Keywords

transpiration cooling, CFD, entry vehicles, material response

Abstract

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.

Completion Date

2025

Semester

Summer

Committee Chair

Michael Kinzel

Degree

Doctor of Philosophy (Ph.D.)

College

College of Engineering and Computer Science

Department

Mechanical and Aerospace Engineering

Format

PDF

Identifier

DP0029512

Language

English

Document Type

Thesis

Campus Location

Orlando (Main) Campus

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