Performance Analysis of a Pure Electric Aircraft.

This paper offers an extensive performance analysis of an all-electric airplane based on a MATLAB/Simulink simulation environment. The research concentrates on the influence of major design and operating parameters i.e., battery capacity, propulsion efficiency, and maximum takeoff weight (MTOW) on representative airplane performance characteristics such as range, endurance, rate of climb, and power usage. Modular simulation architecture for Simulink was defined with main subsystems such as electric propulsion, energy battery management, and flight dynamics. Four discrete case studies were simulated for testing performance sensitivities and trade-offs of operations in various varying configurations against the Pipistrel Velis Electro aircraft profile. Results identify the non-linear character of propulsion efficiency and range achievable, the MTOW imposed limitation of climb capability, and the maximum state-of-art lithium-based battery energy density constraint. Optimum parameter values leading to maximum mission effectiveness within legislative and structural confines are also obtained. The findings of this study provide a foundation for further development of electric aircraft, and provide valuable information for design optimization, feasibility analysis, and implementation in practice of sustainable aviation technologies.