as an X axis, the upper airfoil surface-lower airfoil surface direction as a Y axis and the wing flying feather-wing re-feather 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 airfoil surface-lower airfoil surface direction as a Y axis and the wing flying feather-wing feather recombination direction as a Z axis in the structural parameter optimization saw tooth structure of the extracted wing, as shown in fig. 2, a wing section is uniformly intercepted by using a Y-Z plane to form a side profile, an applicable curve is selected, the profile is imported into Getdata software, 200 points on the curve are extracted, and then the upper curve is fitted by using Origin software to obtain a curve characteristic equation.
S3, extracting wing structure parameters according to the entity model of the right wing of the pigeon established in the step S1, and optimizing the wing structure.
Step S3 further comprises the sub-steps of:
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, so as to obtain 7 section curves at different positions.
S32, optimizing the curve obtained in the step S31 through curvature sampling, reducing the number of points in a smooth area, reducing fitting difficulty, and reserving the number of points in a high curvature area so as to reserve more details.
S33, analyzing the 7 groups of curves, discarding 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.
In step S34, the method of extracting points on the contour curve is to import the contour curve into the Getdata software to extract coordinate points.
And S35, fitting the upper curve obtained in the step S34 by adopting a least square method to obtain an upper curve characteristic equation.
In the step S35, the Origin software is used to fit the contour curve, so as to obtain a curve characteristic equation.
S36, comparing the obtained 2, 3 and 4 groups of curves, wherein compared with the rest curves, the 2 group of curves have the largest protrusion degree and the largest striking area for the material, and finally selecting the 2 group of curves as the final curve.
S37, obtaining wing-shaped shape parameters based on the characteristic curve in S34.
S38, combining the structure of the crushing chamber, and taking the convenience and cost of processing into consideration, equally dividing the sieve sheet into 6 parts along the circumferential direction, and designing a 6-group wing-shaped structure.
S39, selecting the maximum relative camber f and the maximum camber relative position x of the wing according to the design rule of the wing f Relative position x of maximum thickness t And 3 parameters are optimized for the wing shape, 3 parameter optimization ranges are set, and corresponding response surface test design schemes are designed for further optimizing the parameters.
In step S39, the design of the response surface test scheme further optimizes the bionic structure with respect to the parameters, specifically, the maximum relative camber f and the maximum camber relative position x f Relative position x of maximum thickness t As independent variables, taking the pressure difference in the crushing chamber as an efficiency evaluation index, and designing a response surface test scheme based on Box-Behnken; and verifying the response surface test scheme by using finite element analysis software, and determining the optimal bionic parameter combination.
In the step S39, the maximum relative bending degree is 7% -11%, the maximum relative bending degree position is 40% -60%, and the maximum relative thickness position is 10% -20%.
Based on the bionic design and the design principle of the sieve sheet, parameters in the steps S2, S3 and S4 are reasonably set, and the design response surface test scheme optimizes the structure of the sieve sheet and combines the bionic design principle and the design principle of the sieve sheet.
Those of ordinary skill in the art will recognize that the embodiments described herein are for the purpose of aiding the reader in understanding the principles of the present invention and should be understood that the scope of the invention is not limited to such specific statements and embodiments. Those of ordinary skill in the art can make various other specific modifications and combinations from the teachings of the present disclosure without departing from the spirit thereof, and such modifications and combinations remain within the scope of the present disclosure.
Claims (1)
1. A sieve plate bionic design method based on pigeon wing structural features is characterized by comprising the following steps:
s1, selecting a pigeon right wing as a biological model, and obtaining a three-dimensional value model by adopting a reverse engineering technology;
s2, establishing a three-dimensional rectangular coordinate system of the right wing of the pigeon;
s3, extracting wing structure parameters according to the entity model of the right wing of the pigeon established in the step S1, and optimizing the wing structure;
the step S3 further comprises the sub-steps of:
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 7 section curves at different positions;
s32, optimizing the curve obtained in the step S31 through curvature sampling, reducing the number of points in a smooth area, reducing fitting difficulty, and reserving the number of points in a high curvature area so as to reserve more details;
s33, analyzing the 7 groups of curves, discarding 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;
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, wherein compared with the rest curves, the 2 nd group of curves have the greatest protrusion degree and the greatest striking area for the material, and finally selecting the 2 nd group of curves as the final curve;
s37, obtaining wing-shaped shape parameters based on the characteristic curve in the S34;
s38, combining the structure of the crushing chamber, equally dividing the sieve sheet into 6 parts along the circumferential direction in consideration of the convenience and cost of processing, and designing 6 groups of wing-shaped structures;
s39, selecting the maximum relative camber f and the maximum camber relative position x of the wing according to the design rule of the wing f Relative position x of maximum thickness t 3 parameters are optimized for the wing shape, 3 parameter optimization ranges are set, and corresponding response surface test design schemes are designed for further optimizing the parameters;
the design response surface test scheme in step S39 further optimizes parameters of the bionic structure, specifically, the maximum relative bending degree f and the maximum bending degree relative position x f Maximum thickness relative position x t Independent variables, namely, taking the pressure difference in the crushing chamber as an efficiency evaluation index, and designing a response surface test scheme based on Box-Behnken; verifying the response surface test scheme by using finite element analysis software, and determining the optimal bionic parameter combination;
the three-dimensional rectangular coordinate system in the step S2 is a three-dimensional rectangular coordinate system 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 feather-wing re-feather direction as a Z axis; extracting a structural parameter optimization sawtooth structure of a wing, taking the wing root-wing tip direction as an X axis, taking the upper wing surface-lower wing surface direction as a Y axis, taking the wing flying feather-wing compound feather direction as a three-dimensional rectangular coordinate system established by a Z axis, uniformly intercepting a wing section by using a Y-Z plane to form a side profile, selecting an applicable curve, importing the profile into Getdata software, extracting 200 points on the curve, and then fitting the upper curve by using Origin software to obtain a curve characteristic equation;
when reverse engineering is adopted in the step S1, non-contact scanning is carried out on pigeon wings by utilizing handheld 3D scanning to obtain point cloud data, and reverse engineering software Geomagic Studio is used for simplifying, reducing noise, preprocessing, packaging, perfecting a triangular patch polygonal model, constructing a NURBS curved surface and completing reverse reconstruction of a three-dimensional entity model;
in the step S34, the contour curve is imported into the Getdata software to extract coordinate points;
in the step S35, the contour curve is fitted by using Origin software to obtain a curve characteristic equation;
the maximum relative bending degree in the S39 is 7% -11%, the maximum bending degree relative position is 40% -60%, and the maximum thickness relative position is 10% -20%.
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