{"id":{"repo_id":"maryland","oai_identifier":"oai:drum.lib.umd.edu:1903/3766"},"canonical_url":"https://search.dev.ndltd.org/etd/maryland/oai:drum.lib.umd.edu:1903/3766","repository":{"repo_id":"maryland","name":"University of Maryland","base_url":"https://api.drum.lib.umd.edu/server/oai/request"},"display":{"title":"MULTIDISCIPLINARY OPTIMIZATION OF NON-SPHERICAL, BLUNT-BODY HEAT SHIELDS FOR A PLANETARY ENTRY VEHICLE","abstract":"Gradient-based optimization of the aerodynamic performance, static stability, and stagnation-point heat transfer has been completed to find optimal heat shield geometries for blunt-body planetary entry vehicles. In the parametric study, performance trends have been identified by varying geometric parameters that define a range of cross-sections and axial shapes. Cross-sections considered include oblate and prolate ellipses, rounded-edge polygons, and rounded-edge concave polygons. Axial shapes consist of the spherical-segment, spherically-blunted cone, and power law. By varying angle-of-attack and geometric parameters, the aerodynamics, static stability, and heat transfer are optimized based on Newtonian impact theory with semi-empirical shock-standoff distance and stagnation-point heat transfer correlations. Methods have been verified against wind tunnel and flight data of the Apollo Command Module and are within 15% for aerodynamic coefficients and stagnation-point heat fluxes. Results indicate that oblate parallelogram configurations provide optimal sets of aerothermodynamic characteristics.","abstract_html":"Gradient-based optimization of the aerodynamic performance, static stability, and stagnation-point heat transfer has been completed to find optimal heat shield geometries for blunt-body planetary entry vehicles. In the parametric study, performance trends have been identified by varying geometric parameters that define a range of cross-sections and axial shapes. Cross-sections considered include oblate and prolate ellipses, rounded-edge polygons, and rounded-edge concave polygons. Axial shapes consist of the spherical-segment, spherically-blunted cone, and power law. By varying angle-of-attack and geometric parameters, the aerodynamics, static stability, and heat transfer are optimized based on Newtonian impact theory with semi-empirical shock-standoff distance and stagnation-point heat transfer correlations. Methods have been verified against wind tunnel and flight data of the Apollo Command Module and are within 15% for aerodynamic coefficients and stagnation-point heat fluxes. Results indicate that oblate parallelogram configurations provide optimal sets of aerothermodynamic characteristics.","abstract_has_math":false,"creators":["Johnson, Joshua Elijah"],"institution":null,"degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Aerospace Engineering","school":null,"contributors":[],"advisors":["Lewis, Mark J"],"committee_chairs":[],"committee_members":[],"year":2006,"date_issued":"2006-07-03","date_published":"2006-07-03","updated_at":"2026-07-24T03:02:29Z","subjects":[],"languages":["en_US"],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/1903/3766","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Lewis, Mark J"]},{"key":"dc:contributor.department","label":"Department","values":["Aerospace Engineering"]},{"key":"dc:creator","label":"Author","values":["Johnson, Joshua Elijah"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2006-09-12T05:42:23Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2006-09-12T05:42:23Z"]},{"key":"dc:date.issued","label":"Date","values":["2006-07-03"]},{"key":"dc:type","label":"Dc Type","values":["Thesis"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language.iso","label":"Language (ISO)","values":["en_US"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier.uri","label":"Identifier URI","values":["http://hdl.handle.net/1903/3766"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["Gradient-based optimization of the aerodynamic performance, static stability, and stagnation-point heat transfer has been completed to find optimal heat shield geometries for blunt-body planetary entry vehicles. In the parametric study, performance trends have been identified by varying geometric parameters that define a range of cross-sections and axial shapes. Cross-sections considered include oblate and prolate ellipses, rounded-edge polygons, and rounded-edge concave polygons. Axial shapes consist of the spherical-segment, spherically-blunted cone, and power law. By varying angle-of-attack and geometric parameters, the aerodynamics, static stability, and heat transfer are optimized based on Newtonian impact theory with semi-empirical shock-standoff distance and stagnation-point heat transfer correlations. Methods have been verified against wind tunnel and flight data of the Apollo Command Module and are within 15% for aerodynamic coefficients and stagnation-point heat fluxes. Results indicate that oblate parallelogram configurations provide optimal sets of aerothermodynamic characteristics."]},{"key":"dc:format.mimetype","label":"Dc Format Mimetype","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["MULTIDISCIPLINARY OPTIMIZATION OF NON-SPHERICAL, BLUNT-BODY HEAT SHIELDS FOR A PLANETARY ENTRY VEHICLE"]}]}],"canonical_facts":{"dc:contributor.advisor":["Lewis, Mark J"],"dc:contributor.department":["Aerospace Engineering"],"dc:creator":["Johnson, Joshua Elijah"],"dc:date.accessioned":["2006-09-12T05:42:23Z"],"dc:date.available":["2006-09-12T05:42:23Z"],"dc:date.issued":["2006-07-03"],"dc:description.abstract":["Gradient-based optimization of the aerodynamic performance, static stability, and stagnation-point heat transfer has been completed to find optimal heat shield geometries for blunt-body planetary entry vehicles. In the parametric study, performance trends have been identified by varying geometric parameters that define a range of cross-sections and axial shapes. Cross-sections considered include oblate and prolate ellipses, rounded-edge polygons, and rounded-edge concave polygons. Axial shapes consist of the spherical-segment, spherically-blunted cone, and power law. By varying angle-of-attack and geometric parameters, the aerodynamics, static stability, and heat transfer are optimized based on Newtonian impact theory with semi-empirical shock-standoff distance and stagnation-point heat transfer correlations. Methods have been verified against wind tunnel and flight data of the Apollo Command Module and are within 15% for aerodynamic coefficients and stagnation-point heat fluxes. Results indicate that oblate parallelogram configurations provide optimal sets of aerothermodynamic characteristics."],"dc:format.mimetype":["application/pdf"],"dc:identifier.uri":["http://hdl.handle.net/1903/3766"],"dc:language.iso":["en_US"],"dc:title":["MULTIDISCIPLINARY OPTIMIZATION OF NON-SPHERICAL, BLUNT-BODY HEAT SHIELDS FOR A PLANETARY ENTRY VEHICLE"],"dc:type":["Thesis"]},"updated_at":"2026-07-24T03:02:29Z"}