INTRAVITREAL FLUOCINOLONE IMPLANT MACULAR DEGENERATION

Not Available While major advances have been made in complex missile component thermal and thermo-structural analysis software and desktop computing, technological advances in the generation of convective heating and pressure boundary conditions have not kept pace. The objective of this effort is to develop an efficient and easy-to-use analysis tool for generating and applying these boundary conditions. To this end, our existing software will be modified and upgraded and an interface tool developed so it can be readily used to generate and transfer boundary conditions for finite element analyses of external missile structures. The Maneuvering Aerotherm Shape Change Code (MASCC) computer code can currently model all of the phenomena of interest relative to external missile heating in supersonic and hypersonic flight regimes. Much of the missile geometry inputs that are currently done by hand will be automated under this program. The development of a Graphical User Interface, which steps the user through development of a geometry model and input of environments, is a significant part of this program. A single, standard graphical desktop tool set for all UNIX based platforms will be developed. BENEFITS: The automated analysis tool developed in this program will provide the thermal analyst an easy to use technique for generating and applying boundary conditions to external missile surfaces. The capabilities provided by the MASCC code will provide the analyst the ability to mode1 all i