Dymore new features

  1. To analyze the hysteresis loops generated by hydraulic and elastomeric damper, a new post-precessing object, hysteresis loop, was developed.
  2. A new elastomeric damper model has been created, which is composed of elastic, dashpot, plastic, and viscous branches.
  3. A new interface element has been created, called the force element interface, which interfaces a force element, such as a hydraulic or elastomeric damper, with a general multibody system.
  4. A new utility object has been created, the function, which defines an arbitrary function of a single variable, F = F(x), where x is the independent variable and F the value of the function. This new utility object is used to help the definition of springs and dampers.
  5. The data section air properties has been renamed fluid properties and data has been reorganized for improved clarity and support of other fluids besides air.
  6. The Leishman-Beddoes model was been updated to allow all coefficients to be functions of Mach number. A sample input file is found in runGolandWing\GolandWingLB.dym.
  7. The ONERA dynamic stall model was been updated to allow all coefficients to be functions of Mach number. A sample input file is found in runGolandWing\GolandWing3D.dym.
  8. The Morrison unsteady aerodynamic model has been added as an optional unsteady aerodynamic model. The Morrison model describes the hydrodynamic forces acting on a cable.
  9. Parameters were added to the step control parameters section to handle singular stiffness matrices. To remove the singularity, fictitious springs connected to the ground can be added automatically. When performing an eigenanalysis, application of the eigen spectrum shift factor allows the evaluation of the eigenmodes associated with zero frequencies without adding fictitious springs to avoid singularities. A sample input file is found in run\BeamKick\PinnedFreeBeam.dym.
  10. The SectionBuilder-Dymore interface is operational. The interface describes the relationship between SectionBuilder and Dymore and involves the following objects: SectionBuilder Section and SectionBuilder Recovery. The input files found in run\BenchmarkProblems\FourBar and run\BenchmarkProblems\LateralBuckling provide examples of application.
  11. The definition of beam sectional properties has been streamlined. The 6x6 stiffness matrix and data table definition options have been eliminated. Note that the 6x6 stiffness matrix definition is now available under the SectionBuilder-Dymore interface as the PropertyType = SECTION_BUILDER option in the SectionBuilder Section.
  12. The preferred manner of defining beam sectional properties is through object SectionBuilder Section, using either of the two options provided. The beam sectional properties object then simply defines the variation of the properties along the beam's span. The former manner of defining beam properties is still available.
  13. The Auto-Pilot controller has been updated. The duration of the phases is now expressed in actual time rather than number of time steps. A “release phase” was added to the trimming process to avoid abrupt changes in controls. Input file run\GolandWing\GolandWingTrim.dym provides an example of application.
  14. The mesh optimization and property smoothing of beam sectional properties has been updated and streamlined. Input file run\PropSmoothing\BeamStatic.dym provides an example of application.
  15. The compound air tables object was implemented and tested. It allows grouping together a number of airfoil tables to provide modeling capabilities for airfoils with trailing edge flaps.
  16. The unsteady aerodynamic model of Peters was documented and implemented for both rigid airfoil and airfoil with trailing edge flaps. Combination of Peters model with flap plus compound air tables needs to be validated with actual data. All apparent mass effects are now included for both rigid airfoil and airfoil with trailing edge flaps.