• 해당 논문은 2nd International Conference on Drones and Unmanned Systems (DAUS’ 2026) 에서 발표되었습니다.
YouYoung Yang1, JeongHwan Oh1, JunSeong Lee1, SungSu Kim1 and KwangHyun Lee1
MOASOFT Co.,Ltd, Seoul, 05770, Republic of Korea
Tel.: +82-24203203
E-mail: yyyang@moasoftware.co.kr
Summary
본 연구는 탄소중립 항공 기술의 일환으로, 개조된 세스나 172R 항공기(C-172RHX)에 적용된 수소 연료전지–배터리 하이브리드 전기추진 시스템의 시스템 수준 모델링과 임무 프로파일 기반 전력 분석 기법을 제안한다. 연구에서는 연료전지, 배터리, 전력분배장치, 인버터, 전기모터를 통합한 추진 시스템 모델을 구축하고, 실제 운항 프로파일을 기반으로 비행 단계별 전력 흐름과 에너지 소비 특성을 분석하였다. 이를 통해 구성 요소 용량 산정, 안전성 평가, 열관리 전략 수립 및 향후 수소전기 항공기 인증 체계 개발에 필요한 기초 데이터를 제공하며, 무배출 항공 기술 발전에 기여하고자 한다.
This study presents a system-level modeling framework and mission-profile-based power analysis for a hydrogen fuel cell–battery hybrid electric propulsion system applied to a retrofitted Cessna 172R aircraft, referred to as the C-172RHX. Motivated by global efforts toward carbon-neutral aviation, hydrogen-electric propulsion has emerged as a promising alternative for small and regional aircraft. Despite active demonstrations worldwide, system-level evaluations under realistic operational conditions remain limited. To address this gap, a unified powertrain model integrating the fuel cell stack, battery, power distribution unit, inverter, and electric motor is developed. Using a mission profile derived from the aircraft’s Pilot Operating Handbook, the model quantifies power flow, energy consumption, and power-split characteristics across all flight phases. The results provide insights for component sizing, safety assessment, and thermal management strategies, and support future certification frameworks for hydrogen-electric aircraft. This work contributes to advancing zero-emission aviation technologies.
1. 서론
the present study investigates a hydrogen-electric conversion of the certified Cessna 172R, designated C-172RHX, in which the conventional reciprocating engine is replaced by a hydrogen fuel cell–battery hybrid electric propulsion system. This work develops a system-level power and energy analysis framework and performs a mission-profile-based assessment of propulsion power demand and energy consumption by integrating baseline performance data from the C-172R Pilot’s Operating Handbook with models of the fuel cell system, high-voltage battery, power distribution unit, inverter, and electric motor. The results aim to support early-stage design and feasibility assessment of hydrogen fuel cell–battery hybrid propulsion systems for retrofitted light aircraft.
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2. 결론
This study presented a system-level modeling and mission-based power analysis of a hydrogen fuel cell–battery hybrid electric propulsion system retrofitted to a certified Cessna 172R aircraft (C-172RHX). The results demonstrate that the hybrid powertrain can satisfy mission-dependent power requirements of a CS-23 class light aircraft while maintaining operational margins. Transient peak demands during taxi, takeoff, and climb are effectively supported by the battery system, whereas steady-state cruise operation is predominantly sustained by the fuel cell near its nominal continuous rating. The estimated cruise hydrogen consumption, derived from experimental fuel cell data, indicates that the selected onboard hydrogen storage capacity is sufficient for the defined reference mission.
- 수소연료전지추진시스템 장착 및 항공기 인증체계 구축 관련 문의 : 02-420-3203 / Contact us – (주)모아소프트 (moasoftware004.mycafe24.com/)
