AbstractDischarge reliability is typically neglected in low-ignition-cycle ablative pulsed plasma thrusters (APPTs). In this study, the discharge reliability of an APPT is assessed analytically and experimentally. The goals of this study are to better understand the ignition characteristics and to assess the accuracy of the analytical method. For each of six sets of operating conditions, 500 tests of a parallel-plate APPT with a coaxial semiconductor spark plug are conducted. The discharge voltage and current are measured with a high-voltage probe and a Rogowski coil, respectively, to determine whether the discharge is successful. Generally, the discharge success rate increases as the discharge voltage increases, and it decreases as the electrode gap and the number of ignitions increases. The theoretical analysis and the experimental results are reasonably consistent. This approach provides a reference for designing APPTs and improving their stability.
HighlightsDischarge reliability cannot be neglected in high-ignition-cycle APPTs.Strengthening electric field intensity will improve the discharge performance.The ignition circuit should be designed to get larger secondary emission coefficient.A method for automatically cleaning the spark plug electrodes is recommended.
Discharge reliability in ablative pulsed plasma thrusters
Acta Astronautica ; 137 ; 8-14
2017-04-06
7 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Discharge Feasibility in Ablative Pulsed Plasma Thrusters Using Space Debris (AIAA 2018-4589)
British Library Conference Proceedings | 2018
|A new ablation model for ablative pulsed plasma thrusters
Elsevier | 2019
|