CN106021770B - The method for analyzing stability and device of aircaft configuration rectangular plate - Google Patents
The method for analyzing stability and device of aircaft configuration rectangular plate Download PDFInfo
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Abstract
The embodiment of the invention provides the method for analyzing stability and device of a kind of aircaft configuration rectangular plate, this method comprises: carrying out electronic disposal to the curve graph of double pressure shear buckling correlation curves of rectangular plate, obtain curve data, wherein, the value on the abscissa, ordinate and curve of the curve graph is denoted as CurveRx, CurveRy and CurveRs in the curve data respectively；According to the compression allowable stress σ of the X-direction of rectangular plateccrx, Y-direction compression allowable stress σccry, shearing allowable stress τcr, X-direction compression work stress σcx, Y-direction compression work stress σcy, shearing work stress τ calculate Rx, Ry, Rs；The value for meeting CurveRx, CurveRy and CurveRs of formula (1) is searched in the curve data based on binary chop algorithm；Calculate the safety margin MS=K-1 of the rectangular plate；The stability of the rectangular plate is analyzed according to the safety margin MS.The present invention enables to calculated safety margin to have stronger scientific and reliability, so that the stability analysis result to aircaft configuration rectangular plate is more rationally reliable.
Description
Technical Field
The invention relates to the technical field of airplane structures, in particular to a method and a device for analyzing the stability of a rectangular flat plate of an airplane structure.
Background
The design and the fine analysis work of the bearing stability of the airplane structure have important engineering significance on the aspects of the bearing safety, the service life, the weight optimization and the like of the structure. The flat plate double-pressure shear instability analysis combines finite element calculation results with a test curve and an empirical formula to calculate the stability of a flat plate.
In the structural stability design manual written by Mr. of Ruideng, the plane rectangular flat plate hardening is performed by the curve of the flat plate double-pressure shear instability analysisWhen analyzing the stability of the structure, mainly by calculating the abscissa Rx of the curve, the value Rs on the curve and the value Ry on the ordinate, and by using two values of Rx, Rs as input parameters, a value Ry corresponding to them can be uniquely determined on the curve, where Ry is represented by CurveRy, and the safety margin is
However, this method of calculating the safety margin assumes that the compressive stress in the X direction is not changed and the shear stress is not changed, and increases the compressive stress in the Y direction to obtain the safety margin.
Obviously, the assumption does not conform to the actual stress situation of the rectangular flat plate of the airplane structure, and therefore, when the stability analysis is carried out by using the safety margin obtained by calculation, the problem of poor reliability obviously exists.
Disclosure of Invention
The technical problem to be solved by the embodiments of the present invention is to provide a method and an apparatus for analyzing stability of an aircraft structure rectangular flat plate, so as to solve the problem in the prior art that the reliability of an analysis result is poor due to the fact that the actual stress condition of the aircraft structure rectangular flat plate is not considered when the stability of the aircraft structure rectangular flat plate is analyzed.
In order to solve the above problem, according to an aspect of the present invention, the present invention discloses a method for analyzing stability of a rectangular flat plate of an aircraft structure, comprising:
performing electronization processing on a curve graph of the rectangular flat plate double-pressure shearing buckling related curve to obtain curve data, wherein the abscissa and the ordinate of the curve graph and values on the curve are respectively marked as CurveRx, CurveRy and CurveRs in the curve data;
allowable compressive stress sigma in X direction of rectangular flat plateccrxCompressive working stress sigma in the X directioncxAllowable compressive stress σ in Y-directionccryCompressive working stress sigma in Y directioncyShear allowable stress taucrCalculating the shearing working stress tau:
finding values of CurveRx, CurveRy, and CurveRs in the curve data that satisfy the following equation (1) based on a binary search algorithm:
calculating the safety margin MS of the rectangular flat plate as K-1;
and analyzing the stability of the rectangular flat plate according to the safety margin MS.
According to another aspect of the present invention, the present invention also discloses an apparatus for analyzing the stability of a rectangular plate of an aircraft structure, comprising:
the system comprises an electronization processing module, a data processing module and a data processing module, wherein the electronization processing module is used for performing electronization processing on a curve graph of a double-pressure shearing buckling related curve of a rectangular flat plate to obtain curve data, and the abscissa and the ordinate of the curve graph and values on the curve are respectively marked as CurveRx, CurveRy and CurveRs in the curve data;
a first calculation module for calculating a compressive allowable stress σ in the X direction of the rectangular flat plateccrxCompressive working stress sigma in the X directioncxAllowable compressive stress σ in Y-directionccryCompressive working stress sigma in Y directioncyShear allowable stress taucrCalculating the shearing working stress tau:
a searching module, configured to search the curve data for values of CurveRx, CurveRy, and CurveRs that satisfy the following formula (1) based on a binary search algorithm:
the second calculation module is used for calculating the safety margin MS of the rectangular flat plate to be K-1;
and the analysis module is used for analyzing the stability of the rectangular flat plate according to the safety margin MS.
Compared with the prior art, the embodiment of the invention has the following advantages:
the embodiment of the invention adopts the steps of carrying out electronic processing on the graph and utilizing subsequent data to search and analyze; and points which accord with a preset formula are searched in the graph by utilizing a dichotomy searching technology, and synchronous amplification of loads in all directions is realized, so that the calculated safety margin has stronger scientificity and reliability, and the stability analysis result of the rectangular flat plate of the airplane structure is more reasonable and reliable.
Drawings
FIG. 1 is a flow chart illustrating the steps of an embodiment of a method for analyzing the stability of a rectangular plate of an aircraft structure according to the present invention;
FIG. 2 is a schematic of a rectangular flat plate dual compression shear buckling correlation curve of the present invention having an aspect ratio of 2;
FIG. 3 is a schematic representation of a rectangular flat plate dual compression shear buckling correlation curve of the present invention having an aspect ratio of 3;
FIG. 4 is a schematic diagram of a rectangular flat plate with an aspect ratio of 2 after an electronization process of a related curve of double-pressure shear buckling according to the present invention;
FIG. 5 is a schematic diagram of a rectangular flat plate with an aspect ratio of 3 after an electronization process of a related curve of double-pressure shear buckling according to the present invention;
FIG. 6 is a schematic flow chart diagram illustrating an alternative embodiment of a method for analyzing the stability of a rectangular plate in an aircraft structure according to the present invention;
FIG. 7 is a flow chart illustrating steps in an alternative embodiment of a method for analyzing the stability of a rectangular plate in an aircraft structure in accordance with the present invention;
fig. 8 is a block diagram of an embodiment of the stability analysis device for the rectangular flat plate of the aircraft structure according to the present invention.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Referring to fig. 1, a flowchart illustrating steps of an embodiment of a method for analyzing stability of a rectangular flat plate of an aircraft structure according to the present invention is shown, which may specifically include the following steps:
step 101, performing electronic processing on a curve graph of a rectangular flat plate double-pressure shearing buckling related curve to obtain curve data, wherein the abscissa and the ordinate of the curve graph and values on the curve are respectively marked as CurveRx, CurveRy and CurveRs in the curve data;
in the present embodiment, the stability analysis of a rectangular flat plate (also a rectangular flat plate structure) of an airplane structure is performed by using a curve related to rectangular flat plate dual-pressure shear buckling in "flat plate dual-pressure shear stability analysis".
103, according to the compression allowable stress sigma of the X direction of the rectangular flat plateccrxCompressive working stress sigma in the X directioncxAllowable compressive stress σ in Y-directionccryCompressive working stress sigma in Y directioncyShear allowable stress taucrCalculating the shearing working stress tau:
step 105, searching the values of CurveRx, CurveRy and CurveRs which meet the following formula (1) in the curve data based on a binary search algorithm:
step 107, calculating the safety margin MS of the rectangular flat plate to be K-1;
and step 109, analyzing the stability of the rectangular flat plate according to the safety margin MS.
And the safety margin obtained by calculation is the safety margin of the rectangular flat plate of the airplane structure to be analyzed, so that the stability of the rectangular flat plate of the airplane structure is further analyzed.
By means of the technical scheme of the embodiment of the invention, the embodiment of the invention adopts the steps of carrying out electronic processing on the graph and utilizing subsequent data to search and analyze; and points which accord with a preset formula are searched in the graph by utilizing a dichotomy searching technology, and synchronous amplification of loads in all directions is realized, so that the calculated safety margin has stronger scientificity and reliability, and the stability analysis result of the rectangular flat plate of the airplane structure is more reasonable and reliable.
In order to better understand the above technical solution of the present invention, the following describes the above technical solution of the present invention in detail with reference to a specific embodiment of a rectangular flat plate composite instability analysis calculation.
Firstly, performing electronization treatment on a rectangular flat plate double-pressure shearing buckling related curve to obtain curve data, wherein the abscissa and the ordinate of the curve graph and the value on the curve are respectively marked as CurveRx, CurveRy and CurveRs in the curve data; in fig. 1 and 2, the abscissa is Rx, the ordinate is Ry, the number on the graph is Rs, i.e. a contour line with Rs as a certain number, and then the solving steps are as follows:
firstly, when calculating the composite instability analysis of the stability of the rectangular flat plate, the length-width ratio (i.e. a/b) of the plate is generally calculated, and the example shows a double-pressure shear buckling related curve graph with a/b being 2 shown in fig. 2 and a double-pressure shear buckling related curve graph with a/b being 3 shown in fig. 3;
here, the graphs shown in fig. 2 and 3 are processed electronically, that is, the abscissa, ordinate, and values on the curve corresponding to each point in the graphs are processed into curve data electronically, and the obtained curve data are shown in fig. 4 and 5, respectively. In fig. 4 and 5, X columns represent abscissa Rx (hereinafter, referred to as CurveRx) in the graphs, and as can be seen from fig. 2 and 3, Rx values in the graphs are in the range of [0,1], Y1 in fig. 4 and 5, and Y2 … … Y10 represent the values of ordinate Ry (hereinafter, referred to as CurveRy) on the respective curves on the graph, respectively, for a total of 10; the value of the numeric Rs on each curve (hereinafter referred to as curvars) is defined in the electronized curve data (e.g., database) by a field.
It should be noted that the electronization process of the graph of the rectangular flat plate with the aspect ratio of 2 and 3 is only schematically described here, and the electronization process of the graph of any rectangular flat plate with the aspect ratio of an integer is substantially the same, and therefore, the description thereof is omitted.
In practical application, on one hand, in order to facilitate analysis of the stability of the aircraft structure rectangular flat plates with different aspect ratios, the dual-pressure shear buckling correlation curve graphs of the aircraft structure rectangular flat plates with the integral aspect ratios can be respectively subjected to electronic processing to obtain various curve data corresponding to the different aspect ratios; on the other hand, the specific ratio of the length to the width of the aircraft structure rectangular flat plate with stability can be calculated according to needs, and the double-pressure shear buckling related curve graph with the corresponding ratio is selected for electronic processing, so that curve data corresponding to the aspect ratio of the aircraft structure rectangular flat plate needing to be analyzed currently is obtained, and the system calculation amount is reduced.
Wherein, for the same rectangular flat plate unit, the allowable stress value is invariable under the condition that the material characteristics (elastic modulus, Poisson ratio and yield stress) and the geometric characteristics (length, width and thickness) are determined, namely the compressive allowable stress sigma in the X direction is invariableccrxAllowable compressive stress σ in Y-directionccryShear allowable stress τ of rectangular flat platecrFor a determined value, the compressive working stress σ in the X directioncxCompressive working stress σ in the Y-directioncyThe shear working stress tau is the stress result of finite element calculation on the rectangular flat plate unit, therefore, can be based on the rectangular flat plateActual stress calculation of the plate elements Rx, Ry, Rs:
then, the values of CurveRx, CurveRy and CurveRs which satisfy the following formula (1) are searched in the corresponding curve data based on a binary search algorithm:
specifically, when the ratio of the length to the width of the rectangular flat plate of the aircraft structure is an integer, for example, the ratio is 2, then curve data with the ratio of 2 (i.e., the data shown in fig. 4) is selected from a plurality of curve data corresponding to different ratios; and finds the points satisfying equation (1) (i.e., the values of CurveRx, CurveRy, and CurveRs) from the data shown in fig. 4. As can be seen from the foregoing step of performing the electronization process, the abscissa Rx of a point on any curve is represented by CurveRx, the ordinate Ry is represented by CurveRy in the curve data, and the value Rs on the curve is represented by CurveRs in the curve data.
Therefore, it is only necessary to search the curve data shown in fig. 4 for a point on the curve shown in fig. 2, so that the values of CurveRx, CurveRy and CurveRs at the point are respectively the same as the corresponding ratios of Rx, Ry and Rs calculated by using various stresses in the foregoing, and the ratio is denoted by k.
If the length-width ratio a/b of the rectangular flat plate of the aircraft structure has a decimal value of 2.5, i.e., between 2 and 3, then curve data (i.e., curve data corresponding to fig. 3 and 4) of two integer ratios adjacent to 2.5 (i.e., ratios of 2 and 3) are selected from the plurality of curve data corresponding to different ratios; and newton interpolation calculations are performed between the curve data of fig. 3 and fig. 4 to find the values of CurveRx, CurveRy, and CurveRs that satisfy equation (1).
Thus, when the aspect ratio of the rectangular flat plate is not matched with the aspect ratio corresponding to the original curve graph, calculation can be carried out by utilizing a Newton interpolation method, and the method has sufficient practicability.
It should be noted that the abscissa, ordinate, and value on the curve in the graphs shown in fig. 2 and 3 represent the same meanings as those of Rx, Ry, and Rs calculated based on the actual stress of the rectangular flat plate unit, except that they are theoretical values in the graphs, and the calculated values are actual values.
Then, the safety margin MS of the rectangular plate can be calculated, i.e., MS — K-1.
Finally, the stability of the rectangular plate can be analyzed according to the safety margin MS. Specifically, when the stability of the rectangular flat plate is analyzed according to the safety margin MS, it may be determined whether the safety margin MS is greater than zero; if the judgment result is larger than zero, the stability of the rectangular flat plate is determined to be good; and if the judgment is less than zero, determining that the stability of the rectangular flat plate is poor.
Wherein, in one embodiment, when looking up the values of CurveRx, CurveRy, and CurveRs that satisfy the formula (1) in the curve data based on a binary search algorithm, it is first determined that the condition is satisfied: and after two adjacent iterations, when the absolute value of the difference value between CurveRyi/Ry and tempRx/Rx is less than 0.001, the formula (1) is considered to be satisfied.
The basic idea of calculating the safety margin by the dichotomy is to use the ratio of the ith RxAnd the ratio of the i +1 th searchPerforming subtraction, and if the absolute value of the difference is less than or equal to 0.001, K is CurveRyi+1Ry, safety margin sought
It should be noted that although in the present embodiment it will beCompared with 0.001, but those skilled in the art should understand that the value of the comparison object is not limited to 0.001, but may be 0.002, 0.01, etc., that is, the value of the comparison object here may be flexibly set according to the precision requirement of the actual application scenario, if the precision requirement is high, the value of the comparison object is relatively small and is closer to 0, and if the precision requirement is low, the value of the comparison object is only less than 0.05.
The implementation steps are shown in fig. 7, and specifically include:
A. obtaining Rx, Rs, Ry, CurveRy calculated according to the above stresses as a result of performing S001 shown in fig. 6;
defining a logic judgment variable criterion loop for judging whether the sign of the MS is changed in the iteration process, wherein the initial value is false;
defining an initial value start and end for representing that when the signs of two adjacent iterations are changed, an initial tempRx and an end tempRx represent that an iteration result is to be generated between the start and the end;
defining temporary variables tempRx and tempRs for storing the input of an S001 file in the iteration process;
defining number K for calculating a temporary ratio;
defining a dynamic array ListMS for recording the difference value of K/Ry and tempRx/Rx;
a dynamic array ListRx, ListRs is defined for recording tempRx, tempRy during each iteration of the loop.
B. Let tempRx and tempRs be Rx and Rs, i.e. input calculated Rx and Rs, and look up the curve data to obtain the first CurveRy1, because tempRx/Rx is 1 and tempRs/Rs is 1. Thus, at this time Rx, Rs is equivalent to a 1-fold magnification, the difference CurveRy1/Ry-tempRx/Rx is calculated, i.e., CurveRy1/Ry-1, and stored in ListMS ifIt means that the currently searched value is in accordance with the safety margin calculation formula (1), and the safety margin MS is CurveRy 1/Ry-1.
C. If the value curveRy1 obtained by checking the curve for the first time does not satisfy the safety margin formula (1), that is, curveRy1/Ry-1>0.001, the multiples of Rx and Rs are multiplied by the same proportional value (curveRy1/Ry +1)/2 by bisection, the multiplication results are respectively represented by tempRx and tempRs, and the difference (for example, a number less than 0) between curveRy/Ry and tempRx/Rx executed this time is recorded by ListMS, ListRx records tempRx executed this time, and ListRs records tempRs executed this time.
D. Taking the tempRx and tempRs of the current time as input to continue to execute S001 curve searching;
E. if the calculation formula (1) of the safety margin can be met, the safety margin MS is CurveRy2/Ry- (CurveRy1/Ry + 1)/2;
F. if not, firstly judging the symbol of the last ListMS [ i ] (namely the difference value between CurveRy/Ry and tempRx/Rx);
G. if the symbol of the F-th step is the same as the symbol of the last adjacent step, then judging the logic variable criterion loop, if the symbol is false, using dichotomy to amplify the tempRx and the multiple of tempRs by (CurveRy/Ry + tempRx/Rx)/2 times, recording ListMS, ListRx and ListRs, and continuing to execute the step D;
H. if the sign of the F-th step is different from the sign of the last adjacent step, the reverse signs of ListMS [ i-1] and ListMs [ i ] are described, if the logic variable criterion Loop is false, then start is ListRx [ i-1]/Rx, end is ListRx [ i ]/Rx, the value of iteration is generated between satrt and end, the binary method is used to amplify (start + end)/2 times the tempRx, the logic variable criterion Loop is changed to true, and D is executed;
I. if ListMS [ i ] and ListMS [ i-1] have the same sign after the H step is executed, the ratio of tempRx is still larger, the value of start is not changed at the moment, and end is ListRx [ i ]/Rx, tempRx and tempRy continue to amplify (start + end)/2 times, and D is executed;
J. if the ListMS [ i ] and the ListMS [ i-1] have opposite signs after the H step is executed, the value of tempRx is smaller, at this time, the value of start is ListRx [ i ]/Rx, and the value of end is unchanged, the tempRx and tempRy continue to amplify (start + end)/2 times, and D is executed;
K. and ending the loop until the condition is met.
According to the embodiment of the invention, a curve value searching method searched in a rectangular flat plate composite stability general formula in a structural stability design manual is improved, so that the compression load in the X direction, the compression load in the Y direction and the shearing load are increased synchronously, the calculation result of the safety margin is more reasonable, and the stability analysis result of the rectangular flat plate of the aircraft structure is more reasonable and has more referential significance.
It should be noted that, for simplicity of description, the method embodiments are described as a series of acts or combination of acts, but those skilled in the art will recognize that the present invention is not limited by the illustrated order of acts, as some steps may occur in other orders or concurrently in accordance with the embodiments of the present invention. Further, those skilled in the art will appreciate that the embodiments described in the specification are presently preferred and that no particular act is required to implement the invention.
Corresponding to the method provided by the embodiment of the present invention, referring to fig. 8, a structural block diagram of an embodiment of a stability analysis apparatus for an aircraft structural rectangular flat plate according to the present invention is shown, and specifically, the structural block diagram may include the following modules:
the electronic processing module 81 is configured to perform electronic processing on the dual-pressure shear buckling related curve graph of the rectangular flat plate to obtain curve data, wherein the abscissa and the ordinate of the curve graph and values on the curve are respectively marked as CurveRx, CurveRy and CurveRs in the curve data;
a first calculation module 82 for calculating a compressive allowable stress σ according to the X-direction of the rectangular flat plateccrxAllowable compressive stress σ in Y-directionccryShear allowable stress taucrCompressive working stress sigma in the X directioncxCompressive working stress sigma in Y directioncxCalculating the shearing working stress tau:
a searching module 83, configured to search the curve data for values of CurveRx, CurveRy, and CurveRs that satisfy the following formula (1) based on a binary search algorithm:
a second calculating module 84, configured to calculate a safety margin MS of the rectangular flat plate, which is K-1;
and the analysis module 85 is used for analyzing the stability of the rectangular flat plate according to the safety margin MS.
The electronic processing module 81 is configured to perform electronic processing on the dual-pressure shear-buckling correlation curve graph on the rectangular flat plate with the integral ratio of the length to the width, and obtain various curve data corresponding to different ratios.
The searching module 83 is further configured to select curve data corresponding to the ratio of the length to the width of the rectangular flat plate from the plurality of kinds of curve data corresponding to different ratios to search for the values of CurveRx, CurveRy, and CurveRs that satisfy the formula (1) when the ratio of the length to the width of the rectangular flat plate is an integer.
Optionally, the apparatus further comprises:
a selecting module (not shown) for selecting curve data of two integer ratios adjacent to the decimal when the ratio of the length to the width of the rectangular flat plate is the decimal; corresponding to
The searching module 83 is further configured to perform a newton difference calculation between curve data of two integer ratios adjacent to the decimal to search for values of CurveRx, CurveRy, and CurveRs that satisfy the formula (1).
Further, the analysis module 85 includes:
a first judgment sub-module (not shown) for judging whether the safety margin MS is greater than zero;
a first determination submodule (not shown) for determining that the stability of the rectangular flat plate is good if the judgment is larger than zero;
and a second determining sub-module (not shown) for determining that the stability of the rectangular flat plate is poor if the judgment is less than zero.
The lookup module 83 may include:
a representation submodule (not shown) for representing an iteration variable of Rx by tempRx, an iteration variable of Rs by tempRs, and an ith iteration result of an ordinate found in the curve data using tempRx and tempRs by CurveRyi;
a bisection calculation sub-module (not shown) for multiplying the calculated Rx and Rs by the same proportional value respectively by a bisection method to obtain the tempRx and tempRs;
wherein,wherein,the proportional value multiplied by the loop iteration of Rx and Rs is given, and in the first iteration, i is 1, tempRx is Rx, tempRs is Rs;
a lookup sub-module (not shown) for looking up CurveRyi corresponding to the tempRx, tempRs in the curve data;
a first calculating submodule (not shown) for calculating a ratio of the CurveRyi to the calculated Ry to obtain CurveRyi/Ry;
a second calculating submodule (not shown) for calculating a ratio of tempRx to the calculated Rx, resulting in tempRx/Rx;
a recording sub-module (not shown) for recording a difference between CurveRyi/Ry and tempRx/Rx to obtain CurveRyi/Ry-tempRx/Rx and an absolute value of the difference to obtain | CurveRyi/Ry-tempRx/Rx |;
a second judgment sub-module (not shown) for judging whether | CurveRyi/Ry-tempRx/Rx | is less than or equal to 0.001;
a third determining submodule (not shown) for determining whether the current value is greater than the first valueThen, K is determined as CurveRyi/Ry.
A variable assignment module (not shown) for making a variable start equal to the ratio of tempRx to Rx at the i-1 st time and making a variable end equal to the ratio of tempRx to Rx at the i-th time when | CurveRyi/Ry-tempRx/Rx | is greater than 0.001 and when it is determined that the difference between the ratio of CurveRyi to Ry after the i-th iteration CurveRyi/Ry and the ratio of tempRx to Rx is opposite in sign to the difference calculated at the 1 st time;
the bisection computation submodule (not shown) is further configured to multiply the tempRs and the tempRs by the same proportional value between start and end respectively by using a binary search method, and perform the iteration step of the bisection method until the requirement of the same proportional value between start and end is metThe iteration is exited.
According to the embodiment of the invention, a curve value searching method searched in a rectangular flat plate composite stability general formula in a structural stability design manual is improved, so that the compression load in the X direction, the compression load in the Y direction and the shearing load are increased synchronously, the calculation result of the safety margin is more reasonable, and the stability analysis result of the rectangular flat plate of the aircraft structure is more reasonable and has more referential significance.
For the device embodiment, since it is basically similar to the method embodiment, the description is simple, and for the relevant points, refer to the partial description of the method embodiment.
The embodiments in the present specification are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, apparatus, or computer program product. Accordingly, embodiments of the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, embodiments of the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
Embodiments of the present invention are described with reference to flowchart illustrations and/or block diagrams of methods, terminal devices (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing terminal to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing terminal, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing terminal to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing terminal to cause a series of operational steps to be performed on the computer or other programmable terminal to produce a computer implemented process such that the instructions which execute on the computer or other programmable terminal provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
While preferred embodiments of the present invention have been described, additional variations and modifications of these embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the embodiments of the invention.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or terminal that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or terminal. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or terminal that comprises the element.
The method for analyzing the stability of the aircraft structure rectangular flat plate and the device for analyzing the stability of the aircraft structure rectangular flat plate provided by the invention are described in detail, specific examples are applied in the text to explain the principle and the implementation mode of the invention, and the description of the examples is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (14)
1. A method for analyzing the stability of a rectangular flat plate of an airplane structure is characterized by comprising the following steps:
performing electronization processing on a curve graph of the rectangular flat plate double-pressure shearing buckling related curve to obtain curve data, wherein the abscissa and the ordinate of the curve graph and values on the curve are respectively marked as CurveRx, CurveRy and CurveRs in the curve data;
allowable compressive stress sigma in X direction of rectangular flat plateccrxAllowable compressive stress σ in Y-directionccryShear allowable stress taucrCompressive working stress sigma in the X directioncxCompressive working stress sigma in Y directioncyCalculating the shearing working stress tau:
finding values of CurveRx, CurveRy, and CurveRs in the curve data that satisfy the following equation (1) based on a binary search algorithm:
calculating the safety margin MS of the rectangular flat plate as K-1;
and analyzing the stability of the rectangular flat plate according to the safety margin MS.
2. The method of claim 1, wherein the step of electronically processing the dual-pressure shear buckling correlation plot of the rectangular flat plate to obtain curve data comprises:
and respectively carrying out electronization treatment on the double-pressure shearing buckling related curve graphs on the rectangular flat plates with the integral ratio of the length to the width to obtain various curve data corresponding to different ratios.
3. The method as claimed in claim 2, wherein when the ratio of the length to the width of the rectangular flat plate is an integer, selecting the curve data corresponding to the ratio of the length to the width of the rectangular flat plate from the plurality of curve data corresponding to different ratios to find the values of CurveRx, CurveRy and CurveRs satisfying the formula (1).
4. The method of claim 2, further comprising:
when the ratio of the length to the width of the rectangular flat plate is a decimal, selecting curve data with two integer ratios adjacent to the decimal from the multiple kinds of curve data corresponding to different ratios;
the calculation of the newton difference method is performed between the curve data of the two integer ratios adjacent to the decimal to find the values of CurveRx, CurveRy, and CurveRs satisfying the formula (1).
5. The method of claim 1, wherein the step of analyzing the stability of the rectangular plate according to the safety margin MS comprises:
judging whether the safety margin MS is larger than zero;
if the judgment result is larger than zero, the stability of the rectangular flat plate is determined to be good;
and if the judgment is less than zero, determining that the stability of the rectangular flat plate is poor.
6. The method of claim 1, wherein the step of finding the values of CurveRx, CurveRy, and CurveRs that satisfy the formula (1) in the curve data based on a binary search algorithm comprises:
the iteration variable of Rx is represented by tempRx, the iteration variable of Rs is represented by tempRs, and the ith iteration result of the ordinate searched in the curve data by using tempRx and tempRs is represented by CurveRyi;
multiplying the calculated Rx and Rs by the same proportional value respectively through a bisection method to obtain the tempRx and the tempRs;
wherein,wherein,the proportional value multiplied by the loop iteration of Rx and Rs is given, and in the first iteration, i is 1, tempRx is Rx, tempRs is Rs;
searching CurveRyi corresponding to the tempRx and tempRs in the curve data;
calculating the ratio of the CurveRyi to the Ry obtained by calculation to obtain CurveRyi/Ry;
calculating the ratio of tempRx to the Rx obtained through calculation to obtain tempRx/Rx;
recording the difference value between CurveRyi/Ry and tempRx/Rx to obtain CurveRyi/Ry-tempRx/Rx and the absolute value of the difference value to obtain | CurveRyi/Ry-tempRx/Rx |;
judging whether | CurveRyi/Ry-tempRx/Rx | is less than or equal to 0.001;
when in useThen, K is determined as CurveRyi/Ry.
7. The method of claim 6, wherein the step of searching the curve data for values of CurveRx, CurveRy, and CurveRs that satisfy the formula (1) based on a binary search algorithm when | CurveRyi/Ry-tempRx/Rx | is greater than 0.001 further comprises:
when the difference between the ratio of CurveRyi to Ry after the ith iteration and the ratio of tempRx/Rx of tempRx and Rx after the ith iteration is judged to be opposite to the sign of the difference calculated at the 1 st time, a variable start is made to be equal to the ratio of tempRx to Rx at the i-1 st time, and a variable end is made to be equal to the ratio of tempRx to Rx at the ith time;
multiplying Rx and Rs by the same proportion value between start and end by a binary search method to obtain tempRx and tempRs, and performing iteration steps of the dichotomy until the conditions are metThe iteration is exited.
8. An aircraft structure rectangular flat plate stability analysis device, comprising:
the system comprises an electronization processing module, a data processing module and a data processing module, wherein the electronization processing module is used for performing electronization processing on a curve graph of a rectangular flat plate double-pressure shearing buckling related curve to obtain curve data, and the abscissa and the ordinate of the curve graph and values on the curve are respectively marked as CurveRx, CurveRy and CurveRs in the curve data;
a first calculation module for calculating a compressive allowable stress σ in the X direction of the rectangular flat plateccrxAllowable compressive stress σ in Y-directionccryShear allowable stress taucrCompressive working stress sigma in the X directioncxCompressive working stress sigma in Y directioncyCalculating the shearing working stress tau:
a searching module, configured to search the curve data for values of CurveRx, CurveRy, and CurveRs that satisfy the following formula (1) based on a binary search algorithm:
the second calculation module is used for calculating the safety margin MS of the rectangular flat plate to be K-1;
and the analysis module is used for analyzing the stability of the rectangular flat plate according to the safety margin MS.
9. The device of claim 8, wherein the electronic processing module is configured to perform electronic processing on the dual-pressure shear buckling correlation graph for rectangular flat plates with integral length-width ratios to obtain multiple curve data corresponding to different ratios.
10. The apparatus of claim 9, wherein the searching module is further configured to select the curve data corresponding to the ratio of the length to the width of the rectangular flat plate from the plurality of curve data corresponding to different ratios to search for the values of CurveRx, CurveRy, and CurveRs satisfying the formula (1) when the ratio of the length to the width of the rectangular flat plate is an integer.
11. The apparatus of claim 9, further comprising:
the selection module is used for selecting curve data of two integer ratios adjacent to the decimal in the multiple kinds of curve data corresponding to different ratios when the ratio of the length to the width of the rectangular flat plate is the decimal; corresponding to
The searching module is further used for performing Newton difference calculation between curve data of two integer ratios adjacent to the decimal to search the values of CurveRx, CurveRy and CurveRs which meet the formula (1).
12. The apparatus of claim 8, wherein the analysis module comprises:
the first judgment submodule is used for judging whether the safety margin MS is larger than zero or not;
the first determining submodule is used for determining that the stability of the rectangular flat plate is good if the judgment is larger than zero;
and the second determining submodule is used for determining that the stability of the rectangular flat plate is poor if the judgment is less than zero.
13. The apparatus of claim 8, wherein the lookup module comprises:
a representation submodule, configured to represent an iteration variable of Rx by tempRx, represent an iteration variable of Rs by tempRs, and represent an ith iteration result of a ordinate found in the curve data by tempRx and tempRs by CurveRyi;
a bisection calculation submodule, configured to multiply the calculated Rx and Rs by the same proportional value respectively through a bisection method to obtain the tempRx and the tempRs;
wherein,wherein,the proportional value multiplied by the loop iteration of Rx and Rs is given, and in the first iteration, i is 1, tempRx is Rx, tempRs is Rs;
the searching submodule is used for searching CurveRyi corresponding to the tempRx and tempRs in the curve data;
the first calculation submodule is used for calculating the ratio of the CurveRyi to the Ry obtained through calculation to obtain CurveRyi/Ry;
the second calculation submodule is used for calculating the ratio of tempRx to the Rx obtained through calculation to obtain tempRx/Rx;
the recording submodule is used for recording the difference value between CurveRyi/Ry and tempRx/Rx to obtain CurveRyi/Ry-tempRx/Rx and the absolute value of the difference value to obtain | CurveRyi/Ry-tempRx/Rx |;
the second judgment submodule is used for judging whether | CurveRyi/Ry-tempRx/Rx | is less than or equal to 0.001;
a third determination submodule for determining whether the current value is greater than the first valueThen, K is determined as CurveRyi/Ry.
14. The apparatus of claim 13, wherein the lookup module further comprises:
a variable assignment module, configured to, when | CurveRyi/Ry-tempRx/Rx | is greater than 0.001 and when it is determined that a difference between a ratio CurveRyi/Ry of CurveRyi to Ry and a ratio tempRx/Rx of tempRx and Rx is opposite to the difference sign calculated at the 1 st time after the ith iteration, make a variable start equal to a ratio of tempRx and Rx at the i-1 st time, and make a variable end equal to a ratio of tempRx and Rx at the i-th time;
the dichotomy calculation submodule is also used for multiplying the Rx and the Rs by the same proportion value between the start and the end by a binary search method to obtain tempRx and tempRs respectively, and performing iteration steps of the dichotomy until the conditions are metThe iteration is exited.
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| CN105197253A (en) * | 2015-08-14 | 2015-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Safety margin calculation method of wing reinforced wallboard |
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| CN104778309A (en) * | 2015-03-19 | 2015-07-15 | 合科软件（北京）有限责任公司 | Airplane structure strength checking method and device |
| CN105197253A (en) * | 2015-08-14 | 2015-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Safety margin calculation method of wing reinforced wallboard |
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