{"679968":{"#nid":"679968","#data":{"type":"event","title":"MS Proposal by Evan Sanchez","body":[{"value":"\u003Cp\u003EEvan Sanchez\u003Cbr\u003E(Advisor: Dr. \u00c1lvaro Romero-Calvo]\u003Cbr\u003Ewill propose a master\u2019s thesis entitled,\u003Cbr\u003EMagnetohydrodynamic Liquid Metal Cooling for Hypersonic SmallSat Reentry\u003Cbr\u003EOn\u003Cbr\u003EThursday, January 30 at 12:00 p.m.\u003Cbr\u003EEngineering Science and Mechanics Building 108\u003Cbr\u003EAbstract\u003Cbr\u003EThe rapid development of CubeSat technologies is expected to render current thermal control methods\u003Cbr\u003Eincreasingly ineffective. As more power-hungry subsystems are adopted, novel heat transport strategies\u003Cbr\u003Ewill become necessary to keep spacecraft components in their design temperature ranges. The\u003Cbr\u003Emagnetohydrodynamic (MHD) liquid metal loop was recently conceived to address this need. The device\u003Cbr\u003Einduces a Lorentz force in an electrically conductive liquid by running an electrical current through the\u003Cbr\u003Efluid in the presence of a magnetic field. By removing mechanical parts, the MHD pump can eliminate\u003Cbr\u003Efailure points and increase the robustness of the system. Liquid metals have high electrical and thermal\u003Cbr\u003Econductivity, and high volumetric specific heat. Combining these properties results in a device with dense\u003Cbr\u003Eand reliable energy transfer that is ideally suited to the SmallSat environment. In this thesis, the MHD\u003Cbr\u003Eliquid metal loop is applied to the management of thermal loads during atmospheric CubeSat reentry,\u003Cbr\u003Esupporting a platform that serves as a testbed for hypersonic research. MHD liquid metal cooling is\u003Cbr\u003Eimplemented to provide an active and reliable heat management method to reduce the thermal loads on\u003Cbr\u003Ethe drag shield. It is hypothesized that, by drawing heat away from the shield and transporting it directly\u003Cbr\u003Eto the radiator, it is possible to reduce the mass and volume of the Entry, Descent, and Landing subsystem.\u003Cbr\u003EThe heat transfer capabilities of the liquid metal loop will be validated using a prototype system to\u003Cbr\u003Econtinue the feasibility study of this approach. The Phase A design of the thermal control system will be\u003Cbr\u003Ebased on the results from numerical and experimental efforts.\u003Cbr\u003ECommittee\u003Cbr\u003E\u2022 Dr. \u00c1lvaro Romero-Calvo \u2013 School of Aerospace Engineering (advisor)\u003Cbr\u003E\u2022 Dr. Krishan Ahuja\u2013 School of Aerospace Engineering\u003Cbr\u003E\u2022 Dr. John Dec \u2013 School of Aerospace Engineering\u003C\/p\u003E","summary":"","format":"limited_html"}],"field_subtitle":"","field_summary":[{"value":"\u003Cp\u003EMagnetohydrodynamic Liquid Metal Cooling for Hypersonic SmallSat Reentry\u003C\/p\u003E","format":"limited_html"}],"field_summary_sentence":[{"value":"Magnetohydrodynamic Liquid Metal Cooling for Hypersonic SmallSat Reentry"}],"uid":"27707","created_gmt":"2025-01-24 20:40:22","changed_gmt":"2025-01-24 20:41:05","author":"Tatianna Richardson","boilerplate_text":"","field_publication":"","field_article_url":"","field_event_time":{"event_time_start":"2025-01-30T12:00:00-05:00","event_time_end":"2025-01-30T14:00:00-05:00","event_time_end_last":"2025-01-30T14:00:00-05:00","gmt_time_start":"2025-01-30 17:00:00","gmt_time_end":"2025-01-30 19:00:00","gmt_time_end_last":"2025-01-30 19:00:00","rrule":null,"timezone":"America\/New_York"},"location":"Engineering Science and Mechanics Building 108","extras":[],"groups":[{"id":"221981","name":"Graduate Studies"}],"categories":[],"keywords":[{"id":"166866","name":"MS Proposal"}],"core_research_areas":[],"news_room_topics":[],"event_categories":[{"id":"1788","name":"Other\/Miscellaneous"}],"invited_audience":[{"id":"78771","name":"Public"}],"affiliations":[],"classification":[],"areas_of_expertise":[],"news_and_recent_appearances":[],"phone":[],"contact":[],"email":[],"slides":[],"orientation":[],"userdata":""}}}