This thesis derives analytical methods for sizing the propulsive battery packs for designing an electric-driven aircraft. Lithium-Ion (Li-Ion) battery is the primary choice of battery cell chemistry in this thesis research due to its superior specific energy and market availability. The characteristics of Lithium-Ion battery cells are first determined and studied using experimental test results and manufacturers published data. Based on the design requirement to the battery system, the battery sizing will fall into one of the two sizing categories. The first category is power sizing, which requires the battery’s ability to deliver full power demanded by the electric motor. The second category is endurance sizing, which requires the battery system to store sufficient energy for the required endurance. Both types of sizing are analytically derived. From the sizing result, capacity is used to determine the parallel connected battery cells. The required system voltage governs the series connected cells. A battery discharging simulation model is built to validate the sizing results.
","abstract_html":"<p>This thesis derives analytical methods for sizing the propulsive battery packs for designing an electric-driven aircraft. Lithium-Ion (Li-Ion) battery is the primary choice of battery cell chemistry in this thesis research due to its superior specific energy and market availability. The characteristics of Lithium-Ion battery cells are first determined and studied using experimental test results and manufacturers published data. Based on the design requirement to the battery system, the battery sizing will fall into one of the two sizing categories. The first category is power sizing, which requires the battery’s ability to deliver full power demanded by the electric motor. The second category is endurance sizing, which requires the battery system to store sufficient energy for the required endurance. Both types of sizing are analytically derived. From the sizing result, capacity is used to determine the parallel connected battery cells. The required system voltage governs the series connected cells. A battery discharging simulation model is built to validate the sizing results.</p>","abstract_has_math":false,"creators":["Zhao, Tianyuan"],"institution":null,"degree_name":"Master of Science in Aerospace Engineering","degree_level":"Thesis - Open Access","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":[],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2018,"date_issued":"2018-05-01T07:00:00Z","date_published":"2018-05-01T07:00:00Z","updated_at":"2026-07-27T19:26:34Z","subjects":["propulsive","battery packs","aviation","Aerospace Engineering","Propulsion and Power"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/edt/393","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:creator","label":"Author","values":["Zhao, Tianyuan"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis - Open Access"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science in Aerospace Engineering"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["propulsive","battery packs","aviation","Aerospace Engineering","Propulsion and Power"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/edt/393"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["This thesis derives analytical methods for sizing the propulsive battery packs for designing an electric-driven aircraft. Lithium-Ion (Li-Ion) battery is the primary choice of battery cell chemistry in this thesis research due to its superior specific energy and market availability. The characteristics of Lithium-Ion battery cells are first determined and studied using experimental test results and manufacturers published data. Based on the design requirement to the battery system, the battery sizing will fall into one of the two sizing categories. The first category is power sizing, which requires the battery’s ability to deliver full power demanded by the electric motor. The second category is endurance sizing, which requires the battery system to store sufficient energy for the required endurance. Both types of sizing are analytically derived. From the sizing result, capacity is used to determine the parallel connected battery cells. The required system voltage governs the series connected cells. A battery discharging simulation model is built to validate the sizing results.
"]},{"key":"dc:title","label":"Title","values":["Propulsive Battery Packs Sizing for Aviation Applications"]}]}],"canonical_facts":{"dc:creator":["Zhao, Tianyuan"],"dc:description.abstract":["This thesis derives analytical methods for sizing the propulsive battery packs for designing an electric-driven aircraft. Lithium-Ion (Li-Ion) battery is the primary choice of battery cell chemistry in this thesis research due to its superior specific energy and market availability. The characteristics of Lithium-Ion battery cells are first determined and studied using experimental test results and manufacturers published data. Based on the design requirement to the battery system, the battery sizing will fall into one of the two sizing categories. The first category is power sizing, which requires the battery’s ability to deliver full power demanded by the electric motor. The second category is endurance sizing, which requires the battery system to store sufficient energy for the required endurance. Both types of sizing are analytically derived. From the sizing result, capacity is used to determine the parallel connected battery cells. The required system voltage governs the series connected cells. A battery discharging simulation model is built to validate the sizing results.
"],"dc:identifier":["https://commons.erau.edu/edt/393"],"dc:subject":["propulsive","battery packs","aviation","Aerospace Engineering","Propulsion and Power"],"dc:title":["Propulsive Battery Packs Sizing for Aviation Applications"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis - Open Access"],"thesis:degree_name":["Master of Science in Aerospace Engineering"]},"updated_at":"2026-07-27T19:26:34Z"}