Abstract
A one-dimensional numerical technique is presented herein for determining the surface temperature boundary condition from an in-depth temperature history that is obtained from a single thermocouple in the Space Shuttle orbiter's thermal protection system (TPS). An iterative solution technique is given for solving this inverse heat conduction problem with a multi-material system that has been modeled with unequally spaced nodes. Results are presented for both a test case and an actual flight case (the second flight of the Space Shuttle). Heat flux, backed out from thermocouple temperature, is shown to match angle-of-attack maneuver phasing for an effective thermocouple displacement below the surface. Backed-out heat flux for an effective thermocouple depth is also shown to provide an acceptablc match with surface calorimeter data.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
