Particle in Cell Simulation of kW Hall Thruster

The propulsion system in satellites provides; collision avoidance, orbital maneuvering, station keeping, orbit transfers, formation flights and interplanetary trajectories. The effectiveness of the satellite propulsion system is dependent on the size, weight, available power, cost effectiveness and

Project Title

Particle in Cell Simulation of kW Hall Thruster

Project Area of Specialization

Electrical/Electronic Engineering

Project Summary

The propulsion system in satellites provides; collision avoidance, orbital maneuvering, station keeping, orbit transfers, formation flights and interplanetary trajectories. The effectiveness of the satellite propulsion system is dependent on the size, weight, available power, cost effectiveness and the mission requirements. The propulsion is generally of two types: Chemical propulsion and Electric propulsion. Chemical propulsion is used in space launch systems like SpaceX’s Falcon, but it cannot be used in satellite propulsion as it has low specific impulse, thus consuming more fuel, and large mass. Electric propulsion on the other hand is fuel efficient thus less fuel mass and storage space are required. Due to volume and mass constraints, the small satellites prefer electric propulsion (EP). 
There are three types of electric propulsion (EP) which include electrostatic, electromagnetic and electrothermal. In the electrostatic thrusters, the electrical power is used to ionize the propellant for the formation of the plasma. The ions are then accelerated using the electric field that is provided by the electrodes. These types of the thrusters include Electrospray Thrusters, Gridded Ion Thrusters and Hall Thrusters. In the electrothermal thrusters, the electrical power is used to heat the propellant to high temperature. The propellant is then accelerated using converging and diverging nozzles. In electromagnetic thrusters, both magnetic and electric fields are applied which ionize and accelerate the propellant. Due to usage of both electric and magnetic fields these types of systems generally require large amounts of power. 
The review and analysis show that the thrust values for electrostatic thrusters range from 3?N to 92mN depending on power budget ranging from 50mW to 2.3KW, specific impulse ranging from 150s to 7500s, type of propellant and type of thruster used like hall thruster, colloid, and Field Emission Electric Propulsion (FEEP) thruster. It is evident that electrostatic thrusters are more fuel efficient than the other two.

Hall Thruster provides more thrust for a given amount of power as compared to other electrostatic thrusters. First, xenon gas molecules are ions by collsion with fast moving electrons produing plasma. Ions are then accelerated under action of electrostatic forces. This expells ions out of thruster, exerting thrust on the satellite.

 

Project Objectives

Main objective of this project is to develop a prototype of hall thruster. Following are objectives of the project:

1. Case Study of existing Electric Propulsion Systems
2. Design and Development of Hall Thruster for Small Satellite
3.  Particle in Cell simulation is to be carried out by using particle solver of CST Studio Suite. Due to its effectiveness and efficiency, Particle in Cell algorithm is a widely used computational tool for kinetic plasma modeling. Plasma modelling is vital in analyzing and optimizing the performance of an electric thruster. Various performance parameters of a Hall Thruster are simulated in this project.

Project Implementation Method

The project has been divided into following modules:

1. Litrature review
2. Design and development of electron accelerator 
3. Design and development of ionization chamber
4. System Integration
5. Testing
6. Particle in Cell Simulation on CST Particle Solver
7. Comparison of the results

Benefits of the Project

The project has great significance in satellite applications. Development of an electric propulsion system has capablity to extend functionality of a satellite. It can enable a satellite to avoid collisions with space debris, perform orbital manuevers, keep its station and carry out deep space explorations. A satellite equipped with electric propulsion system can be way more efficient and effeective. Development of the propulsion system will enhance functionality of satellites in every respect.

Technical Details of Final Deliverable

Final deliverable will be a working prototype of hall thruster. It would performe its operation between voltages of 500-4500 volts. Particle in Cell SImulation will be used to optimize the performance of hall thruster.

Final Deliverable of the Project

HW/SW integrated system

Core Industry

Others

Other Industries

Education , Telecommunication

Core Technology

Others

Other Technologies

3D/4D Printing

Sustainable Development Goals

Quality Education, Industry, Innovation and Infrastructure

Required Resources

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