A computer program to perform flow and thermal analysis during pressurization of the Space Shuttle Solid Rocket Motor field jointA computational technique for prediction of the flow and thermal environment in the SRM field joint cavities is described. The SRM field joint hardware was tested with a defect in the insulation, and due to this defect, the O-ring gland cavities are pressurized during the early part of the ignition. A computer model is developed to predict the thermal environment and flow through the simulated flaw, during the pressurization of the field joint. The transient mass, momentum, and energy conservation equations in the flow passage together with the thermodynamic equation of state are solved by a fully implicit iterative numerical procedure.
Document ID
19910068953
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Clayton, J. Louie (NASA Marshall Space Flight Center Huntsville, AL, United States)
Colbert, R. F. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Ghaffarian, B. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Majumdar, Alok (Sverdrup Technology, Inc. Huntsville, AL, United States)