WE PROPOSE TO DEVELOP COMPUTATIONAL METHODS AND SOFTWARE IMPLEMENTATION FOR THE SIMULATION OF FLEXIBLE PARACHUTES UNDER STRONG DYNAMIC LOADING AS IT OCCURS DURING DEPLOYMENT OF SUCH DEVICES. THE RANGE OF CONDITIONS TARGETED BY THE PROPOSED WORK RANGES FROM: I. A NEARLY COLLAPSED PARACHUTE GEOMETRY UNDERGOING INITIAL INFLATION. II. THE INITIAL STRUCTURAL TRANSIENTS RESULTING FROM THE INFLATION. III. THE FULLY OPENED CONFIGURATION. THE TECHNIQUES THAT WILL BE USED ARE A LARGE DEFORMATION NON ISOTROPIC SHELL MECHANICS FOR THE MODELING OF FABRICS DETACHED AND LARGE EDDY SIMULATION FOR THE MODELING OF TURBULENCE ADAPTIVE CARTESIAN MESHING FOR THE CONTROL OF RESOLUTION REQUIREMENTS AT SCALES SMALLER AND COMPARABLE TO THE PARACHUTE SIZE AND FINALLY A NOVEL CURVILINEAR ANALYTICALLY BASED CONFORMING GRID TO COMMUNICATE ACCURATELY STRUCTURAL AND FLUID MECHANICAL INFORMATION. THIS LATTER ELEMENT IS A NOVELTY OF CRITICAL IMPORTANCE FOR THE TYPE OF SIMULATIONS BEING CONSIDERED SINCE IT REDUCES DRAMATICALLY THE GEOMETRICAL COMPUTATIONAL COSTS ASSOCIATED WITH HANDLING A FINE GRID NEAR AND AROUND THE DEFORMING PARACHUTE AND VITAL FOR ACCURATE PREDICTIONS OF FORCES AND HEAT TRANSFER. THE UNDERLYING FRAMEWORK OF THIS SEMI ANALYTICAL GRID METHODOLOGY IS ROOTED IN MANIFOLD THEORY AND USING OVERLAPPING CHARTS AND THE PARTITION OF UNITY DECOMPOSITION. THE ALGORITHMS WILL BE IMPLEMENTED USING THE STANDARD MPI LIBRARY FOR MODERN SUPERCOMPUTERS.