3. Overview of MSC/NASTRAN

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1 3. Overview of MSC/NASTRAN MSC/NASTRAN is a general purpose finite element analysis program used in the field of static, dynamic, nonlinear, thermal, and optimization and is a FORTRAN program containing over one million lines of code. MSC/NASTRAN is consisted of bunch of building block called module and a module is a collection of subroutines designed to perform specific task processing model geometry, assembling matrix, applying boundary conditions, solving matrix, calculating output quantities, printing, and so on. The modules are controlled by DMAP program called the Direct Matrix Abstraction. Each type of analysis is consisted of a collection of hundreds or thousands of DMAP commands. Once a type of analysis is chosen, its DMAP command sends instruction to the modules that are needed to perform the requested solution. MSC/ NASTRAN can quickly solve a large size of problem with small amount of disk space by using the Sparse Matrix Algorithms. Solution Flow Chart Formulate element stiffness matrices from element properties, material properties, and geometry Assemble all element stiffness matrices into a global stiffness matrix Apply boundary conditions to constrain model Apply loads to the model (forces, moments, pressure, etc) Calculate displacements of nodes Calculate stresses from the displacements < Types of solutions of MSC/NASTRAN > SOL 101 : Statics 103 : Normal Modes 105: Buckling 106: Nonlinear Statics 107 : Direct Complex Eigenvalues 108 : Direct Frequency Response 109 : Direct Transient Response 110 : Modal Complex Eigenvalue 111 : Modal Frequency Response 112 : Modal Transient Response 114 : Cyclic Statics with Option 115 : Cyclic Normal Modes 116 : Cyclic Direct Frequency Response 129 : Nonlinear Transient Response 144 : Static Aeroelastic Response 145 : Aerodynamic Fluter 146 : Aerostatic Response 153 : Steady Nonlinear Heat Transfer 159 : Transient Heat Transfer 200 : Design Optimization 3.1 The structure of the MSC/NASTRAN Input File MSC/NASTRAN Input file contains four distinct sections. File Management Section (FMS) The File Management Section is not used in general solution sequences and is optional. If the problem is large, this section is used to initialize the maximum size of database, member names, and location of file. Also this is used to perform a restart run. Example) RESTART ASSIGN,MASTER=aaa.MASTER Executive Control Section (ECS) 15

2 This section specifies the type of analysis solution to be performed. Example) SOL 101 <=== Linear Static Type CEND Case Control Section (CCS) The Case Control Sections defines the analysis condition with a subcase containing identification number (ID) of boundary and load conditions specified in the Bulk Data Section (BDS) for the analysis model and the type of outputs required. Example) SUBCASE 1 <=== the first analysis condition SPC = 10 <-----define the constraint identified as 10 in BDS LOAD = 10 <-----define the load identified as 10 in BDS DISP= ALL <-----print the displacements of all nodes STRESS = ALL <-----print stresses of all elements SUBCASE 2 <===the second analysis condition SPC = 10 <-----define the constraint identified as 10 in BDS LOAD= 20 <-----define the load identified as 20 in BDS DISP= ALL <-----print the displacements of all nodes STRESS = ALL <-----print stresses of all elements Bulk Data Section (BDS) The Bulk Data Section is mainly generated by the pre-processor and defines everything required to describe the finite element model as nodes and elements grid data, element data, several boundary conditions, load conditions, and parameters required. Example) SOL 101 CEND SPC=10 LOAD=20 DISP=ALL BEGIN BULK GRID,1,,0.,0.,0. ======> define the solution sequence ======> describe the end of ECS ======> define the constraint ======> define the load condition ======> define printing displacements ======> input geometry, loads, and the constraints ======> define nodes GRID,2,,5.,0.,0. GRID,3,,10.,0.,0. GRID,4,,0.,5.,0. GRID,5,,5.,5.,0. GRID,6,,10.,5.,0. 16

3 GRID,7,,0.,10.,0. GRID,8,,5.,10.,0. GRID,9,,10.,10.,0. CQUAD4,1,10,1,2,5,4 ======> define elements CQUAD4,2,10,2,3,6,5 CQUAD4,3,10,4,5,8,7 CQUAD4,4,10,5,6,9,8 PSHELL,10,30,0.25,30 ======> define element properties (thickness : 0.25) MAT1,30,3.E7,,0.33 ======> define material properties FORCE,20,5,,-1000.,0.,0.,1. ======> define loads SPC1,10,123456,1,2,3,4,6,7,+AA1 ====> define the constraints +AA1,8,9 ENDDATA ======> the end of input file 17

4 3.2 Files Created by MSC/NASTRAN MSC/NASTRAN files that analyst should basically manage are input files which are.dat and.bdf, and the result files which are.f06 printed out as text and.op2 for post-processing. Generally, the files related to MSC/NASTRAN are the fillowing. (Jobname is test1.) TEST1.dat : Input file for MSC/NASTRAN (Mainly generated by Pre-Processor) When using MSC/PATRAN, the extension is.bdf. TEST1.f06 : File containing the results of MSC/NASTRAN (can be opened with editor because this is ASCII file) TEST1.op2 : MSC/NASTRAN result files for interfacing with the post-processor designated by analyst (Verify the results graphically by post-processor) TEST1.f04 : File containing information files used, disk space, modules used, etc. This file is useful in debugging. TEST1.log : File containing information system environment for executing MSC/NASTRAN and file link. TEST1.pch : Punch file of MSC/NASTRAN analysis results (Optional) TEST1.MASTER : As the file for restart run, this contains information about the master directory of files used in execution of program and physical location of files. TEST1.DBALL : Database containing input file, assembled matrices, and solutions. 3.3 Units Error detected frequently in the finite element analysis is due to units and boundary conditions. MSC/NASTRAN does not use the specific units system. To avoid the error, consistent units system should be used. Example) E : 2.1e11 N/m 2 Poisson ratio : kgf = 9.8N = 9.8 Kg -m/ sec 2 18

5 Density : 7800 Kg/m 3 1 Kg = (1/9.8) kgf- sec 2 / m G : 9.8 m/sec 2 Length : 1m * 1m * 0.01m Volume : 0.01 m 3 Mass : 7800 * 0.01 = 78 kg Weight : 78 kg * 9.8 m/sec 2 = 764 kg m/sec 2 = 764 N The summary of analysis conditions and the results is the folloeing. S I Units ( N-M ) Engineering Units ( Kgf - M ) Weight 764 N 1 Kgf = 9.8 N (764/9.8)= Kgf Volume 0.01 m m 3 Density 7800 Kg/m 3 1Kg=(1/9.8) kgf-sec 2 /m kgf- sec 2 /m 4 Mass 78 kg W/g kgf -sec 2 /m g 9.8 m/sec m/sec 2 E 2.1E+11 N/m E+11 kgf/m 2 Poisson s Ratio Mass for results 78 kg kgf/m 2 Displacement E-5 m E-5 m Stress E7 N/m E+6 kgf/m 2 Nature Frequency Hz Hz ** If density in engineering units system, 7800 Kg/m 3, is used, g should be 1.0 m/sec 2. (But, not applicable to the dynamic analysis) In case that M, the length of an analysis model, is converted into mm, material properties and the results are the following; When units of force is N, this is a general case that N is used, regardless of that length is M or mm. At this time be careful that density should not be used to 7800 E-9 Kg/mm 3 instead of 7800 Kg/m 3. In SI units system; Kg is equal to N- sec 2 /m. Change 7800 Kg/m 3 to 7800 N- sec 2 / m 4 and convert. 19

6 As it were, 7800 Kg/m 3 = 7800 E-12 N- sec 2 /mm 4 S I Units (N-MM) Engineering Units (Kgf-MM) Weight 764 N 1 Kgf = 9.8 N (764/9.8)= Kgf Volume 1 E+7 mm 3 1 E+7 mm 3 Density 7.8E-9 N-sec 2 /mm 4 1Kg (1/9.8) kgf-sec 2 /m E-10 kgf-sec 2 /mm 4 Mass 7.8 E-2 N-sec 2 /mm W/g 7.955E-3 kgf-sec 2 /mm g 9800 mm/sec mm/sec 2 E 2.1E5 N/mm E+4 kgf/mm 2 Poisson ratio Mass for results 7.8 E-2 N-sec 2 /m 7.955E-3 kgf-sec 2 /mm Displacement E-2 mm -7.09E-2 mm Stress E1 N/mm kgf/mm 2 Natural Frequency Hz Hz ** When using engineering units system, density is 7.8E-9 N-sec 2 /mm 4 and g is 1000 mm/sec 2. In SI units system density is 7800 E-9 Kg/mm 3 and g is 9.8 mm/sec 2. (But, not applicable to the dynamic analysis) 3.3 Considerations of the Structure Analysis 1) The purpose of the analysis and the accuracy of the analysis Before constructing a Model engineering judgement about the behavior of the structure is required. The accuracy of the analysis results depends on experience and judgement, and also modeling method. Increasing the number of elements improves accuracy, but increases calculating time. A fine mesh is required in regions where high stress gradients are expected and where high accuracy is required. 2) Understand the nature of the problem MSC/NASTRAN will only solve a problem about given conditions. So to speak, in linear static analysis, if analyst compress a long, slender column indefinitely, the result is a short, highly stressed column. In practical case, Buckling can be occurred under a small compressive load. Buckling analysis should be performed by a solution sequence of buckling. 3) Material Property MSC/NASTRAN gives a functionality to generate several material properties - isotropic, anisotropic, orthotropic, nonlinear (stress-dependent), fluid, temperature-dependence, composite behavior, and so on. 20

7 * Linear : Deformations are directly proportional to the applied load. As it were, strain is directly proportional to stress. * Elastic : When the applied load is removed, an elastic structure returns to its original, undeformed shape. * Homogeneous : The material is the same nature, regardless of location within the material. * Isotropic : Material properties do not change with the direction of the material. * Modulus of Elasticity (E) : In the linear region E corresponds to the constant slope of the stressstrain curve. The greater the value of E, the stiffer the material. * Shear Modulus (G) : G corresponds to the constant slope of the shear stress-shear strain curve in the linear region. * Poisson s Ratio : The ratio of lateral linear strain to axial linear strain. If the loading on a structure is sufficient to exceed the linear elastic limit of the material, nonlinear analysis is required to predict the nature of the plastically deformed state. MAT1 : Homogeneous, Isotropic MAT2 : Anisotropic material for two-dimensional elements, plates or shells. In-plane, transverse shear material MAT3 : Material for axisymmetric three-dimensional elements (Axisymmetric solid orthotropic Material) MAT8 : Orthotropic material for two-dimensional elements, plate or shell. (Including transverse shear material) MAT9 : Anisotropic material for three-dimensional solid elements. PCOMP : Define the property per layer. (ease of use for two-dimensional composite problems) Anisotropic material matrix is required in case of three-dimensional composite problems. 4) Loads and boundary conditions < Load Conditions > MSC/NASTRAN can describe various types of loads static load, dynamic load, repeated load, thermal load, earthquake acceleration, random load, and so on. Static Loads : Concentrated Loads, Moments, Distributed loads on Bar or Beam, Surface Pressure on Plate or Shell, Gravity, Acceleration Loads, Enforced Displacement, etc. There are lucky cases that analyst can directly use the load when its type is clear. But, there are cases that analyst assumes or calculates the character of the load. Especially, contact problems or wind load as external forces are examples of that kind of load. In this case analyst should be careful of the accuracy when describing the load. < Boundary Conditions > The structure reacts on the external forces by the constrained sections. Types of constraints : Fixed, Hinged, and Elastic. In reality, there are many cases that boundary condition is not simple. Because the selection of boundary conditions greatly affects on the reaction of a structure, the boundary conditions should be clearly applied to the structure. 5) Understanding the behavior of a structure 21

8 Analyst should consider the function of the structure under load. Choose types of elements based on the expected behavior of the structure by considering bending, torsion, shear, and axial loads. 6) Using test models One of the most useful and timesaving methods in finite element analysis is to check the relation among the number of elements, analysis accuracy, and modeling cost by the use of small test models. When analyzing the model involving new or unfamiliar element or type of solution, small test models are helpful. Also, this method is useful that it is difficult to predict the general behavior or critical regions of the structure. The results of the test model gives information about selecting elements and determining where refined mesh regions should be located in the model. 7) Reviewing the results Analyst is responsible for verifying the correctness of the model, loads, and boundary conditions. * Check for Error Message, Epsilon, and displacements Whatever there are no fatal error messages in the.06 file, this is no guarantee of accuracy of analysis itself. If the value of epsilon used is greater than 10-6, then judgement is that there are some problems. (Check stability) By checking the displacement values, verify that they are physically suitable or that a geometric nonlinear analysis is not required. For example, if the displacement is obtained to several inches, this indicates that a nonlinear analysis is required or that a cross sectional property or an elastic modulus has been incorrectly specified. * Check Reaction Forces Check static equilibrium between the applied load and the reaction forces. * Draw the shear diagram or the moment diagram. * Check displacement and stress results Check that the direction of the displacement is the expected direction or verify stress values at the start and end point of adjacent element in Beam element. * Comparing the results with theory Bending Deflection, Shear Deflection, Bending Stresses, etc. 22

9 3.5 Linear Static Analysis A general governing equation used in the structural analysis is the following. [ M ]{ u(t) } + [ B ]{ u(t) } + [ K ]{ u(t) } = { P(t) } The above equation is a general motion equation that inertia and damping forces can be considered, that includes nonlinearity, and that load can be changed according to time. But, in linear static analysis, because the load does not change according to time and is constant, the equation can be written to the simple equation that neglects inertia forces, damping forces, and nonlinearity. [ K ]{ u } = { P } where [ K ] : stiffness matrix { u } : node displacement vector { P } : load vector < Assumptions of Linear static Analysis > 1. Linear Elastic Material Material is assumed to be homogeneous and isotropic. Material is assumed to be a continuum without having gap or void and to maintain constant. Stress is directly proportional to strain and load does not exceed the yield point of the material (the material remains elastic). Analyst assumes that the unloaded structure is free of initial or residual stress. Fortunately, this restrictions are satisfied in wide range of engineering problems. 2. Small Displacements Small displacement assumption is used in the formulation of governing equations for linear beam, plate, shell, and solid behavior. This assumption means that deflections are bounded on 20% of the thickness of the plate and on 2% of the length of small span. Large displacements require nonlinear analysis methods. 3. Slowly Applied Load In linear static analysis the structure is in static equilibrium. Loads must be slowly applied so that they induce no dynamic effects. Each elements in linear static analysis is substituted with spring elements which can approximate the physical behavior of small parts in a real structure to a mathematical behavior. The final goal is that analyst build a collections of discrete elements, which has the same behavior as a real structure. Therefore, analyst should understand the nature of the structure and select appropriately the type and the number of elements. 23

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