Next Article in Journal
Wake-Model Effects on Induced Drag Prediction of Staggered Boxwings
Next Article in Special Issue
Prilling and Coating of Ammonium Dinitramide (ADN) Solid Green Propellant in Toluene Mixture Using Ultrasound Sonication
Previous Article in Journal
Numerical Investigation on Windback Seals Used in Aero Engines
Previous Article in Special Issue
Molecular Dynamics Electrospray Simulations of Coarse-Grained Ethylammonium Nitrate (EAN) and 1-Ethyl-3-Methylimidazolium Tetrafluoroborate (EMIM-BF4)
Article Menu
Issue 1 (March) cover image

Export Article

Open AccessArticle
Aerospace 2018, 5(1), 13; https://doi.org/10.3390/aerospace5010013

Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster

Department of Electronics and Communication Engineering, Manipal Institute of Technology, Manipal, Karnataka 576104, India
Received: 19 December 2017 / Revised: 16 January 2018 / Accepted: 18 January 2018 / Published: 22 January 2018
Full-Text   |   PDF [1240 KB, uploaded 22 January 2018]   |  

Abstract

Liquid propellants are fast becoming attractive for pulsed plasma thrusters due to their high efficiency and low contamination issues. However, the complete plasma interaction and acceleration processes are still not very clear. Present paper develops a multi-layer numerical model for liquid propellant PPTs (pulsed plasma thrusters). The model is based on a quasi-steady flow assumption. The model proposes a possible acceleration mechanism for liquid-fed pulsed plasma thrusters and accurately predicts the propellant utilization capabilities and estimations for the fraction of propellant gas that is completely ionized and accelerated to high exit velocities. Validation of the numerical model and the assumptions on which the model is based on is achieved by comparing the experimental results and the simulation results for two different liquid-fed thrusters developed at the University of Tokyo. Simulation results shows that up-to 50 % of liquid propellant injected is completely ionized and accelerated to high exit velocities (>50 Km/s), whereas, neutral gas contribute to only 7 % of the total specific impulse and accelerated to low exit velocity (<4 Km/s). The model shows an accuracy up-to 92 % . Optimization methods are briefly discussed to ensure efficient propellant utilization and performance. The model acts as a tool to understand the background physics and to optimize the performance for liquid-fed PPTs. View Full-Text
Keywords: electric propulsion; space propulsion systems; pulsed plasma thruster; liquid propellant; numerical modeling; ionized gas electric propulsion; space propulsion systems; pulsed plasma thruster; liquid propellant; numerical modeling; ionized gas
Figures

Figure 1

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0).
SciFeed

Share & Cite This Article

MDPI and ACS Style

Misra, K. Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster. Aerospace 2018, 5, 13.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Aerospace EISSN 2226-4310 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top