An automated Computational Fluid Dynamics process for determining the aerodynamic Characteristics of debris shedding from the Space Shuttle Launch Vehicle during ascent is presented. This process uses Cartesian fully-coupled, six-degree-of-freedom simulations of isolated debris pieces in a Monte Carlo fashion to produce models for the drag and crossrange behavior over a range of debris shapes and shedding scenarios. A validation of the Cartesian methods against ballistic range data for insulating foam debris shapes at flight conditions, as well as validation of the resulting models, are both contained. These models are integrated with the existing shuttle debris transport analysis software to provide an accurate and efficient engineering tool for analyzing debris sources and their potential for damage.
Characterization of Space Shuttle Ascent Debris Aerodynamics Using CFD Methods
2005
20 pages
Report
No indication
English
Extraterrestrial Exploration , Aerodynamics , Meetings , Aerodynamic characteristics , Ascent , Computational fluid dynamics , Debris , Spacecraft launching , Space shuttles , Ballistic ranges , Monte carlo method , Degrees of freedom , Flight conditions , Insulation , Foams , Accident investigation , Displacement , Mach number , Columbia(Orbiter)
Characterization of Space Shuttle Ascent Debris Aerodynamics Using CFD Methods
British Library Conference Proceedings | 2005
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