CN112214843B - Finite element rigidity correction method and device for wind tunnel test wing model - Google Patents
Finite element rigidity correction method and device for wind tunnel test wing model Download PDFInfo
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Abstract
The embodiment of the invention discloses a finite element stiffness correction method and device for a wind tunnel test wing model, wherein the method comprises the following steps: carrying out a static loading test on the wind tunnel test wing model, and measuring the wing deformation under the set static load; establishing a novel hybrid element structure finite element model according to the wind tunnel test wing model structure; combining finite element models of static loading devices such as an actuator, a lever, a steel rope and the like to carry out simulation calculation of a simulation static loading test; calculating correction factors by using the wing deformation measured by the static loading test and the wing deformation calculated by simulation so as to correct the rigidity matrix of the wing finite element model; the wind tunnel test wing model finite element rigidity correction method based on the novel hybrid element technology is high in modeling precision, small in calculated amount and high in calculation efficiency, and the calculation accuracy of finite element values is improved.
Description
Technical Field
The embodiment of the invention relates to the technical field of simulation models, in particular to a finite element correction method and device for a wind tunnel model test model.
Background
In the field of aeronautics, an aircraft deforms under the action of aerodynamic force in the flight process, and the deformation can cause aerodynamic force change of the wing, which in turn changes the deformation of the wing until the wing structure reaches a static balance state. This phenomenon of structural coupling with aerodynamic forces is known as the aeroelastic effect. In wind tunnel tests of civil airliners, the swept wings of the test model also produce similar static aeroelastic deformation under aerodynamic force. The aerodynamic variation of the model wing caused by such deformation may reduce the accuracy of the test data.
In order to solve the problems, a computational fluid dynamics method and a structural finite element analysis method are generally combined, and the aeroelastic deformation of the model wing and the aerodynamic variable quantity caused by the aeroelastic deformation are solved through multiple iterations. In finite element modeling of a wing, a conventional method is to use a linear beam model or a three-dimensional body unit model. The rigidity characteristic of the wing can only be approximately simulated, the method has better precision for solving the linear elastic deformation, but the method cannot be used for solving the nonlinear large deformation. The rigidity characteristic of the wing can be better simulated, but the difficulty of three-dimensional grid division for a complex structure is high, and meanwhile, the calculated quantity of the finite element increases exponentially. How to balance the accuracy and the calculation amount of the model is a problem to be solved.
Disclosure of Invention
The embodiment of the invention provides a method, a device, equipment and a storage medium for correcting finite element rigidity of a wind tunnel test wing model, which are used for improving model precision.
In a first aspect, an embodiment of the present invention provides a method for correcting finite element stiffness of a wind tunnel test model wing, where the method for correcting finite element stiffness of a wind tunnel test model wing includes:
according to the predetermined static load, carrying out a static loading test on the wing model of the wind tunnel test, and measuring the deformation of the wing model;
establishing geometrical nonlinear finite element hybridization Liang Moxing of the wing model according to the structure of the wing model;
according to constraint conditions of a static load test and a geometric nonlinear finite element hybrid beam model of the wing model, establishing a finite element model for simulating the static load test, and performing simulation calculation for simulating the static load test to obtain the deformation of the wing model under a predetermined static load;
and correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the deformation of the wing model under the predetermined static load.
In a second aspect, an embodiment of the present invention further provides a finite element stiffness correction device for a wind tunnel test wing model, where the finite element stiffness correction device for a wind tunnel test wing model includes:
the measuring module is used for carrying out a static loading test on the wind tunnel test wing model according to the predetermined static load and measuring the deformation of the wing model;
the model building module is used for building geometrical nonlinear finite element hybridization Liang Moxing of the wing model according to the structure of the wing model;
the deformation determining module is used for establishing a finite element model for simulating the static loading test according to the constraint condition of the static loading test and the geometric nonlinear finite element hybrid beam model of the wing model, and performing simulation calculation for simulating the static loading test to obtain the deformation of the wing model under the predetermined static loading;
and the correction module is used for correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the deformation of the wing model under the predetermined static load.
In a third aspect, an embodiment of the present invention further provides an apparatus, including:
one or more processors;
storage means for storing one or more programs,
the one or more programs, when executed by the one or more processors, cause the one or more processors to implement a method for finite element stiffness correction for a wind tunnel test wing model as described in any of the embodiments of the invention.
In a fourth aspect, embodiments of the present invention further provide a computer readable storage medium having stored thereon a computer program which when executed by a processor implements a method for finite element stiffness correction for a wind tunnel test wing model according to any of the embodiments of the present invention.
The embodiment of the invention provides a method, a device, equipment and a storage medium for correcting finite element rigidity of a wind tunnel test wing model, which are used for measuring the deformation of the wing model by carrying out a static loading test on the wind tunnel test wing model according to a predetermined static load; establishing geometrical nonlinear finite element hybridization Liang Moxing of the wing model according to the structure of the wing model; according to constraint conditions of a static load test and a geometric nonlinear finite element hybrid beam model of the wing model, establishing a finite element model for simulating the static load test, and performing simulation calculation for simulating the static load test to obtain the deformation of the wing model under a predetermined static load; according to the deformation of the wing model under the predetermined static load, the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model is corrected, the problems of low modeling precision and large calculated amount in the prior art are solved, the finite element model simulating the static load test is built through the constraint condition simulating the static load test and the geometrical nonlinear finite element hybrid beam model, the deformation of the wing deformation is obtained through simulation calculation simulating the static load test, the geometrical nonlinear finite element hybrid beam model is corrected through comparison verification with the test result, the precision of the geometrical nonlinear finite element hybrid beam model is improved, the geometrical nonlinear finite element hybrid beam model of the wing model is utilized to realize accurate prediction of the wing nonlinear large deformation, the calculated amount is small, meanwhile, the wing rigidity matrix is automatically calculated, the working efficiency is improved, and the complexity of data processing is reduced.
Drawings
FIG. 1 is a flow chart of a method for finite element stiffness correction of a wind tunnel test wing model in accordance with a first embodiment of the present invention;
FIG. 2 is a flow chart of a method for finite element stiffness correction of a wind tunnel test wing model in accordance with a second embodiment of the present invention;
FIG. 3 is an exemplary diagram of a two-dimensional quadrilateral finite element in a wing section for use in a method for correcting finite element stiffness of a wind tunnel test wing model in accordance with a second embodiment of the present invention;
FIG. 4 is a flowchart of an implementation of determining a stiffness matrix for use in a method for finite element stiffness correction of a wind tunnel test wing model in accordance with a second embodiment of the present invention;
FIG. 5 is an exemplary diagram of a finite element model for simulating a static loading test in a method for correcting finite element stiffness of a wing model for wind tunnel test in accordance with a second embodiment of the present invention;
FIG. 6 is a schematic structural diagram of a finite element stiffness correction device for a wind tunnel test wing model according to a third embodiment of the present invention;
fig. 7 is a schematic structural view of an apparatus according to a fourth embodiment of the present invention.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present invention are shown in the drawings.
Example 1
Fig. 1 is a flowchart of a method for correcting finite element stiffness of a wind tunnel test wing model according to an embodiment of the present invention, where the embodiment is applicable to model correction, and is applicable to correction of a wing finite element model of a wind tunnel test wing model made of any material, and the method may be executed by a device for correcting finite element stiffness of a wind tunnel test wing model, and specifically includes the following steps:
and S110, carrying out a static loading test on the wing model of the wind tunnel test according to the predetermined static load, and measuring the deformation of the wing model.
The wing of the scaled aircraft wind tunnel test model is deformed by applying a certain acting force to obtain the actual deformation, namely the deformation of the wing model, and the steps are as follows: fixing the wind tunnel test model body by using a support; selecting at least 5 spanwise stations (wing sections) on a single side wing of the model wing, and connecting the model wing and a loading actuator cylinder through a clamping plate, a steel rope and a lever; the loading actuator cylinder is controlled to lift the wing upwards in a step-by-step slow loading mode, so that the wing is bent and deformed; when the loading load reaches the predetermined static load, the vertical displacement of the front and rear edge identification points of the model wing is recorded, and the deformation of the spanwise station where the model wing identification points are located is calculated, namely the deformation of the wing model. The model airplane is characterized in that the model airplane is provided with a model airplane wing, a fixed model airplane body, a selected direction-expanding station and a loading actuator cylinder, wherein a certain acting force is applied to the model airplane wing, the model airplane body is fixed, the model airplane wing and the loading actuator cylinder are connected through a clamping plate, a steel rope and a lever, and the model airplane wing is used as a constraint condition for simulating the static loading test and a reference standard for the set acting force, so that a subsequent correction of a finite element model of the wing is facilitated.
And step S120, establishing a geometric nonlinear finite element hybrid beam model of the wing model according to the structure of the wing model.
In this embodiment, the geometric nonlinear finite element hybrid beam model of the wing model can be understood as a digital model of discretized wing structure, which is determined in advance, and can be used for analysis of wing-shaped variables. And (3) constructing a geometric nonlinear finite element hybrid beam model of the wing model according to analysis on the structure of the wing model, such as the wingspan direction of the aircraft and the wing shape of the wing.
And S130, establishing a finite element model for simulating the static loading test according to the constraint condition of the static loading test and the geometric nonlinear finite element hybrid beam model of the wing model, and performing simulation calculation for simulating the static loading test to obtain the deformation of the wing model under the predetermined static load.
In the embodiment, the simulated static loading test refers to numerical simulation analysis of deformation of the wing through computer simulation; constraint conditions are understood to be parameters set for the wing structure in the wing finite element model when simulating deformation of the wing, for example, fixed support boundary conditions are set at the root of the wing finite element model, and steel ropes and levers used when applying force to the wing in practice are simulated by adding rigid units and beam units to the sections of the wing mounting clamping plates.
The method comprises the steps of establishing a geometric nonlinear finite element hybridization Liang Moxing of a wing model which can be used for simulating deformation of a wing, setting constraint conditions of a static loading test on the root of the wing geometric nonlinear finite element hybridization beam model to obtain a finite element model for simulating the static loading test, and then performing simulation calculation for simulating the static loading test to obtain the deformation of the wing model under the predetermined static load. Constraint conditions are selected or set according to test requirements, the constraint conditions can be stored after being set once, and the finite element model is corrected later or the constraint conditions do not need to be set again when the deformation of the wing is predicted according to the finite element model. The geometrical nonlinear finite element hybrid beam model of the wing model can predict nonlinear deformation with larger deformation quantity.
And step 140, correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the deformation of the wing model under the predetermined static load.
After deformation of the wing, determining deformation of the wing model under a predetermined static load according to the positions before deformation and after deformation, wherein the deformation comprises vertical displacement and torsion angle. And judging whether the deformation is in an error allowable range or not, further judging whether the finite element model is accurate or not, and if the error is large, correcting the rigidity matrix of the finite element model according to the deformation of the wing model under a predetermined static load.
The embodiment of the invention provides a finite element rigidity correction method for a wind tunnel test wing model, which improves the precision of the finite element model, realizes the prediction of the deformation quantity of the nonlinear large deformation of the wing by using the wing finite element model, solves the problem that the nonlinear large deformation cannot be predicted by the traditional finite element model, has smaller calculated amount, improves the working efficiency and reduces the complexity of data processing.
Further, according to the deformation of the wing model under the predetermined static load, the method for correcting the rigidity of the geometric nonlinear finite element hybrid beam model of the wing model can be as follows: and correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test.
The geometric nonlinear finite element hybrid beam model comprises a rigidity matrix, the accuracy of the rigidity represents the accuracy of the geometric nonlinear finite element hybrid beam model, so that whether the rigidity matrix is accurate or not is determined according to the magnitude relation between the measured deformation of the wing model and the deformation of the wing model in a simulated static loading test, if not, the rigidity matrix is corrected according to the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test, and further the rigidity correction of the geometric nonlinear finite element hybrid beam model is realized.
Further, according to the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test, the method for correcting the stiffness matrix of the geometric nonlinear finite element hybrid beam model of the wing model may be:
if the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test is greater than a preset threshold, determining a stiffness correction scale factor according to the ratio of the measured deformation to the deformation of the wing model in the simulated static loading test; and multiplying the scale factors by the rigidity matrix calculated originally to obtain a new rigidity matrix, and carrying out numerical simulation calculation on the simulated static loading test again until the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test is smaller than a preset threshold value, stopping iterative calculation, and finishing the rigidity correction of the wing model in the wind tunnel test.
In this embodiment, the preset threshold may be understood as a preset error allowable range; the scale factor may be understood as the ratio of the elastic deformation to the preset deformation.
Calculating a difference value between the measured deformation of the wing model and the deformation of the wing model for simulating the static loading test, if the difference value is larger than a preset threshold value, indicating that the predicted deformation of the geometric nonlinear finite element hybrid beam model is inaccurate, correcting the rigidity matrix of the geometric nonlinear finite element hybrid beam model, calculating the ratio of the measured deformation of the wing model to the deformation of the wing model for simulating the static loading test, taking the ratio as a proportionality factor, multiplying the proportionality factor by the rigidity matrix to obtain the product as a new rigidity matrix, obtaining the first corrected geometric nonlinear finite element hybrid beam model, but judging whether the new rigidity matrix of the geometric nonlinear finite element hybrid beam model is accurate or not, carrying out numerical simulation calculation for simulating the static loading test again to obtain the deformation of the wing, judging whether the difference value between the deformation and the measured deformation is larger than the preset threshold value again, if the difference value between the measured deformation of the wing model and the deformation of the wing model for simulating the static loading test is still larger than the preset threshold value, continuing correction until the difference value between the measured deformation of the wing model and the deformation of the wing model for simulating the static loading test is smaller than the preset threshold value, stopping calculation, and completing the rigidity correction of the wing model for wind tunnel test.
The rigidity matrix of the geometric nonlinear finite element hybridization beam model is corrected to obtain the high-precision geometric nonlinear finite element hybridization Liang Moxing, so that the deformation of the wing is predicted through the geometric nonlinear finite element hybridization beam model, the aerodynamic force change is determined according to the deformation, and the test data of the wind tunnel test are corrected.
Example two
Fig. 2 is a flowchart of a finite element stiffness correction method for a wing model of a wind tunnel test according to a second embodiment of the present invention. The technical scheme of the embodiment is further refined on the basis of the technical scheme, and specifically mainly comprises the following steps:
and S210, carrying out a static loading test on the wind tunnel test wing model according to a predetermined static load, and measuring the deformation of the wing model.
And S220, determining the centroid positions of different stations along the wing span direction according to the wing profile of the incoming flow direction, and obtaining the elastic axis of the wing model.
And S230, cutting the wing perpendicular to the elastic axis, and obtaining a set number of wing sections along the wing spanwise direction, wherein the spanwise station position is determined by the complexity of the section shape.
In this embodiment, the number of settings may be any number, such as 40, 60, etc., and in order to ensure accuracy of the finite element model, the number of settings in this embodiment of the present application is at least 40.
Cutting the wing along the wing span direction, and selecting a set number of wing sections, wherein each wing section is perpendicular to the geometric core line of the wing (the wing section is parallel to the symmetry line of two wings in the aircraft).
And S240, performing finite element discrete processing on each wing section, and obtaining a two-dimensional finite element model of each wing section by adopting two-dimensional finite element units with variable node numbers.
In this embodiment, the two-dimensional finite element cell can be understood as a triangle, a quadrangle, or the like. And carrying out finite element discrete processing on each obtained wing section, accurately describing any complex section shape by adopting a two-dimensional finite element unit with a variable node number of 3 to 9 nodes, and obtaining a two-dimensional finite element model of each wing section. By way of example, FIG. 3 presents an exemplary diagram of two-dimensional quadrilateral finite element elements within a wing section that is discretized into a plurality of two-dimensional quadrilateral finite element elements for use in a wind tunnel test wing model finite element stiffness correction method.
S250, carrying out finite element discrete processing on the model wing along the elastic axis of the wing, and modeling by adopting a novel geometric nonlinear finite element hybrid beam unit, wherein the hybrid beam unit consists of a two-dimensional finite element model of the section of the wing and a three-dimensional nonlinear beam unit of the wing span direction.
The three-dimensional nonlinear beam unit in the embodiment of the application is a nonlinear beam unit between two adjacent sections, the nonlinear beam unit is used for simulating a lever between the two sections when a real wing deforms, and the three-dimensional nonlinear beam unit is determined according to the coordinates of each two-dimensional finite element unit in each wing section.
And step S260, determining a rigidity matrix required by hybrid beam unit modeling and determining nonlinear deformation of the wing model by three-dimensional nonlinear beam units between two adjacent sections in the wing sections according to the two-dimensional finite element units.
Further, fig. 4 provides a flowchart for implementing determining a stiffness matrix in a finite element stiffness correction method of a wind tunnel test wing model, and determining the stiffness matrix according to each plane unit specifically includes the following steps:
step 261, selecting the node number of the two-dimensional finite element unit according to the complexity of the section shape, determining the precision of the two-dimensional finite element unit, determining the relative coordinates in the node section by the discrete wing section, and determining the finite element data of each corresponding wing section by given material properties.
In this embodiment, according to the complexity of the cross-sectional shape, the number of nodes of the two-dimensional finite element unit is selected, preferably, the number of nodes is 3-9 nodes, the precision of the two-dimensional finite element unit is determined, usually 1-order precision to 3-order precision, the discrete wing sections determine the relative coordinates in the node sections, and given the material properties (parameters such as young's modulus, poisson ratio, density, etc.), the corresponding finite element data of each wing section is determined. . The mode of selecting the node number of the two-dimensional finite element unit may be: the method comprises the steps of setting corresponding node numbers for different complexity degrees of the cross-sectional shapes in advance, analyzing the complexity degrees of the cross-sectional shapes through a preset algorithm when the cross-sectional shapes are obtained, and determining the node numbers according to corresponding mapping relations after determining the complexity degrees.
And step 262, predicting a full-rank stiffness matrix of each wing section according to a finite element calculation program developed by a variational asymptotic algorithm, and taking the full-rank stiffness matrix as a stiffness matrix required by hybrid beam unit modeling.
And performing dimension reduction modeling on the data through a variation asymptotic algorithm, and calculating a full rank stiffness matrix of each wing section.
And step 263, processing the full rank stiffness matrix of each wing section through a preset algorithm to obtain a stiffness curve to be corrected of the wing model.
In this embodiment, the stiffness curve is an expression of the relationship between force and deformation, and the stiffness curve is determined by a warping function, which is an expression between the three-dimensional stress of the wing section and the deformation. The stiffness curve to be corrected can be understood as the stiffness curve of the geometric nonlinear finite element hybrid beam model, and the stiffness curve at the moment can be inaccurate, so that whether the stiffness curve is accurate or not needs to be verified later, and the stiffness curve is corrected under the condition of inaccuracy. The preset algorithm can be integrated in software, such as CroSect, and the software automatically processes the data by outputting the finite element data into the software, calculates bending, torsion and shearing rigidity of each wing section and corresponding rigidity coupling items, determines the mass center, shearing center and rigid center positions of each wing section, and automatically processes the bending, torsion and shearing rigidity coupling items to generate a rigidity curve to be corrected of the whole wing.
Step S270, determining a geometrical nonlinear finite element hybrid beam model of the wing model according to each hybrid beam unit comprising two-dimensional finite element units and three-dimensional nonlinear beam units.
The two-dimensional finite element units and the three-dimensional nonlinear beam units form a hybrid beam unit, the geometrical nonlinear finite element hybrid Liang Moxing of the wing model is determined according to the hybrid beam unit, the stiffness matrix is the characteristic of the wing finite element model, and the finally determined geometrical nonlinear finite element hybrid beam model of the wing model comprises the stiffness matrix.
And step S280, establishing a finite element model for simulating the static loading test according to the constraint condition of the static loading test and the geometric nonlinear finite element hybrid beam model of the wing model, and performing simulation calculation for simulating the static loading test to obtain the deformation of the wing model under the predetermined static load.
And step S290, correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the deformation of the wing model under the predetermined static load.
By way of example, FIG. 5 provides an exemplary diagram of a finite element model for simulating a static loading test in a wind tunnel test wing model finite element stiffness correction method, with fixed support boundary conditions set at the root of the wing finite element model; and (3) adding a rigid unit (vertical line) and a beam unit (short horizontal line connected with the vertical line) to the section of the wing mounting clamping plate to respectively simulate a steel cable and a lever used when the wing is actually controlled to deform, thereby completing the finite element model for determining the simulated static loading test according to the constraint condition of the static loading test. And slowly loading the geometrical nonlinear finite element hybrid beam model of the wing model step by step through the rigid body unit until reaching a predetermined static load, and calculating the deformation of each wing section. The number of the wing sections is multiple, so that the deformation is also a plurality of corresponding wing sections, the difference between the deformation and the deformation of the corresponding measured wing model can be calculated, and further the geometric nonlinear finite element hybrid beam model is corrected. Since a part of the calculated differences of the deformation amounts may be within a preset threshold and a part of the calculated differences are not within the preset threshold, it may be set that more than a certain number of differences are not within the preset threshold, and correction is considered to be needed, or correction is needed as long as the differences are larger than the preset threshold, or correction is needed when the average value of the differences is larger than the preset threshold, or the values obtained by measuring the average value, the maximum value, the median and the like of the deformation amounts are compared with the measured deformation amount, and correction is needed when the values are larger than the preset threshold, which is an alternative way, and the correction of the geometric nonlinear finite element hybrid beam model can be realized under the condition of the known deformation variables.
The embodiment of the invention provides a finite element rigidity correction method for a wing model for a wind tunnel test, which is characterized in that a two-dimensional finite element model is obtained by cutting and dispersing wings, and a geometric nonlinear finite element hybrid beam model of the wing model is determined by a hybrid beam unit comprising the two-dimensional finite element model and a three-dimensional nonlinear beam unit, so that the prediction of the deformation quantity of the nonlinear large deformation of the wings is realized, and the problem that the nonlinear large deformation cannot be predicted by the traditional finite element model is solved. The problems of lower precision and larger calculated amount of the wing model in the prior art are solved by correcting the finite element model, the geometric nonlinear finite element hybrid beam model of the wing model is corrected according to the deformation, the precision of the geometric nonlinear finite element hybrid beam model of the wing model is improved, the calculated amount is smaller, the working efficiency is improved, and the complexity of data processing is reduced.
Example III
Fig. 6 is a schematic structural diagram of a finite element stiffness correction device for a wing model for wind tunnel test according to a third embodiment of the present invention, where the device includes: a measurement module 31, a model building module 32, a deformation determination module 33 and a correction module 34.
The measuring module 31 is configured to perform a static loading test on the wind tunnel test wing model according to a predetermined static load, and measure a deformation of the wing model; the model building module 32 is configured to build a geometric nonlinear finite element hybrid Liang Moxing of the wing model according to the structure of the wing model; the deformation determining module 33 is configured to establish a finite element model for simulating the static loading test according to constraint conditions of the static loading test and a geometric nonlinear finite element hybrid beam model of the wing model, and perform simulation calculation for simulating the static loading test to obtain deformation of the wing model under a predetermined static load; and the correction module 34 is used for correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the deformation of the wing model under the preset dead load.
The embodiment of the invention provides a finite element stiffness correction device for a wind tunnel test wing model, which solves the problems of low modeling precision and large calculated amount in the prior art, establishes a finite element model for simulating a static loading test through a constraint condition for simulating the static loading test and a geometric nonlinear finite element hybrid beam model, carries out simulation calculation for simulating the static loading test to obtain the deformation of the wing deformation, corrects the geometric nonlinear finite element hybrid beam model through comparison verification with a test result, improves the precision of the geometric nonlinear finite element hybrid beam model, realizes accurate prediction of the wing nonlinear large deformation by utilizing the geometric nonlinear finite element hybrid beam model of the wing model, has small calculated amount, simultaneously automatically calculates the wing stiffness matrix, improves the working efficiency and reduces the complexity of data processing.
Further, the model building module 32 includes:
the axis determining unit is used for determining centroid positions of different stations along the wing span direction according to the wing profile of the incoming flow direction to obtain an elastic axis of the wing model;
the section determining unit is used for cutting the wing perpendicular to the elastic axis, acquiring a set number of wing sections along the wing spanwise direction, and determining the spanwise station position by the complexity of the section shape;
the finite element model determining unit is used for carrying out finite element discrete processing on each wing section, and a two-dimensional finite element unit with a variable node number is adopted to obtain a two-dimensional finite element model of each wing section;
the modeling unit is used for carrying out finite element discrete processing on the model wing along the elastic axis of the wing, modeling by adopting a novel geometric nonlinear finite element hybrid beam unit, wherein the hybrid beam unit consists of a two-dimensional finite element model of the section of the wing and a three-dimensional nonlinear beam unit of the wing span direction;
the deformation determining unit is used for determining a rigidity matrix required by hybrid beam unit modeling and determining nonlinear deformation of the wing model according to each two-dimensional finite element unit and a three-dimensional nonlinear beam unit between two adjacent sections in each wing section;
and the hybrid beam model determining unit is used for determining a geometric nonlinear finite element hybrid beam model of the wing model according to each hybrid beam unit comprising the two-dimensional finite element unit and the three-dimensional nonlinear beam unit.
Further, the deformation determining unit is specifically configured to: selecting the node number of the two-dimensional finite element unit according to the complexity of the cross section shape, determining the precision of the two-dimensional finite element unit, determining the relative coordinates in the node cross section by the discrete wing cross section, and determining the finite element data of each corresponding wing cross section by given material properties; predicting a full-rank stiffness matrix of each wing section according to a finite element calculation program developed by a variational asymptotic algorithm, and taking the full-rank stiffness matrix as a stiffness matrix required by hybrid beam unit modeling; and processing the stiffness matrix of each wing section through a preset algorithm to obtain a stiffness curve to be corrected of the wing model.
Further, the correction module 34 is specifically configured to: and correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test.
Further, according to the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test, correcting the stiffness matrix of the geometric nonlinear finite element hybrid beam model of the wing model can be implemented by the following modes: if the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test is greater than a preset threshold, determining a stiffness correction scale factor according to the ratio of the measured deformation to the deformation of the wing model in the simulated static loading test; and multiplying the scale factors by the rigidity matrix calculated originally to obtain a new rigidity matrix, and carrying out numerical simulation calculation on the simulated static loading test again until the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test is smaller than a preset threshold value, stopping iterative calculation, and finishing the rigidity correction of the wing model in the wind tunnel test.
The finite element rigidity correction device for the wind tunnel test wing model provided by the embodiment of the invention can be used for executing the finite element rigidity correction method for the wind tunnel test wing model provided by any embodiment of the invention, and has the corresponding functional modules and beneficial effects of the execution method.
Example IV
Fig. 7 is a schematic structural diagram of an apparatus according to a fourth embodiment of the present invention, and as shown in fig. 7, the apparatus includes a processor 40, a memory 41, an input device 42 and an output device 43; the number of processors 40 in the device may be one or more, one processor 40 being taken as an example in fig. 7; the processor 40, the memory 41, the input means 42 and the output means 43 in the device may be connected by a bus or other means, in fig. 7 by way of example.
The memory 41 is used as a computer readable storage medium, and may be used to store software programs, computer executable programs, and modules, such as program instructions/modules corresponding to the method for correcting the finite element stiffness of the wind tunnel test wing model in the embodiment of the present invention (for example, the measurement module 31, the model creation module 32, the deformation determination module 33, and the correction module 34 used in the device for correcting the finite element stiffness of the wind tunnel test wing model). The processor 40 performs various functional applications of the apparatus and data processing by running software programs, instructions and modules stored in the memory 41, i.e. implements the above-described method for finite element stiffness correction of a wind tunnel test wing model.
The memory 41 may mainly include a storage program area and a storage data area, wherein the storage program area may store an operating system, at least one application program required for functions; the storage data area may store data created according to the use of the terminal, etc. In addition, memory 41 may include high-speed random access memory, and may also include non-volatile memory, such as at least one magnetic disk storage device, flash memory device, or other non-volatile solid-state storage device. In some examples, memory 41 may further include memory located remotely from processor 40, which may be connected to the device via a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.
The input means 42 may be used to receive entered numeric or character information and to generate key signal inputs related to user settings and function control of the device. The output means 43 may comprise a display device such as a display screen.
Example five
A fifth embodiment of the present invention also provides a storage medium containing computer executable instructions, which when executed by a computer processor, are for performing a method for finite element stiffness correction of a wind tunnel test wing model, the method comprising:
according to the predetermined static load, carrying out a static loading test on the wing model of the wind tunnel test, and measuring the deformation of the wing model;
establishing geometrical nonlinear finite element hybridization Liang Moxing of the wing model according to the structure of the wing model;
according to constraint conditions of a static load test and a geometric nonlinear finite element hybrid beam model of the wing model, establishing a finite element model for simulating the static load test, and performing simulation calculation for simulating the static load test to obtain the deformation of the wing model under a predetermined static load;
and correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the deformation of the wing model under the predetermined static load.
Of course, the storage medium containing the computer executable instructions provided by the embodiment of the invention is not limited to the method operations described above, and the related operations in the finite element stiffness correction method for the wind tunnel test wing model provided by any embodiment of the invention can also be performed.
From the above description of embodiments, it will be clear to a person skilled in the art that the present invention may be implemented by means of software and necessary general purpose hardware, but of course also by means of hardware, although in many cases the former is a preferred embodiment. Based on such understanding, the technical solution of the present invention may be embodied essentially or in a part contributing to the prior art in the form of a software product, which may be stored in a computer readable storage medium, such as a floppy disk, a Read-Only Memory (ROM), a random access Memory (Random Access Memory, RAM), a FLASH Memory (FLASH), a hard disk or an optical disk of a computer, etc., and include several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the method according to the embodiments of the present invention.
It should be noted that, in the embodiment of the finite element stiffness correction device for a wind tunnel test wing model, each unit and module included are only divided according to the functional logic, but not limited to the above division, so long as the corresponding function can be realized; in addition, the specific names of the functional units are also only for distinguishing from each other, and are not used to limit the protection scope of the present invention.
Note that the above is only a preferred embodiment of the present invention and the technical principle applied. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, while the invention has been described in connection with the above embodiments, the invention is not limited to the embodiments, but may be embodied in many other equivalent forms without departing from the spirit or scope of the invention, which is set forth in the following claims.
Claims (8)
1. The finite element rigidity correction method for the wind tunnel test wing model is characterized by comprising the following steps of:
according to the predetermined static load, carrying out a static loading test on the wing model of the wind tunnel test, and measuring the deformation of the wing model;
establishing geometrical nonlinear finite element hybridization Liang Moxing of the wing model according to the structure of the wing model;
according to constraint conditions of a static load test and a geometric nonlinear finite element hybrid beam model of the wing model, establishing a finite element model for simulating the static load test, and performing simulation calculation for simulating the static load test to obtain the deformation of the wing model under a predetermined static load;
correcting a rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the deformation of the wing model under a predetermined static load;
the building of the geometrical nonlinear finite element hybrid beam model of the wing model according to the structure of the wing model comprises the following steps:
determining centroid positions of different stations along the wing span direction according to the wing profile of the incoming flow direction to obtain an elastic axis of the wing model;
cutting the wing perpendicular to the elastic axis, and obtaining a set number of wing sections along the wing spanwise direction, wherein the spanwise station position is determined by the complexity of the section shape;
performing finite element discrete processing on each wing section, and obtaining a two-dimensional finite element model of each wing section by adopting a two-dimensional finite element unit with a variable node number;
performing finite element discrete processing on a model wing along an elastic axis of the wing, and modeling by adopting a novel geometric nonlinear finite element hybrid beam unit, wherein the hybrid beam unit consists of a two-dimensional finite element model of a wing section and a three-dimensional nonlinear beam unit of a wing span;
determining a rigidity matrix required by hybrid beam unit modeling and determining nonlinear deformation of the wing model by a three-dimensional nonlinear beam unit between two adjacent sections in the wing sections according to each two-dimensional finite element unit;
and determining the geometrical nonlinear finite element hybrid beam model of the wing model according to the hybrid beam units which comprise the two-dimensional finite element units and the three-dimensional nonlinear beam units.
2. The method of claim 1, wherein determining a stiffness matrix required for hybrid beam element modeling from each of the two-dimensional finite element elements comprises:
selecting the node number of the two-dimensional finite element unit according to the complexity of the cross section shape, determining the precision of the two-dimensional finite element unit, determining the relative coordinates in the node cross section by the discrete wing cross section, and determining the finite element data of each corresponding wing cross section by given material properties;
predicting a full-rank stiffness matrix of each wing section according to a finite element calculation program developed by a variational asymptotic algorithm, and taking the full-rank stiffness matrix as a stiffness matrix required by hybrid beam unit modeling;
and processing the stiffness matrix of each wing section through a preset algorithm to obtain a stiffness curve to be corrected of the wing model.
3. The method of claim 1, wherein modifying the stiffness matrix of the geometrically nonlinear finite element hybrid beam model of the wing model based on the amount of deformation of the wing model under a predetermined dead load comprises:
and correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test.
4. A method according to claim 3, wherein said modifying the stiffness matrix of the geometrically nonlinear finite element hybrid beam model of the wing model based on the difference between the measured deflection of the wing model and the deflection of the wing model of the simulated static load test comprises:
if the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test is greater than a preset threshold, determining a stiffness correction scale factor according to the ratio of the measured deformation to the deformation of the wing model in the simulated static loading test;
and multiplying the scale factors by the rigidity matrix calculated originally to obtain a new rigidity matrix, and carrying out numerical simulation calculation on the simulated static loading test again until the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test is smaller than a preset threshold value, stopping iterative calculation, and finishing the rigidity correction of the wing model in the wind tunnel test.
5. A finite element stiffness correction device for a wind tunnel test wing model, comprising:
the measuring module is used for carrying out a static loading test on the wind tunnel test wing model according to the predetermined static load and measuring the deformation of the wing model;
the model building module is used for building geometrical nonlinear finite element hybridization Liang Moxing of the wing model according to the structure of the wing model;
the deformation determining module is used for establishing a finite element model for simulating the static loading test according to the constraint condition of the static loading test and the geometric nonlinear finite element hybrid beam model of the wing model, and performing simulation calculation for simulating the static loading test to obtain the deformation of the wing model under the predetermined static loading;
the correction module is used for correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the deformation of the wing model under the predetermined static load;
the model building module comprises:
the axis determining unit is used for determining centroid positions of different stations along the wing span direction according to the wing profile of the incoming flow direction to obtain an elastic axis of the wing model;
the section determining unit is used for cutting the wing perpendicular to the elastic axis, acquiring a set number of wing sections along the wing spanwise direction, and determining the spanwise station position by the complexity of the section shape;
the finite element model determining unit is used for carrying out finite element discrete processing on each wing section, and a two-dimensional finite element unit with a variable node number is adopted to obtain a two-dimensional finite element model of each wing section;
the modeling unit is used for carrying out finite element discrete processing on the model wing along the elastic axis of the wing, modeling by adopting a novel geometric nonlinear finite element hybrid beam unit, wherein the hybrid beam unit consists of a two-dimensional finite element model of the section of the wing and a three-dimensional nonlinear beam unit of the wing span direction;
the deformation determining unit is used for determining a rigidity matrix required by hybrid beam unit modeling and determining nonlinear deformation of the wing model according to each two-dimensional finite element unit and a three-dimensional nonlinear beam unit between two adjacent sections in each wing section;
and the hybrid beam model determining unit is used for determining the geometrical nonlinear finite element hybrid beam model of the wing model according to the hybrid beam units which comprise the two-dimensional finite element units and the three-dimensional nonlinear beam units.
6. The apparatus of claim 5, wherein the correction module is specifically configured to: and correcting the rigidity matrix of the geometrical nonlinear finite element hybrid beam model of the wing model according to the difference between the measured deformation of the wing model and the deformation of the wing model in the simulated static loading test.
7. An electronic device, the electronic device comprising:
one or more processors;
storage means for storing one or more programs,
when executed by the one or more processors, causes the one or more processors to implement a method for finite element stiffness correction for a wind tunnel test wing model as claimed in any one of claims 1 to 4.
8. A computer readable storage medium having stored thereon a computer program, which when executed by a processor implements a method for finite element stiffness modification of a wind tunnel test wing model according to any one of claims 1 to 4.
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