TY - JOUR
T1 - Effect of Electrode Angle on Pulsed Plasma Thruster Performance
AU - Li, Yueh Heng
AU - Dorn, Killian
AU - Hsieh, Hsun Chen
AU - Kuo, Tien Chuan
AU - Hsu, Yao Chung
N1 - Funding Information:
This work was financially supported by the Ministry of Science and Technology, Taiwan, under the grant numbers MOST 105-2628-E-006-005-MY3 and MOST 108-2628-E-006-008-MY3, and by National Space Organization, National Applied Research Laboratories, Taiwan.
Publisher Copyright:
© 2021, The Aeronautical and Astronautical Society of the Republic of China. All right reserved.
PY - 2021/9
Y1 - 2021/9
N2 - This study focused on the development of a pulsed plasma thruster (PPT) using various electrode angles, including asymmetric ones. Four electrode angles and asymmetric configuration setups were selected and examined, and we revealed their influence on the performance and reliability of the PPT. The original design, manufacture, and demonstration of the PPT were completed. An interesting phenomenon was observed and elucidated using a high-speed camera, and hypothetical solutions were addressed. In addition, a Taguchi method was employed to analyze the effects of design parameters on PPT performance and reliability. The results demonstrated that the electrodes with a deflection angle of 40° would deteriorate the reliability of PPT discharging, and the corresponding failure rate would reach 50% and more.
AB - This study focused on the development of a pulsed plasma thruster (PPT) using various electrode angles, including asymmetric ones. Four electrode angles and asymmetric configuration setups were selected and examined, and we revealed their influence on the performance and reliability of the PPT. The original design, manufacture, and demonstration of the PPT were completed. An interesting phenomenon was observed and elucidated using a high-speed camera, and hypothetical solutions were addressed. In addition, a Taguchi method was employed to analyze the effects of design parameters on PPT performance and reliability. The results demonstrated that the electrodes with a deflection angle of 40° would deteriorate the reliability of PPT discharging, and the corresponding failure rate would reach 50% and more.
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U2 - 10.6125/JoAAA.202109_53(3).02
DO - 10.6125/JoAAA.202109_53(3).02
M3 - Article
AN - SCOPUS:85111486073
SN - 1990-7710
VL - 53
SP - 353
EP - 368
JO - Journal of Aeronautics, Astronautics and Aviation
JF - Journal of Aeronautics, Astronautics and Aviation
IS - 3
ER -