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The study begins with roadmap analysis for the electric propulsion aircraft (EPA) development. Then the requirements for the overall performance of EPA are analyzed. The paper focus on the relationships among battery energy density (BED), take-off Power/weight ratio (P/W ratio) and range, takeoff distance, Lift/drag ratio (L/D), cruise Energy ratio (CER) and thrust ratio (TR). The estimation equations and diagrams are also presented. It is pointed that the range will increase when BED, L/D, CER and TR raise their numerical values. At the given range, enhancing the L/D, CER and TR will decrease the BED request. Currently the fly range shortage of EPA is phenomenal mainly because of lower BED. Thus it is difficult to replace the oil powered aircrafts. The study shows P/W ratio will grows up when take-off velocity, airplane drag ratio increase or the take-off distance cut down. It is also showed that in terms of weight the electric powered thrust system is lighter than the oil powered thrust system.

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Study on Overall Performance Decision for Electric Propulsion Aircraft

  • 会议论文

  • 发表日期：

    2026年

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  • Longbin Li,
  • Luo Wang,
  • Liao Sun,
  • Yueli Li

摘要

The study begins with roadmap analysis for the electric propulsion aircraft (EPA) development. Then the requirements for the overall performance of EPA are analyzed. The paper focus on the relationships among battery energy density (BED), take-off Power/weight ratio (P/W ratio) and range, takeoff distance, Lift/drag ratio (L/D), cruise Energy ratio (CER) and thrust ratio (TR). The estimation equations and diagrams are also presented. It is pointed that the range will increase when BED, L/D, CER and TR raise their numerical values. At the given range, enhancing the L/D, CER and TR will decrease the BED request. Currently the fly range shortage of EPA is phenomenal mainly because of lower BED. Thus it is difficult to replace the oil powered aircrafts. The study shows P/W ratio will grows up when take-off velocity, airplane drag ratio increase or the take-off distance cut down. It is also showed that in terms of weight the electric powered thrust system is lighter than the oil powered thrust system.