International Research Journal of Engineering and Technology (IRJET)
e-ISSN: 2395-0056
Volume: 11 Issue: 06 | Jun 2024
p-ISSN: 2395-0072
www.irjet.net
DESIGN AND FABRICATION OF PROPULSION SYSTEM USING IONIC PRINCIPLE Aayush Dhokne1, Manoj Gore1, Mayuresh Desai1, Sudhanshu Gurav1, Dr. S. V. Chaitanya2 1U.G. Student, Dept. of Mechanical Engineering, AISSMS COE, Pune, India
2Head of Department, Dept. of Mechanical Engineering, AISSMS COE, Pune, India
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Abstract - This is a research paper on Design and
continuous low-thrust maneuvers, such as station keeping, orbit adjustments, and long-duration missions [4]. They are commonly used in geostationary satellites, deep space probes, and scientific missions where efficiency and longevity are prioritized over rapid acceleration [5].
development of propulsion system using ionic principle. Ion thrusters have emerged as an efficient alternative to conventional propulsion systems due to their high specific impulse, resulting in minimal fuel requirements. While the thrust, they generate is significantly lower compared to chemical propulsion systems, ion thrusters excel in various mission applications, including orbital positioning for geostationary satellites, orbit and attitude control, and versatile mission profiles. Unlike chemical propulsion, which is unsuitable for long-duration missions, ion thrusters enable successful long-range missions. Electric propulsion (EP) facilitates numerous strategic missions by NASA and other space agencies, aiding in the exploration of our solar system, the discovery of new planets, stars, galaxies, and potentially habitable Earth-like planets in neighboring systems, and the search for extraterrestrial life. The development of EP technology supports these missions by integrating advanced technologies into ongoing projects. This article provides a concise overview of electric propulsion systems, with a specific focus on ion thrusters.
1.1 Problem Statement Develop a comprehensive design and modelling framework for an efficient and reliable ionic thruster, addressing key parameters such as propulsion efficiency, thrust-to-weight ratio, power consumption, and operational stability. This involves optimizing the thruster's geometry, electrode configuration, and power supply to maximize thrust generation while minimizing energy consumption and potential failure points. The goal is to achieve a practical and scalable propulsion solution suitable for various space missions, from satellite maneuvers to deep space exploration.
1.2 Objectives
Key Words: Ionic Thruster, Corona Discharge, Ions, Propulsion System, Hall Thruster, Spacecraft Travel, Propellent, Final year Project.
1.INTRODUCTION An ion thruster is a spacecraft propulsion system that generates thrust by ionizing and accelerating propellant, differing from traditional chemical rockets which rely on combustion. It operates on the principle of electrostatic acceleration of ions, often using gases like xenon [1]. This technology, which dates to the early 20th century, has seen significant advancements in recent decades, particularly in space exploration. Ion thrusters are highly efficient, offering much higher specific impulse compared to conventional rocket engines, which is crucial for long-duration space missions due to their fuel economy [2]. The ionization process in these thrusters involves electron guns or RF antennas to create positively charged ions, which are then accelerated by an electric field to produce thrust. Although they generate lower thrust than chemical rockets, their ability to run continuously for extended periods makes them ideal for position maintenance, orbit control, and interplanetary travel [3]. This high efficiency and durability make ion thrusters suitable for applications requiring
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To develop a small-scale technology demonstrator that is propelled by ionization of air.
To understand the working of ionization principle.
To develop a thrust without a moving part.
2. OVERVIEW ABOUT IONIC THRUSTER The ion engine operates on a straightforward principle, using a strong electric field between two grids acting as electrodes to accelerate heavy positive ions. These ions form a high-speed exhaust stream, generating relatively low thrust but achieving high specific impulse (Isp). The propellant must be ionized before this process. In an ionic thruster, a gas propellant enters a discharge chamber at a controlled rate. A hot, hollow cathode (negative electrode) at the center of the chamber emits electrons, which are attracted to a cylindrical anode (positive electrode) around the chamber walls. Some of the electrons collide with and ionize atoms of the propellant, creating positively charged ions. These ions are then drawn toward the grids to be accelerated.
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