Comparative Analysis of Electro aerodynamic Propulsion and Electric Motors for the Zephyr 8 UAV

Authors

1 MSc student, Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran

2 Assist. Prof., Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran

3 Assoc. Prof., Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran

10.22044/jsfm.2025.15524.3926

Abstract

Electroaerodynamic propulsion is a thrust-generation technology that has gained significant attention in recent years. This study explores the advantages, disadvantages, and challenges of developing this propulsion system. Additionally, it compares the performance of electroaerodynamic propulsion with an electric propulsion system for the Zephyr 8 UAV.A mathematical model for the electric motor is presented, and performance charts are generated using data from the Zephyr 8 aircraft. Subsequently, a mathematical model for the electroaerodynamic propulsion system is developed. Using a hybrid GA-SQP optimization algorithm, an optimized design for the electro aerodynamic motor is created to achieve thrust comparable to the electric motor at an altitude of 21,000 meters and a flight speed of 10 m/s. Performance charts for the electro aerodynamic motor are also generated and analyzed. A comparison of the two systems indicates that aerodynamic ion propulsion could serve as a viable alternative to electric motors for the Zephyr 8 UAV, offering potential benefits in energy efficiency and high-altitude performance.

Keywords

Main Subjects

References

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Journal of Solid and Fluid Mechanics
Volume 15, Issue 1
March and April 2025
Pages 19-31

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