Numerical Evaluation Of A Novel Transpiration Cooling Scheme For Use In Dynamic Control Of Atmospheric Entry System

Future space exploration missions require sustainable, efficient thermal protection systems for atmospheric entry, instead of disposable ablative shields. Transpiration cooling has interest as a long studied method but never used for missions to date, prompting further study to address concerns of flow transition downstream. In consideration of additional need for aerodynamic maneuvering for greater landing accuracy, a novel asymmetric scheme of transpiration cooling is presented as a method of using onboard coolant to meet entry trajectory maneuvering requirements. This numerical study creates a coupled model of vehicle-scale flow domain and material-scale thermal response to converge on accurate vehicle surface values.