Effects of electrode geometry on magnetic field distribution in a pulsed plasma thruster
- Paper number
IAC-13,C4,P,32.p1,x17271
- Author
Mr. Hua Zhang, College of Aerospace Science and Engineering, National University of Defense Technology, China
- Coauthor
Dr. Rui Zhang, College of Aerospace and Materials Engineering, National University of Defense Technology, China
- Coauthor
Mr. Daixian Zhang, College of Aerospace Science and Engineering, National University of Defense Technology, China
- Coauthor
Dr. Jianjun Wu, National University of Defense Technology, China
- Coauthor
Dr. Zhen He, College of Aerospace and Materials Engineering, National University of Defense Technology, China
- Year
2013
- Abstract
Pulsed plasma thrusters (PPTs) have been used widely in space flight mission due to their high specific impulses, low power requirements, and simple propellant management. The magnetic field distribution between electrodes has great influence on the performance of the pulsed plasma thruster. To better understand the acceleration process, an experimental prototype has been developed. And the magnetic field between the electrodes at different positions in the thruster with different electrode configurations which have the same length and different flared angle and tongue angle are measured using an induction probe. To calibrate the probe, a Helmholtz coil is built. From the experimental results, the effects of electrode geometry on magnetic field distribution between electrodes are obtained.
- Abstract document
- Manuscript document
(absent)