Project Title:
Conjugate Heat-Transfer Analysis for Solid Rocket Motors
11.02-2008
910812
Conjugate Heat-Transfer Analysis for Solid Rocket Motors
Seca, Inc.
3311 Bob Wallace Avenue, Suite 203
Huntsville
AL
35805
Jon A.
Freeman
205-534-2008
MSFC
NAS8-39338
220
11.02-2008
910812
Abstract:
Conjugate Heat-Transfer Analysis for Solid Rocket Motors
Complex heat-transfer processes occur in a solid rocket motor between the particle-laden
exhaust gases, ablative nozzle inserts and liners, case insulation, and metallic
walls of the motor. These are critical to the thermal design, the base heating and
signature of the motor and the launch-stand heating caused by the motor. A computational
fluid dynamics analysis of these conjugate heat-transfer processes will be developed
as a thermal design tool for solid rocket motors. The high particle loading of the
exhaust gases and the ablative behavior of the thermal protection system require
major material evaluations and new code development. This design tool constitutes
an analytical technique for thermal design of solid-rocket-motor nozzles, including
the critical throat region, and all insulation materials. If the motor cases and
insulation are made of advanced composite materials, the analysis will indicate the
critical thermal properties that must be experimentally determined to effect a valid
thermal design.
Applications would be within NASA, DOD, and/or their prime contractors for use in
analyzing advanced and solid propellant motors.
thermal analysis, ablator response to multi-phase flows