CN114357827A - Method for acquiring stress spectrum of structural key part influenced by deflection of control surface - Google Patents
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Abstract
The invention belongs to the technical field of airplane fatigue strength design, and particularly relates to a method for a stress spectrum of a structural key part influenced by deflection of a control surface. The method is based on the technologies of automatic deflection of the control surface, batch processing calculation under multiple working conditions, automatic extraction of loads and the like, the intersection point load of the control surface under the condition of thousands of deflection angles of the control surface is quickly acquired, a method for constructing a linear equation of a stress component and an intersection point load component of a key part of a structure influenced by deflection of the control surface in a classified manner through load partitioning is provided, a stress spectrum of the key part meeting the design requirements of the durability and damage tolerance of the structure influenced by deflection of the control surface is effectively acquired, and the design efficiency of the durability and damage tolerance of the structure is improved.
Description
Technical Field
The invention belongs to the technical field of airplane fatigue strength design, and particularly relates to a method for a stress spectrum of a structural key part influenced by deflection of a control surface.
Background
The control surface is a key component for normal operation of the airplane and ensuring flight safety, and a main bearing structure for transmitting the load of the control surface needs to have excellent durability and damage tolerance characteristics.
For a general structure which is not influenced by skewness, the stress of the key part is generally in a linear relation with the external total load, and the stress of the key part of all other working conditions can be obtained according to the analysis results of a few working conditions to obtain the stress spectrum of the key part. However, for the structure affected by the deflection of the control surface, the deflection degree of the control surface is different in different flight states and different maneuvering types, the stress of the key part and the external total load such as the hinge moment and the intersection point load are not necessarily in a linear or nonlinear relationship, and the stress spectrum of the key part cannot be obtained according to the method of a general structure.
In an airplane design spectrum, thousands of control plane skewness are included, and when the durability and damage tolerance design of an airplane is developed, three-dimensional detail stress analysis of a structure needs to be firstly developed to determine key parts and stress distribution of the structure under different skewness. In the existing method, the skewness of a control plane in a complete machine finite element model needs to be changed in finite element pretreatment software through manual operation, a three-dimensional stress field of a structure under each skewness is solved, the workload is large, the efficiency is low, the requirement of the progress of airplane design is not met, and the analysis of all skewness is unrealistic.
Therefore, aiming at the structure influenced by the deflection of the control surface, the invention provides a method for acquiring the stress spectrum of the key part of the structure influenced by the deflection of the control surface, and provides a method for constructing the relation between the stress component and the intersection point load component through load classification and classification by realizing the functions of automatic deflection of the control surface, multi-working-condition batch processing calculation, automatic load extraction and the like, so that the stress spectrum of the key part meeting the design requirements of the durability and damage tolerance of the structure influenced by the deflection of the control surface is acquired, and the design efficiency of the durability and damage tolerance of the structure is improved.
Disclosure of Invention
The purpose of the invention is as follows: the method for acquiring the stress spectrum of the key part of the structure influenced by the deflection of the control surface is provided, the problems of long period and low efficiency caused by acquiring the stress spectrum by calculating thousands of deflection conditions are avoided, and the design efficiency of the durability and damage tolerance of the structure influenced by the deflection of the control surface is improved.
The technical scheme of the invention is as follows: in order to achieve the above object, a method for obtaining a stress spectrum of a structural key part affected by deflection of a control surface is provided, which comprises the following steps:
the first step is as follows: in the whole-machine finite element model, the relative position of each finite element node on the control surface and the whole machine can be controlled by the reference coordinate system of the control surface, so that the reference coordinate system of the control surface is deflected by a batch processing program according to the actual control surface deflection of each working condition in the whole-machine design spectrum, the deflection of the control surface on the physics is replaced, and the whole-machine finite element stress analysis calculation file under different control surface deflections in the design spectrum is obtained;
the second step is that: submitting the calculation file of the first step to a solver for calculation, and rapidly acquiring control surface intersection point loads of thousands of working conditions with different control surface skewness in a design spectrum by adopting an automatic load extraction tool;
the third step: calculating the resultant force of the load at the intersection point of the second step and an included angle between the resultant force and the selected reference coordinate axis, and dividing the load into k types at equal intervals according to the angle between the resultant force and the reference coordinate axis;
the fourth step: selecting a working condition as a typical working condition at a certain angle in each class according to the load classification in the third step;
the fifth step: extracting boundary load of the main bearing structure influenced by deflection of the control surface under the skewness of the typical working condition of the fourth step in a batch processing mode;
and a sixth step: establishing a three-dimensional entity detail finite element model of the structure influenced by the deflection of the control surface, applying the boundary load of the typical working condition of the fifth step, and calculating to obtain a three-dimensional stress field of the main bearing structure influenced by the deflection of the control surface;
the seventh step: determining structural key parts according to the analysis result of the sixth step, and extracting the maximum or minimum principal stress and six stress components of the key parts under typical working conditions; the determination principle of the key parts is as follows: selecting the parts with the maximum absolute value of the principal stress or the parts with the principal stress exceeding 50% of the material strength limit, classifying the detail characteristics of the parts, and selecting the parts with the maximum absolute value of the principal stress in each class as key parts;
eighth step: for each load classification obtained in the third step, selecting two working conditions with the maximum main stress of the key part as reference working conditions, establishing a linear equation set of each stress component and the intersection point load component by adopting a formula (1), and solving to obtain a weight coefficient of each load component under each stress component;
a ninth step of predicting stress components of the key parts in each load classification in the third step under each working condition according to intersection point loads of the structures influenced by deflection of the control surface under each working condition in the design spectrum in the second step by using the weight coefficients obtained in the eighth step;
and tenth step, calculating to obtain the maximum or minimum principal stress of the key part under each working condition of the design spectrum by adopting a principal stress calculation formula in the elastic mechanics according to the stress component in the ninth step, thereby obtaining the stress spectrum of the key part of the structure influenced by the deflection of the control surface under the actual deflection.
In one possible embodiment, in the third step, the value interval of the number k of load classifications is [4,72], the minimum value of the number k of load classifications is 4, that is, the interval is 90 degrees, and the maximum value k is 72, that is, the interval is 5 degrees. Within this range, an appropriate k value can be obtained according to the actual situation and the prediction accuracy of the principal stress of the critical portion.
In a possible embodiment, in the fourth step, the interval angle is in direct proportion to the distance in the third step, the value interval is [5 degrees ], 30 degrees ], the distance can be selected at unequal intervals according to the actual distribution condition of the included angle between the resultant force and the reference coordinate axis, and the typical load working condition of each type of load is at least 2 and at most no more than 7.
In a possible embodiment, in said seventh step, if the critical part is under tensile stress, it is extractedMaximum principal stress and 6 stress components; otherwise, the minimum principal stress and 6 stress components are extracted. The stress component is denoted as σijWhere σ isij＝σji，i,j＝1,2,3，σ11＝σxRepresents the positive stress, σ, in the x-direction in a rectangular coordinate system22＝σyRepresents the positive stress, σ, in the y-direction in a rectangular coordinate system33＝σzRepresenting the positive stress, σ, in the z-direction in a rectangular coordinate system12＝σ21＝τxy＝τyxRepresents shear stress, σ, in the xy plane13＝σ31＝τxz＝τzxExpressing shear stress, σ, in the xz plane23＝σ32＝τyz＝τzyRepresenting the shear stress in the yz plane.
In one possible embodiment, in the eighth step, a linear equation is constructed according to the 6 stress components and the intersection load component of the selected 2 working conditions, and the linear equation is in the form of:
wherein, Fy、FzLoad components in the y direction and the z direction which are vertical to a rotating shaft of the control surface under a local coordinate system of the control surface are respectively shown, subscripts 1 and 2 respectively represent a selected reference working condition 1 and a selected reference working condition 2, aij、bijRespectively representing loads Fy、FzTo the stress component σijThe weight coefficient of (2).
In a possible embodiment, in the tenth step, the stress component data of the ninth step is adopted, and the maximum principal stress and the minimum principal stress of the critical part are simultaneously calculated, and the stress in the stress spectrum of the critical part is taken as the stress with a large absolute value.
The invention has the beneficial effects that: the method is based on the technologies of automatic deflection of the control surface, batch processing calculation under multiple working conditions, automatic extraction of load and the like, the intersection point load of the control surface under the condition of thousands of deflection angles of the control surface is quickly acquired, a method for constructing the linear equation of the stress component and the intersection point load component of the key part of the structure influenced by deflection of the control surface in a classified manner through load partitioning is provided, the stress spectrum of the key part meeting the design requirements of the durability and damage tolerance of the structure influenced by deflection of the control surface is effectively acquired, and the design efficiency of the durability and damage tolerance of the structure is improved.
Drawings
FIG. 1 is a flow chart of a method of the present invention;
FIG. 2 is a classification schematic of the load classification method in the third step according to the preferred embodiment of the present invention;
FIG. 3 is a schematic diagram of three-dimensional stress field distribution and determined key parts of an integral aileron joint affected by the deflection of a control surface under a typical working condition LC1215 in the preferred embodiment of the invention;
FIG. 4 is a stress spectrum of a critical part of the integral aileron joint affected by the deflection of the control surface obtained by the method of the preferred embodiment of the present invention;
FIG. 5 is a linear fitting graph between the principal stress analysis value and the principal stress prediction value of the verification condition (typical condition except the reference condition) in the preferred embodiment of the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Take the outer intersection point lug of the integral joint of the aileron of an airplane as an example. As shown in fig. 1, a method for acquiring a stress spectrum of a structural key part affected by deflection of a control surface comprises the following steps:
firstly, in a whole-aircraft total finite element model, setting reference coordinate systems of all nodes of an aileron as a reference coordinate system of a control surface, outputting a calculation file, and automatically modifying deflection angles of the reference coordinate system of the aileron in the calculation file in batches by adopting a batch processing program according to actual aileron deflection of each working condition in a design spectrum to obtain a whole-aircraft finite element stress analysis calculation file under different aileron deflection in the design spectrum;
the second step is that: submitting the batch calculation file in the first step to a solver for calculation, and efficiently acquiring the loads of 3 tab intersection points of the integral joints of the ailerons under partial working conditions of all aileron skewness of a design spectrum by adopting a developed automatic load extraction tool, wherein for the outer intersection points, the lateral load Fx is small compared with Fy and Fz and is ignored;
TABLE 1 Point load of integral aileron joints under partial operating conditions
The third step: according to the intersection point load data of each ear intersection point, calculating the angle of the resultant force and the reference coordinate axis, and dividing the loads into k types at equal intervals, wherein k is 4 as an embodiment, that is, the loads are divided into 4 types: (Fy +, Fz +), (Fy-, Fz-), (Fy +, Fz-), see FIG. 2;
the fourth step: in each class, a plurality of working conditions are selected as typical working conditions at certain intervals. Table 2 shows typical operating conditions for each load class, which total 16, as shown in table 2;
table 2 exemplary conditions selected
The fifth step: extracting boundary load of the integral aileron joint under the skewness of 16 typical working conditions in the fourth step in a batch processing mode;
and a sixth step: establishing a three-dimensional entity detail finite element model of the integral aileron joint, applying the boundary load of the typical working condition extracted in the fifth step, and calculating to obtain a three-dimensional stress field of the integral aileron joint, wherein the maximum principal stress cloud picture of the integral aileron joint under the typical working condition LC1215 is shown in FIG. 3;
the seventh step: according to the analysis result of the sixth step, the maximum absolute value of the principal stress of the integral aileron joint is 499MPa, which is not more than 50% of the strength limit of the joint material, so that the critical part of the integral aileron joint is determined as the critical part in the R region inside the ear root at the outer intersection point, as shown in fig. 3. Extracting the maximum or minimum main stress and six stress components of the key part under 16 typical working conditions in an analysis result;
eighth step: for 4 types of load classification, selecting two working conditions with the maximum principal stress at the key part of the outer intersection point of the integral aileron joint, establishing a linear equation of each stress component and the load component of the intersection point, and solving to obtain the weight coefficient of each load component under each stress component, which is shown in table 3;
TABLE 3 weight coefficient of load component under each stress component calculated by the present invention
The ninth step, adopting the weight coefficients of the table 3, and predicting to obtain 6 stress components of the key parts in 4 types under each working condition according to the external intersection point load of the integral joint of the aileron, which takes the actual deflection of the aileron into consideration under the design spectrum extracted in the second step;
and tenth, calculating to obtain the maximum or minimum main stress of the key part under each working condition of the design spectrum according to the stress component in the ninth step by adopting a main stress calculation formula in the elasticity mechanics, and obtaining the stress spectrum of the key part of the integral joint of the aileron considering the actual deflection of the aileron, wherein the stress spectrum is shown in fig. 4.
The typical working conditions in each load classification are used as verification working conditions except the reference working conditions used for determining the load weight coefficient, the remaining typical working conditions are used for verifying the prediction accuracy of the load, and the table 4 gives the ratio of the main stress analysis values of the working conditions to the main stress prediction value adopting the method of the invention, so that the error is within 5 percent for the larger load condition with higher stress of the key part, the large load is the main contributor of fatigue damage, the contribution of the small load is relatively smaller, and the larger error of the small load is acceptable. It can also be seen from fig. 5 that the analyzed principal stress values of the verified condition have a good linear relationship with the predicted principal stress values, and the linear goodness of fit reaches 0.9964. Therefore, the method for acquiring the stress spectrum of the key part of the structure influenced by the deflection of the control surface improves the efficiency, meets the requirements of the durability and damage tolerance analysis of the structure and provides a feasible engineering method for acquiring the stress spectrum of the key part of the structure.
TABLE 4 comparison of principal stress analysis and predicted values for typical conditions except for reference conditions
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A method for acquiring a stress spectrum of a structural key part influenced by deflection of a control surface is characterized by comprising the following steps:
the first step is as follows: in the whole-machine finite element model, the relative position of each finite element node on the control surface and the whole machine can be controlled by the reference coordinate system of the control surface, so that the reference coordinate system of the control surface is deflected by a batch processing program according to the actual control surface deflection of each working condition in the whole-machine design spectrum, the deflection of the control surface on the physics is replaced, and the whole-machine finite element stress analysis calculation file under different control surface deflections in the design spectrum is obtained;
the second step is that: submitting the calculation file of the first step to a solver for calculation, and rapidly acquiring control surface intersection point loads of thousands of working conditions with different control surface skewness in a design spectrum by adopting an automatic load extraction tool;
the third step: according to the intersection point load data of the second step, dividing the loads into k types at equal intervals according to the angle between the intersection point load resultant force and the reference coordinate axis;
the fourth step: selecting a working condition as a typical working condition at a certain angle in each class according to the load classification in the third step;
the fifth step: extracting boundary load of the structure influenced by deflection of the control surface under the deflection of the typical working condition of the fourth step;
and a sixth step: establishing a three-dimensional entity detail finite element model of the structure influenced by the deflection of the control surface, applying boundary load of the typical working condition of the fifth step, and calculating to obtain a three-dimensional stress field of the structure influenced by the deflection of the control surface;
the seventh step: determining a key part of the structure influenced by the deflection of the control surface according to the analysis result of the sixth step, and extracting the maximum or minimum main stress and six stress components of the key part under typical working conditions;
eighth step: for each load classification in the fourth step, selecting two working conditions with the maximum principal stress absolute value of the key part as reference working conditions, establishing a linear equation of the load component of the intersection point of each stress component and the reference working conditions in the seventh step, and solving to obtain the weight coefficient of each load component under each stress component;
a ninth step of predicting stress components of the key parts under each working condition in the load classification of the third step by using the weight coefficients obtained in the eighth step and according to intersection point loads of the structures influenced by the deflection of the control surface under each working condition in the design spectrum in the second step;
and tenth, calculating to obtain the maximum or minimum principal stress of the key part of the structure influenced by the deflection of the control surface under various working conditions of the design spectrum by adopting an elastic mechanics principal stress calculation formula according to the stress component in the ninth step, thereby obtaining the stress spectrum of the key part of the structure influenced by the deflection of the control surface under actual skewness.
2. The method for acquiring the stress spectrum of the structural key part affected by the deflection of the control surface according to claim 1, wherein in the second step, batch processing control files are compiled, full-machine finite element stress analysis calculation files under different deflection of the control surface are submitted one by one for calculation, intersection point loads of thousands of working conditions with different deflection of the control surface are obtained, and an automatic load extraction tool is adopted to quickly extract the intersection point loads of the control surface under the working conditions.
3. The method for acquiring the stress spectrum of the structural key part affected by the deflection of the control surface according to claim 1, wherein in the third step, the value interval of the number k of the load classification is [4,72 ].
4. The method for acquiring the stress spectrum of the structural key part affected by the deflection of the control surface according to claim 1, wherein in the fourth step, a typical working condition is selected in each load classification in the third step, and the interval angle value interval is [5 degrees, 30 degrees ].
5. The method for acquiring the stress spectrum of the key parts of the structure influenced by the deflection of the control surface as claimed in claim 1, wherein in the fifth step, the boundary load of the structure influenced by the deflection of the control surface is calculated and extracted in a batch processing mode.
6. The method for acquiring the stress spectrum of the structural key parts affected by the deflection of the control surface according to claim 1, wherein in the seventh step, the key parts are determined and the main stress and six stress components of the key parts are extracted, and the principle of determining the key parts is as follows: and selecting the parts with the maximum absolute value of the principal stress or the parts with the principal stress exceeding 50% of the material strength limit, classifying the detailed characteristics of the parts, and selecting the parts with the maximum absolute value of the principal stress in each class as key parts.
7. The method for obtaining the stress spectrum of the structural key part affected by the deflection of the control surface according to claim 1, wherein in the eighth step, two working conditions with the maximum absolute value of the principal stress of the key part are selected as reference working conditions, a linear equation set of each stress component in the seventh step and the corresponding intersection point load component is established, and as shown in formula (1), the weight coefficient of each load component under each stress component is obtained by solving;
wherein σijAs a stress component, σij＝σji，i,j＝1,2,3。σ11＝σxRepresents the positive stress, σ, in the x-direction in a rectangular coordinate system22＝σyRepresents the positive stress, σ, in the y-direction in a rectangular coordinate system33＝σzRepresenting the positive stress, σ, in the z-direction in a rectangular coordinate system12＝σ21＝τxy＝τyxRepresents shear stress, σ, in the xy plane13＝σ31＝τxz＝τzxExpressing shear stress, σ, in the xz plane23＝σ32＝τyz＝τzyRepresenting the shear stress in the yz plane. Fy、FzFor the y-direction and z-direction intersection load components, a and b represent weighting coefficients.
8. The method for obtaining the stress spectrum of the key part of the structure affected by the deflection of the control surface as claimed in claim 1, wherein in the tenth step, a principal stress calculation formula in elastic mechanics is adopted, and according to the stress component in the ninth step, the maximum or minimum principal stress of the key part under each working condition of the design spectrum is calculated, so that the stress spectrum of the key part of the structure affected by the deflection of the control surface under the actual deflection is obtained, and the stress spectrum is used for carrying out the durability and damage tolerance analysis of the structure.
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