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Characterization of Space Shuttle Ascent Debris Aerodynamics Using CFD MethodsAn 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.
Document ID
20060051761
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Murman, Scott M. (Eloret Corp. Moffett Field, CA, United States)
Aftosmis, Michael J. (NASA Ames Research Center Moffett Field, CA, United States)
Rogers, Stuart E. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2005
Subject Category
Space Transportation And Safety
Report/Patent Number
AIAA Paper 2005-1223
Meeting Information
Meeting: 43rd AIAA Aerospace Sciences Meeting
Location: Reno, NV
Country: United States
Start Date: January 10, 2005
End Date: January 13, 2005
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
OTHER: 704-40-21
CONTRACT_GRANT: NAS2-00062
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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