FEA Analysis

Structure for the analysis tuple = (‘Analysis Name’, ‘Value’). 'Analysis Name' defines the reference name for the analysis being specified. The "Value" can either be a JSON String dictionary (see Section JSON String Dictionary) or a single string keyword (see Section Single Value String).

JSON String Dictionary

If "Value" is JSON string dictionary (e.g. "Value" = {"numDesiredEigenvalue": 10, "eigenNormalization": "MASS", "numEstEigenvalue": 1, "extractionMethod": "GIV", "frequencyRange": [0, 10000]}) the following keywords ( = default values) may be used:

• analysisType = "Modal"
  Type of load. Options: "Modal", "Static", "AeroelasticTrim", "AeroelasticFlutter" Note: "AeroelasticStatic" is still supported but refers to "AeroelasticTrim" Note: "Optimization" and "StaticOpt" are not valid - Optimization is initialized by the Analysis_Type AIM Input

• analysisLoad = "(no default)"
  Single or list of "Load Name"s defined in FEA Load in which to use for the analysis (e.g. "Name1" or ["Name1","Name2",...].

• analysisConstraint = "(no default)"
  Single or list of "Constraint Name"s defined in FEA Constraint in which to use for the analysis (e.g. "Name1" or ["Name1","Name2",...].

• analysisSupport = "(no default)"
  Single or list of "Support Name"s defined in FEA Support in which to use for the analysis (e.g. "Name1" or ["Name1","Name2",...].

• analysisDesignConstraint = "(no default)"
  Single or list of "Design Constraint Name"s defined in FEA Design Constraints in which to use for the analysis (e.g. "Name1" or ["Name1","Name2",...].

• extractionMethod = "(no default)"
  Extraction method for modal analysis.

• frequencyRange = [0.0, 0.0]
  Frequency range of interest for modal analysis.
  Note: specifying inf (math.inf or np.inf in Python) results in a blank entry in the input card

• numEstEigenvalue = 0
  Number of estimated eigenvalues for modal analysis.

• numDesiredEigenvalue = 0
  Number of desired eigenvalues for modal analysis.
  A value <= 0 will result in a blank card entry

• eigenNormalization = "(no default)"
  Method of eigenvector renormalization. Options: "POINT", "MAX", "MASS"

• gridNormalization = 0
  Grid point to be used in normalizing eigenvector to 1.0 when using eigenNormalization = "POINT"

• componentNormalization = 0
  Degree of freedom about "gridNormalization" to be used in normalizing eigenvector to 1.0 when using eigenNormalization = "POINT"

• machNumber = 0.0 or [0.0, ..., 0.0]
  Mach number used in trim analysis OR Mach up to 6 values used in flutter analysis..

• dynamicPressure = 0.0
  Dynamic pressure used in trim analysis.

• density = 0.0
  Density used in trim analysis to determine true velocity, or flutter analysis.

• aeroSymmetryXY = "(no default)"
  Aerodynamic symmetry about the XY Plane. Options: SYM, ANTISYM, ASYM. Aerodynamic symmetry about the XY Plane. Options: SYM, ANTISYM, ASYM. SYMMETRIC Indicates that a half span aerodynamic model is moving in a symmetric manner with respect to the XY plane. ANTISYMMETRIC Indicates that a half span aerodynamic model is moving in an antisymmetric manner with respect to the XY plane. ASYMMETRIC Indicates that a full aerodynamic model is provided.

• aeroSymmetryXZ = "(no default)"
  Aerodynamic symmetry about the XZ Plane. Options: SYM, ANTISYM, ASYM. SYMMETRIC Indicates that a half span aerodynamic model is moving in a symmetric manner with respect to the XZ plane. ANTISYMMETRIC Indicates that a half span aerodynamic model is moving in an antisymmetric manner with respect to the XZ plane. ASYMMETRIC Indicates that a full aerodynamic model is provided.

• rigidVariable = ["no default"]
  List of rigid body motions to be used as trim variables during a trim analysis. Nastran format labels are used and will be converted by the AIM automatically. Expected inputs: ANGLEA, SIDES, ROLL, PITCH, YAW, URDD1, URDD2, URDD3, URDD4, URDD5, URDD6

• rigidConstraint = ["no default"]
  List of rigid body motions to be used as trim constraint variables during a trim analysis. Nastran format labels are used and will be converted by the AIM automatically. Expected inputs: ANGLEA, SIDES, ROLL, PITCH, YAW, URDD1, URDD2, URDD3, URDD4, URDD5, URDD6

• magRigidConstraint = [0.0 , 0.0, ...]
  List of magnitudes of trim constraint variables. If none and 'rigidConstraint'(s) are specified then 0.0 is assumed for each rigid constraint.

• controlConstraint = ["no default"]
  List of controls surfaces to be used as trim constraint variables during a trim analysis.

• magControlConstraint = [0.0 , 0.0, ...]
  List of magnitudes of trim control surface constraint variables. If none and 'controlConstraint'(s) are specified then 0.0 is assumed for each control surface constraint.

• reducedFreq = [0.1, ..., 20.0], No Default Values are defined.
  Reduced Frequencies to be used in Flutter Analysis. Up to 8 values can be defined.

• flutterVel = [0.1, ..., 20.0]
  Velocities to be used in Flutter Analysis. If no values are provided the following relation is used

  v = sqrt(2*dynamicPressure/density) dv = (v*2 - v/2) / 20;

  flutterVel[0] = v/10 flutterVel[i] = v/2 + i*dv; where i = 1....21 flutterVel[22] = v*10;

• flutterConvergenceParam = 1e-5
  Convergence parameter for flutter eigenvalue.

• visualFlutter = False
  Turn on flutter visualization f06 output.

Single Value String

If "Value" is a string, the string value may correspond to an entry in a predefined analysis lookup table. NOT YET IMPLEMENTED!!!!