CN117150657A - Static mechanical property acquisition and analysis system and method for composite material for aviation - Google Patents
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Abstract
The invention relates to a mechanical property acquisition and analysis system, in particular to a static mechanical property acquisition and analysis system and method of a composite material for aviation. The system comprises a data acquisition unit, a data processing unit and a data processing unit, wherein the data acquisition unit is used for acquiring static mechanical characteristic data; the data preprocessing and analyzing unit is used for analyzing the acquired data based on the finite element analysis model so as to verify the acquired data and evaluate the performance of the composite material structure; and the tracking monitoring unit is used for receiving the abnormal data and alarming the abnormal data. The collected data is analyzed based on the finite element analysis model, so that the high-precision simulation and analysis of the internal mechanical behavior of the composite material are realized, and the mechanical property of the composite material can be accurately estimated by combining with the elastic mechanical theory.
Description
Technical Field
The invention relates to a mechanical property acquisition and analysis system, in particular to a static mechanical property acquisition and analysis system and method for an aviation composite material.
Background
With the development of the aviation industry and the continuous improvement of the performance requirements of aircrafts, the composite material is widely applied in the field of aviation. Composite materials have excellent properties including high strength, low density, excellent corrosion resistance and good design flexibility and are therefore widely used in structural members and components of aircraft.
Because the composite material has anisotropic and complex structural characteristics, the acquisition and analysis of static mechanical properties of the composite material become critical, and the acquisition and analysis of the performance data can help engineers to better understand the behavior of the composite material, optimize the design and improve the performance and safety of an aircraft, the existing acquisition and analysis system is easy to generate errors when acquiring and processing a large amount of data, and the accurate evaluation of the performance of the composite material is influenced, so the system and the method for acquiring and analyzing the static mechanical properties of the composite material for aviation are provided.
Disclosure of Invention
The invention aims to provide a static mechanical property acquisition and analysis system and method for an aviation composite material, which are used for solving the problems that the existing acquisition and analysis system provided in the background art is easy to generate errors when acquiring and processing a large amount of data and affects the accurate evaluation of the performance of the composite material.
In order to achieve the above object, the present invention provides a static mechanical property acquisition and analysis system and method for an aviation composite material, comprising:
the data acquisition unit is used for acquiring static mechanical characteristic data;
the data preprocessing and analyzing unit is used for analyzing the acquired data based on the finite element analysis model so as to verify the acquired data and evaluate the performance of the composite material structure;
and the tracking monitoring unit is used for receiving the abnormal data and alarming the abnormal data.
As a further improvement of the technical scheme, the data acquisition unit comprises a sensor, an analog-to-digital converter and a data storage module, wherein the sensor is used for monitoring and acquiring static mechanical property data of the composite material, and the analog-to-digital converter is used for storing the data acquired by the sensor into the data storage module.
As a further improvement of the technical scheme, the data preprocessing and analyzing unit comprises a material characteristic database, a data preprocessing module and a data analyzing module, wherein the material characteristic database is used for storing standard data of mechanical characteristics of the composite material;
the data preprocessing module is used for preprocessing data acquired by the sensor;
and the data analysis module analyzes the preprocessed collected data based on the finite element analysis model to obtain static mechanical data of the composite material.
As a further improvement of the present technical solution, the core algorithm of the finite element analysis model involves the following steps:
s1, discretizing a composite material structure into finite element units;
s2, defining material characteristics of the composite material;
s3, establishing a linear system equation to analyze different mechanical properties of the material in different directions;
s4, constructing a local stiffness matrix of each unit by using the material characteristics and the geometric shapes of the finite element unitsAnd the local rigidity matrix of each finite element unitAssembling into a global stiffness matrix;
s5, solving a linear system equation to obtain a displacement vector, calculating the strain and stress distribution of each finite element unit based on the solved displacement vector, and analyzing a simulation result to evaluate the performance of the structure.
As a further improvement of the present technical solution, in S3, the linear system equation may be expressed as:
；
wherein,is the stress tensor; d is an elastic stiffness matrix;representing the strain tensor.
As a further improvement of the present technical solution, in S4, the local stiffness matrixThe calculation formula of (2) is as follows:
；
wherein B represents a strain-displacement relationship matrix; d represents an elastic stiffness matrix;representing the volume of the finite element;a volume element being an aerospace composite, representing the tiny volume of one volume unit;
further, the local stiffness matrix is converted into a global stiffness matrix, and the specific formula is as follows:
；
wherein,the global rigidity matrix after conversion;is a local stiffness matrix;is a coordinate transformation matrix. Coordinate transformation matrixFor converting the quantities in the local coordinate system to quantities in the global coordinate system.
As a further improvement of the technical scheme, the specific formula of the displacement vector is as follows:
；
wherein,representing a global stiffness matrix;representing a displacement vector;representing a load vector;
strain and stress distribution calculation method for each finite element unitThe method comprises the following steps: from displacement vectors at nodes、And the displacement gradient in the finite element, calculate the displacement vector U in the finite element; by means ofCalculating strain tensors in each finite elementThe method comprises the steps of carrying out a first treatment on the surface of the Based on the elastic stiffness matrix D and the resulting strain tensorCalculating stress tensors in each finite elementStress tensorRepresenting strain distribution in different directions in a coordinate system for knowing deformation degrees of the material in different directions; stress tensorFor researching the stress condition of an object, the failure mechanism of the material and the structural strength, the stress condition of the material in different directions can be known, the strength and the stability of the material are evaluated, and the structural design is optimized so as to ensure that the material has good performance and reliability in practical application.
As a further improvement of the technical scheme, the data analysis module directly compares the analysis result with standard data in a material characteristic database to judge abnormal data;
specifically, the algorithm model for judging the abnormal data is specifically:
；
wherein,is abnormal data;representing the detected value;the standard value is represented by a standard value,representing a threshold value; when the detected value isSum standard valueWhen the absolute value of (2) is greater than the threshold value T, the detected valueIs abnormal data.
As a further improvement of the technical scheme, the abnormal data judgment algorithm model is subjected to algorithm optimization through a support vector machine to construct an optimization model, wherein the specific optimization model is as follows:
；
constraint adjustment is as follows:
；
wherein,a weight vector representing the hyperplane where the detection value is located;representing the deviation;representing the ith detection valueIs a relaxation variable of (2);a mapping function representing mapping of the ith detection value to the feature space;representing the distance from the hyperplane where the detection value is located to the origin, namely a threshold value;the proportion of the abnormal data is represented,representing the number of data points;representing an ith detection value in the input dataset;
further, the decision function output value of the support vector machine is:
；
wherein,as a sign function for determiningIs the sign of (c).
As a further improvement of the technical scheme, the tracking and monitoring unit comprises a monitoring module and an alarm module; the monitoring module is used for receiving the abnormal data, transmitting the abnormal data to the alarm module, and alarming the abnormal data by the alarm module.
On the other hand, the invention provides a static mechanical property acquisition and analysis method of the composite material for aviation, which is used for the static mechanical property acquisition and analysis system of the composite material for aviation, and comprises the following steps:
s10.1, acquiring static mechanical property data of a composite material through a sensor, converting the data acquired by the sensor into digital data from an analog signal through an analog-to-digital converter, and storing the digital data into a data storage module;
s10.2, the data preprocessing module cleans the collected data, so as to improve the accuracy and the integrity of the data;
s10.3, analyzing the data acquired by the preprocessed sensor through a data analysis module, and obtaining static mechanical data of the composite material based on a finite element analysis model;
s10.4, comparing the static mechanical data with standard data in a material characteristic database to obtain abnormal data;
s10.5, the monitoring module is used for receiving the abnormal data, transmitting the abnormal data to the alarm module, and alarming the abnormal data through the alarm module.
Compared with the prior art, the invention has the beneficial effects that:
1. in the static mechanical property acquisition and analysis system and method of the composite material for aviation, the acquired data are analyzed based on the finite element analysis model, so that the highly accurate simulation and analysis of the internal mechanical behavior of the composite material are realized, and the mechanical property of the composite material can be more accurately estimated by combining with the elastic mechanical theory.
2. In the static mechanical property acquisition analysis system and method for the composite material for aviation, a data storage module and a material characteristic database are established, and an analysis result is directly compared with standard data in the material characteristic database through the data analysis module, so that abnormal data can be rapidly analyzed, and the mechanical property of the composite material can be rapidly estimated.
Drawings
Fig. 1 is an overall flow diagram of the present invention.
The meaning of each reference sign in the figure is:
1. a data acquisition unit; 2. a data preprocessing and analyzing unit; 3. tracking the monitoring unit.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1:
referring to fig. 1, a system and a method for collecting and analyzing static mechanical properties of an aeronautical composite material are provided, where the system for collecting and analyzing static mechanical properties of an aeronautical composite material includes:
the data acquisition unit 1 is used for acquiring static mechanical characteristic data; the data acquisition unit 1 comprises a sensor, an analog-to-digital converter and a data storage module, wherein the sensor is used for monitoring and acquiring static mechanical property data of the composite material, and the analog-to-digital converter is used for storing the data acquired by the sensor (converted from an analog signal into digital data) into the data storage module; the sensor at least comprises a strain gauge, a displacement sensor, a pressure sensor and a temperature sensor, and the sensor is used for monitoring structural parameters of the composite material.
The system also comprises a data preprocessing and analyzing unit 2, which analyzes the acquired data based on a finite element analysis model to verify the acquired data and evaluate the performance of the composite material structure; the data preprocessing and analyzing unit 2 comprises a material characteristic database, a data preprocessing module and a data analyzing module, wherein the material characteristic database is used for storing standard data of mechanical characteristics of the composite material;
the data preprocessing module is used for preprocessing the data acquired by the sensor, wherein the preprocessing comprises data cleaning and is used for checking the quality of the data and processing missing values, abnormal values and repeated data;
the data analysis module analyzes the preprocessed collected data based on the finite element analysis model to obtain static mechanical data of the composite material.
The core algorithm of the finite element analysis model involves the following steps:
s1, discretizing a composite material structure into finite element units, wherein the finite element units specifically refer to small units for dividing a complex structure into simple geometric shapes;
s2, defining material characteristics of the composite material, wherein the material characteristics comprise elastic modulus, poisson' S ratio and strength;
s3, establishing a linear system equation for analyzing different mechanical properties of the material in different directions, wherein the linear system equation is used for representing the behavior of the material when the material is stressed; the linear system equation can be expressed as:
；
wherein,as stress tensors, the reaction of forces inside the material to external effects;
d is an elastic stiffness matrix, and represents an important parameter of the relation between the stress and the strain of the material;
the strain tensor is the degree and direction of deformation of the material.
S4, constructing a local stiffness matrix of each unit by using the material characteristics and the geometric shapes of the finite element unitsAnd the local rigidity matrix of each finite element unitAssembling into a global stiffness matrix; wherein the local stiffness matrixThe calculation formula of (2) is as follows:
；
wherein, B represents a strain-displacement relation matrix, which is used for representing how the strain of the composite material changes along with displacement, and is an important linear approximation relation;the volume element of the composite material for aviation is used for representing the tiny volume of one volume unit, and in a rectangular coordinate system,representation of、Andthe product of the lengths in three directions, i.e.；
D represents an elastic stiffness matrix, and important parameters of the stress response of the composite material at a given strain, including the elastic modulus of the composite material and the geometric properties of the material, used to characterize the stiffness of the material;representing the volume of the finite element.
Further, the local stiffness matrix is converted into a global stiffness matrix, and the specific formula is as follows:
；
wherein,the global rigidity matrix after conversion;
the local stiffness matrix is used for representing the stiffness characteristic of the interior of a single finite element unit and reflecting the strain-stress relation of the composite material in the finite element unit;
is a coordinate transformation matrixFor converting the quantities in the local coordinate system to quantities in the global coordinate system; the global stiffness matrix is used for representing stiffness characteristics of the whole structure and is a key parameter for solving displacement vectors and analyzing strain and stress distribution.
S5, solving a linear system equation to obtain a displacement vector, calculating the strain and stress distribution of each finite element unit based on the solved displacement vector, and analyzing a simulation result to evaluate the performance of the structure;
the specific formula of the displacement vector is as follows:
；
wherein,representing a global stiffness matrix, dividing the composite structure into a plurality of finite element units according to the geometric shape and material properties of the composite structure, calculating a local stiffness matrix of each unit, and assembling the local stiffness matrix into the global stiffness matrix according to the connection relation among the units；
Representing a displacement vector;representing the load vector, which can be determined according to the external load condition of the composite material structureSpecific values of (2).
Method for calculating strain and stress distribution of each finite element unitThe method comprises the following steps: from displacement vectors at nodes、And the displacement gradient in the finite element, calculate the displacement vector U in the finite element; by means ofCalculating strain tensors in each finite elementThe method comprises the steps of carrying out a first treatment on the surface of the Based on the elastic stiffness matrix D and the resulting strain tensorCalculating stress tensors in each finite element. Analyzing the strain and stress distribution obtained by calculation, and evaluating the performance of the composite material structure under the loading condition;
the displacement gradient formula inside the finite element is specifically:
；
wherein,representing displacement vectorsWith respect toPartial derivative of direction;representing displacement vectorsWith respect toPartial derivative of direction;representing displacement vectorsWith respect toPartial derivative of direction;for representing the displacement gradient inside the finite element; substituting the known displacement vector u at the node into the derivative expression of the finite element shape function, and calculating to obtain the displacement gradient inside the finite element；
From displacement gradients inside finite elementsCalculating a displacement vector U in the finite element;
the specific calculation formula is as follows:
。
where the known displacement vector U refers to the displacement vector at each node in the structure, in particular for a finite element model, the structure is discretized into a number of small cells, each cell typically associated with a set of nodes that displace when the structure is subjected to an external load.
The data analysis module directly compares the analysis result with standard data in the material characteristic database to judge abnormal data;
specifically, the algorithm model for judging the abnormal data is specifically:
；
wherein,is abnormal data;representing the detected value;the standard value is represented by a standard value,representing a threshold value; when the detected value isSum standard valueWhen the absolute value of (2) is greater than the threshold value T, the detected valueIs abnormal data and is used for judging whether the detection value is abnormal data.
Carrying out algorithm optimization on the algorithm model for judging the abnormal data through a support vector machine to construct an optimization model so as to find a hyperplane capable of maximizing the classification interval and minimizing the classification error, and constructing a support vector machine model so as to find a hyperplane, wherein the specific optimization model is as follows:
the maximized classification interval is:
；
and the constraint adjusts to:
；
for each detection valueConstraint(s)The method comprises the steps of carrying out a first treatment on the surface of the Ensure that the data point is on the correct side, i.e. it is correctly classified, while being constrainedThe non-negativity of the relaxation variable is ensured, i.e. the relaxation variable cannot be negative.
Wherein,a weight vector representing the hyperplane where the detection value is located;representing the deviation;a relaxation variable representing an i-th detection value;a mapping function representing mapping of the ith detection value to the feature space;representing the distance from the hyperplane where the detection value is located to the origin, namely a threshold value;the proportion of the abnormal data is represented,representing the number of data points;representing an ith detection value in the input dataset;
further, the decision function output value of the support vector machine is:
；
wherein,as a sign function forDetermination ofSign of (c);
in the anomaly detection of a static mechanical property acquisition analysis method of a composite material for aviation, a decision function is outputComparing with a preset threshold value, ifExceeding the threshold value, thenThe method is marked as an abnormal point, and in the training process of the support vector machine, the algorithm obtains the weight vector of the hyperplane where the optimal detection value is located through optimization solutionAnd threshold valueTo achieve the best classification effect.
The system also comprises a tracking and monitoring unit 3, wherein the tracking and monitoring unit 3 is used for receiving abnormal data and alarming the abnormal data; further, the tracking and monitoring unit 3 comprises a monitoring module and an alarm module; the monitoring module is used for receiving the abnormal data and transmitting the abnormal data to the alarm module, the alarm module alarms the abnormal data, and the alarm module is used for sending out an alarm to the abnormal data through any one of the audible alarm and the alarm lamp.
Example 2
The difference between the embodiment 2 and the embodiment 1 of the present invention is that the embodiment describes the static mechanical property collection and analysis method used by the static mechanical property collection and analysis system of the composite material for aviation.
The static mechanical property acquisition and analysis method of the composite material for aviation comprises the following steps:
s10.1, acquiring static mechanical property data of a composite material through a sensor, converting the data acquired by the sensor into digital data from an analog signal through an analog-to-digital converter, and storing the digital data into a data storage module;
s10.2, the data preprocessing module cleans the collected data, so as to improve the accuracy and the integrity of the data;
s10.3, analyzing the data acquired by the preprocessed sensor through a data analysis module, and obtaining static mechanical data of the composite material based on a finite element analysis model;
s10.4, comparing the static mechanical data with standard data in a material characteristic database to obtain abnormal data;
s10.5, the monitoring module is used for receiving the abnormal data, transmitting the abnormal data to the alarm module, and alarming the abnormal data through the alarm module.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above-described embodiments, and that the above-described embodiments and descriptions are only preferred embodiments of the present invention, and are not intended to limit the invention, and that various changes and modifications may be made therein without departing from the spirit and scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. The static mechanical property acquisition and analysis system of the composite material for aviation is characterized by comprising the following components:
the data acquisition unit (1) is used for acquiring static mechanical characteristic data;
the data preprocessing and analyzing unit (2), the data preprocessing and analyzing unit (2) comprises a material characteristic database, a data preprocessing module and a data analyzing module, wherein the material characteristic database is used for storing standard data of mechanical characteristics of the composite material, the data preprocessing module is used for preprocessing data acquired by the sensor, the data analyzing module is used for analyzing the data acquired by the preprocessed sensor based on a finite element analysis model, and the finite element analysis model is used for establishing a linear system equation based on an elastic mechanical theory and analyzing different mechanical properties of the material in different directions;
and the tracking and monitoring unit (3) is used for receiving the abnormal data and alarming the abnormal data.
2. The system for collecting and analyzing the static mechanical properties of the composite material for aviation according to claim 1, wherein the system comprises: the data acquisition unit (1) comprises a sensor, an analog-to-digital converter and a data storage module, wherein the sensor is used for monitoring and acquiring static mechanical characteristic data of the composite material, and the analog-to-digital converter is used for storing the data acquired by the sensor into the data storage module.
3. The system for collecting and analyzing the static mechanical properties of the composite material for aviation according to claim 1, wherein the system comprises: the core algorithm of the finite element analysis model involves the following steps:
s1, discretizing a composite material structure into finite element units;
s2, defining material characteristics of the composite material;
s3, establishing a linear system equation to analyze different mechanical properties of the material in different directions;
s4, constructing a local stiffness matrix of each unit by using the material characteristics and the geometric shapes of the finite element unitsAnd the local stiffness matrix of each finite element is +.>Assembling into a global stiffness matrix;
s5, solving a linear system equation to obtain a displacement vector, calculating the strain and stress distribution of each finite element unit based on the solved displacement vector, and analyzing a simulation result to evaluate the performance of the structure.
4. A static mechanical property acquisition and analysis system for an aerospace composite according to claim 3, wherein: in the S3, the linear system equation may be expressed as:
；
wherein,is the stress tensor; d is an elastic stiffness matrix; />Representing the strain tensor.
5. The system for collecting and analyzing the static mechanical properties of the composite material for aviation according to claim 4, wherein: in the S4, a local stiffness matrixThe calculation formula of (2) is as follows:
；
wherein B represents a strain-displacement relationship matrix; d represents an elastic stiffness matrix;representing the volume of the finite element; />Is a volume element of the composite material for aviation;
the local stiffness matrix is converted into a global stiffness matrix, and the specific formula is as follows:
；
wherein,the global rigidity matrix after conversion; />Is a local stiffness matrix; />Is a coordinate transformation matrix.
6. The system for collecting and analyzing the static mechanical properties of the composite material for aviation according to claim 5, wherein the system comprises: the specific formula of the displacement vector is as follows:
；
wherein,representing a global stiffness matrix; />Representing a displacement vector; />Representing a load vector;
the strain and stress distribution calculation method of each finite element unit specifically comprises the following steps: from displacement vectors at nodes、And calculating a displacement vector U in the finite element by using the displacement gradient in the finite element; by->Calculating the strain tensor in each finite element>The method comprises the steps of carrying out a first treatment on the surface of the According to the elastic stiffness matrix D and the resulting strain tensor +.>Calculating stress tensor in each finite element>。
7. The system for collecting and analyzing the static mechanical properties of the composite material for aviation according to claim 1, wherein the system comprises: the data analysis module compares the analysis result with standard data in a material characteristic database and judges abnormal data;
the algorithm model for judging the abnormal data specifically comprises the following steps:
；
wherein,is abnormal data; />Representing the detected value; />Representing standard value,/->Representing a threshold value; when the detection value +.>And standard value->When the absolute value of said detection value is larger than the threshold value T +.>Is abnormal data.
8. The system for collecting and analyzing the static mechanical properties of the composite material for aviation according to claim 7, wherein: the algorithm model for judging the abnormal data carries out algorithm optimization through a support vector machine to construct an optimization model, and the specific optimization model is as follows:
；
constraint adjustment is as follows:
；
wherein,a weight vector representing a plane in which the detection value is located; />Representing the deviation; />A relaxation variable representing an i-th detection value; />A mapping function representing mapping of the ith detection value to the feature space; />Representing the distance from the plane of the detection value to the origin; />Representation ofProportion of abnormal data, ++>Representing the number of data points; />Representing an ith detection value in the input dataset;
the decision function output value of the support vector machine is as follows:
；
wherein,is a sign function for determining->Sign of (c);
in anomaly detection, a decision function is typically outputComparing with a threshold value set in advance, if +.>Exceeding the threshold value, will->Marked as outliers.
9. The system for collecting and analyzing the static mechanical properties of the composite material for aviation according to claim 1, wherein the system comprises: the tracking monitoring unit (3) comprises a monitoring module and an alarm module; the monitoring module is used for receiving the abnormal data, transmitting the abnormal data to the alarm module, and alarming the abnormal data by the alarm module.
10. A static mechanical property acquisition and analysis method for an aviation composite material, which is used for the static mechanical property acquisition and analysis system of the aviation composite material according to any one of claims 1 to 9, and is characterized by comprising the following steps:
s10.1, acquiring static mechanical property data of a composite material through a sensor, converting the data acquired by the sensor into digital data from an analog signal through an analog-to-digital converter, and storing the digital data into a data storage module;
s10.2, data cleaning is carried out on the collected data by a data preprocessing module;
s10.3, analyzing the data acquired by the preprocessed sensor through a data analysis module, and obtaining static mechanical data of the composite material based on a finite element analysis model;
s10.4, comparing the static mechanical data with standard data in a material characteristic database to obtain abnormal data;
s10.5, the monitoring module receives the abnormal data, the abnormal data are transmitted to the alarm module, and the alarm module alarms the abnormal data.
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