CN109684674B - Cabin door pneumatic load processing method - Google Patents
Cabin door pneumatic load processing method Download PDFInfo
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- CN109684674B CN109684674B CN201811470130.6A CN201811470130A CN109684674B CN 109684674 B CN109684674 B CN 109684674B CN 201811470130 A CN201811470130 A CN 201811470130A CN 109684674 B CN109684674 B CN 109684674B
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- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G06F30/00—Computer-aided design [CAD]
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- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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Abstract
The invention belongs to the field of aeroelastic mechanics, and particularly relates to a cabin door pneumatic load processing method. Through the load processing method, the cabin door finite element grid pneumatic load can be directly used, the calculation error is controlled within an acceptable range, the calculation accuracy is high, the operation is simple and quick, and the application is wide.
Description
Technical Field
The invention belongs to the field of aeroelastic mechanics, and particularly relates to a cabin door pneumatic load processing method.
Background
The aerodynamic load calculation and the finite element model calculation both need to divide the appearance of the aircraft into grids, and because the requirements of the self solving precision and efficiency are met in each field, the requirements on the grid density are different, so that the structural finite element grids and the aerodynamic load calculation grids are greatly different in form, and the complete coincidence of the finite element grids and the load calculation grids cannot be ensured. Therefore, a pneumatic data processing method is required to be sought to realize the transmission of pneumatic data on the finite element model calculation grid and the pneumatic load calculation grid, and the efficient and accurate load processing method is also an important means for ensuring the calculation precision of the finite element model.
Disclosure of Invention
The invention aims to: a cabin door pneumatic load processing method is used for guaranteeing the calculation accuracy of a finite element model.
The technical scheme is as follows: a cabin door pneumatic load processing method comprises the following calculation steps:
firstly, reading a pneumatic total load total distance (comprising a pressing center position) file, a pneumatic distribution load (CP value) file and a pneumatic grid model;
step two, reading a cabin door finite element model (comprising node positions, triangle units and quadrilateral units);
thirdly, processing the calculated aerodynamic distribution load (CP value) to the node position of the cabin door finite element model by adopting a spline function interpolation method;
fourthly, node force of each unit is obtained by integrating triangular units and quadrilateral units of the cabin door finite element model;
and fifthly, calculating the total load total distance of the finite element model node force according to the pressing center position, comparing the total load total distance with the original total load total distance of the pneumatic load, analyzing the error, and if the calculated error is within 3%, judging that the calculated error is acceptable, otherwise, adopting a small increment weight correction method to correct the node force, and controlling the error within 3%.
And sixthly, outputting the finite element model node force according to a Nastran reading format.
The beneficial calculation effect is as follows: through the load processing method, the cabin door finite element grid pneumatic load can be directly used, the calculation error is controlled within an acceptable range, the calculation accuracy is high, the operation is simple and quick, and the application is wide.
Drawings
FIG. 1 is a program flow diagram;
FIG. 2 is a schematic view of a finite element model of a pneumatic mesh and a cabin door;
FIG. 3 is a schematic diagram of finite element model node force distribution;
fig. 4 is a diagram of a Nastran read format output.
Detailed Description
A cabin door pneumatic load processing method comprises the following specific calculation steps:
firstly, reading a pneumatic total load total distance (comprising a pressing center position) file, a pneumatic distribution load (CP value) file and a pneumatic grid model;
step two, reading a cabin door finite element model (comprising node positions, triangle units and quadrilateral units), as shown in fig. 1;
thirdly, processing the calculated aerodynamic distribution load (CP value) to the node position of the cabin door finite element model by adopting a spline function interpolation method;
the spline function interpolation method comprises the following steps:
is arranged at N independent points (x i ,y i ) Function value W on (i=1, 2, … …, N) i Given, then the general surface spline function W (x,y) Can be expressed as:
wherein: r is (r) i 2 ＝(x-x i ) 2 +(y-y i ) 2
Epsilon is a small amount and is set for calculating higher derivative and controlling the degree of curvature change urgency of the surface. The general requirements are: epsilon<<min(r i 2 ) (i=1, 2, … …, N and r i Is a value other than 0)
Coefficient K i (i=1, 2, … …, N) and a 0 、a 1 、a 2 Is determined by the following linear equation set:
wherein:
solving equation set (2) to obtain coefficient K i And a 0 、a 1 、a 2 Substituting the formula (1) to obtain the curved spline interpolation function W (x,y) 。
Fourth, node forces of all units are obtained by integrating the bin elements such as the bin door finite element model triangle unit and the quadrilateral unit, and the node forces are shown in figure 2;
and fifthly, calculating the total load total distance of the finite element model node force according to the pressing center position, comparing the total load total distance with the pneumatic load total distance, and analyzing errors. If the calculated error is within 3%, the node force is corrected by adopting a small increment weight correction method, and the error is controlled within 3%, as shown in table 1.
Table 1 cabin door pneumatic load handling error
The small increment weighting correction method comprises the following steps:
let the pneumatic total load total moment be F z 、M x 、M y The node load after load processing is P i (i=1, 2, … …, N), N being the number of finite element nodes, the coordinates of the node positions being x i 、y i 。
Let the weighting coefficient be b 0 、b 1 And b 2 Let the corrected node load P i ' is:
P i '＝P i +P i (b 0 +b 1 x i +b 2 y i )
then there are:
solving the above-mentioned coefficient b 0 、b 1 And b 2 Substituting and calculating the corrected node load P i '。
Sixth, finite element model node forces are output according to the Nastran read format, as shown in FIG. 4.
It can be seen that the cabin door finite element grid pneumatic load can be directly used through the load processing method, the calculation error is controlled within an acceptable range, the calculation accuracy is high, the operation is simple and quick, and the application is wide.
Claims (3)
1. A cabin door pneumatic load processing method is characterized in that: the calculation steps are as follows:
firstly, reading a pneumatic total load total distance file, a pneumatic distribution load file and a pneumatic grid model;
step two, reading a cabin door finite element model;
thirdly, processing the calculated pneumatic distribution load to the node position of the cabin door finite element model by adopting a spline function interpolation method;
fourthly, node force of each unit is obtained by integrating triangular units and quadrilateral units of the cabin door finite element model;
fifthly, calculating the total load total distance of the finite element model node force according to the pressing center position, comparing the total load total distance with the original total load total distance of the pneumatic load, analyzing errors, if the calculated errors are within 3%, and if not, adopting a small increment weighting correction method to correct the node force, and controlling the errors within 3%;
step six, outputting the finite element model node force according to a Nastran reading format;
the spline interpolation method in the third step is as follows:
is arranged at N independent points (x i ,y i ) The method comprises the steps of carrying out a first treatment on the surface of the i=1, 2, … …, N; function value W of the upper part i Given, then the general surface spline function W (x,y) Can be expressed as:
wherein: r is (r) i 2 ＝(x-x i ) 2 +(y-y i ) 2
Epsilon is a small quantity and is set for calculating a high-order derivative and controlling the degree of urgency of curvature change of a curved surface; epsilon<<min(r i 2 ) The method comprises the steps of carrying out a first treatment on the surface of the i=1, 2, … …, N and r i A value other than 0;
coefficient K i And a 0 、a 1 、a 2 Is determined by the following linear equation set:
wherein:
solving equation set (2) to obtain coefficient K i And a 0 、a 1 、a 2 Substituting the formula (1) to obtain the curved spline interpolation function W (x,y) The method comprises the steps of carrying out a first treatment on the surface of the Where i=1, 2, … …, N.
2. A method for pneumatic load handling of a hatch door according to claim 1, characterized by: the small increment weighting correction method comprises the following steps:
let the pneumatic total load total moment be F z 、M x 、M y The node load after load processing is P i The method comprises the steps of carrying out a first treatment on the surface of the i=1, 2, … …, N; n is the number of finite element nodes, and the coordinates of the node positions are x i 、y i ；
Let the weighting coefficient be b 0 、b 1 And b 2 Let the corrected node load P i ' is:
P i '＝P i +P i (b 0 +b 1 x i +b 2 y i )
then there are:
solving the above-mentioned coefficient b 0 、b 1 And b 2 Substituting and calculating the corrected node load P i '。
3. A method for pneumatic load handling of a hatch door according to claim 1, characterized by: the finite element model in step 2 includes: node position, triangle unit, quadrilateral unit.
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