This thesis focuses on electric propulsion technology associated with serial hybrid power plants most commonly associated with urban air mobility vehicles. While closed form analytical solutions for parallel hybrid aviation cases have been determined, optimized serial hybrid power plants have not seen the same degree of fidelity. Presented here are the analytical relationships between several preliminary aircraft design objectives and the battery weight fraction. These design objectives include aircraft weight, range, operation cost, and carbon emissions. The relationships are based on a serial hybrid electric propulsion architecture from an energy standpoint, and can be applied to hybrid aircraft of different weights, aerodynamic designs, and propulsive efficiencies. Three hybrid electric propulsion design related variables are also defined in the process to help clarify novel specifications unique to hybrid propulsion systems. For all design objectives, the optimal battery weight fraction is found to be either zero or one in unconstrained cases. When a minimum range requirement is applied, non-integer weight fraction solutions can be found for minimizing cost and emissions.
","abstract_html":"<p>This thesis focuses on electric propulsion technology associated with serial hybrid power plants most commonly associated with urban air mobility vehicles. While closed form analytical solutions for parallel hybrid aviation cases have been determined, optimized serial hybrid power plants have not seen the same degree of fidelity. Presented here are the analytical relationships between several preliminary aircraft design objectives and the battery weight fraction. These design objectives include aircraft weight, range, operation cost, and carbon emissions. The relationships are based on a serial hybrid electric propulsion architecture from an energy standpoint, and can be applied to hybrid aircraft of different weights, aerodynamic designs, and propulsive efficiencies. Three hybrid electric propulsion design related variables are also defined in the process to help clarify novel specifications unique to hybrid propulsion systems. For all design objectives, the optimal battery weight fraction is found to be either zero or one in unconstrained cases. When a minimum range requirement is applied, non-integer weight fraction solutions can be found for minimizing cost and emissions.</p>","abstract_has_math":false,"creators":["Yeung, Tsz Him"],"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":2019,"date_issued":"2019-05-01T07:00:00Z","date_published":"2019-05-01T07:00:00Z","updated_at":"2026-07-27T19:25:52Z","subjects":["battery","propulsion systems","aircraft design","Propulsion and Power"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/edt/457","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:creator","label":"Author","values":["Yeung, Tsz Him"]}]},{"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":["battery","propulsion systems","aircraft design","Propulsion and Power"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/edt/457"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["This thesis focuses on electric propulsion technology associated with serial hybrid power plants most commonly associated with urban air mobility vehicles. While closed form analytical solutions for parallel hybrid aviation cases have been determined, optimized serial hybrid power plants have not seen the same degree of fidelity. Presented here are the analytical relationships between several preliminary aircraft design objectives and the battery weight fraction. These design objectives include aircraft weight, range, operation cost, and carbon emissions. The relationships are based on a serial hybrid electric propulsion architecture from an energy standpoint, and can be applied to hybrid aircraft of different weights, aerodynamic designs, and propulsive efficiencies. Three hybrid electric propulsion design related variables are also defined in the process to help clarify novel specifications unique to hybrid propulsion systems. For all design objectives, the optimal battery weight fraction is found to be either zero or one in unconstrained cases. When a minimum range requirement is applied, non-integer weight fraction solutions can be found for minimizing cost and emissions.
"]},{"key":"dc:title","label":"Title","values":["Optimal Battery Weight Fraction for Serial Hybrid Propulsion System in Aircraft Design"]}]}],"canonical_facts":{"dc:creator":["Yeung, Tsz Him"],"dc:description.abstract":["This thesis focuses on electric propulsion technology associated with serial hybrid power plants most commonly associated with urban air mobility vehicles. While closed form analytical solutions for parallel hybrid aviation cases have been determined, optimized serial hybrid power plants have not seen the same degree of fidelity. Presented here are the analytical relationships between several preliminary aircraft design objectives and the battery weight fraction. These design objectives include aircraft weight, range, operation cost, and carbon emissions. The relationships are based on a serial hybrid electric propulsion architecture from an energy standpoint, and can be applied to hybrid aircraft of different weights, aerodynamic designs, and propulsive efficiencies. Three hybrid electric propulsion design related variables are also defined in the process to help clarify novel specifications unique to hybrid propulsion systems. For all design objectives, the optimal battery weight fraction is found to be either zero or one in unconstrained cases. When a minimum range requirement is applied, non-integer weight fraction solutions can be found for minimizing cost and emissions.
"],"dc:identifier":["https://commons.erau.edu/edt/457"],"dc:subject":["battery","propulsion systems","aircraft design","Propulsion and Power"],"dc:title":["Optimal Battery Weight Fraction for Serial Hybrid Propulsion System in Aircraft Design"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis - Open Access"],"thesis:degree_name":["Master of Science in Aerospace Engineering"]},"updated_at":"2026-07-27T19:25:52Z"}