Plasma Applications in Space Technology

**Chapter 2**

**Abstract**

propulsion devices.

an exhaust velocity *U*

**23**

!

spacecraft experience a small change in velocity *dυ*

*Sukhmander Singh*

Hall Thruster: An Electric

Propulsion through Plasmas

The chapter discussed the technological application of plasma physics in space

Terahertz wave generation and welding of metals. In this chapter, the application of plasma physics in the field of electric propulsion and types has been discussed. These devices have much higher exhaust velocities, longer life time, high thrust density than chemical propulsion devices and useful for space missions with regard to the spacecraft station keeping, rephrasing and orbit topping applications. The mathematical relation has been derived to obtain the performance parameters of the

Electric propulsion (EP) devices use electric power to produce thrust. These devices have much higher exhaust velocities than chemical propulsion devices. Therefore, EP devices require much less propellant mass than chemical systems for a given space task. Here first we have overview of different thrusters and their basic

The motion of any propulsion devices is given by Newton's 3rd Law of action and equal, opposite reaction which forms the basis for the motivation for the study of electric propulsion. The rocket equation states that a device can accelerate to a desired final velocity by reaction against an expelled propellant stream [1].

Consider a rocket of mass *m*, which expels an infinitely small unit of fuel *dm* at

*mi*

*dm*

property of the propellant [2]. Conservation of linear momentum requires that the

!

!, such that

*ex* is almost constant and it is a fixed

*dt* <sup>¼</sup> <sup>0</sup> (1)

*<sup>m</sup>* <sup>¼</sup> <sup>0</sup> (2)

science. The plasma technology is using laser-plasma fusion, inertial fusion,

**Keywords:** electric propulsion, Hall thruster, impulse, exhaust velocity

**1. Overview of propulsion devices and rocket equation**

mechanism based on type of propellant used to get the thrust.

*ex*. The exhaust velocity *U*

*m dυ* ! *dt* <sup>þ</sup> *<sup>U</sup>* ! *ex dm*

ð *υf*

*dυ* !

*U* ! *ex* þ *U* ! *ex* ð *mf*

*υi*

Integrating by setting appropriate limits in mass and velocity yields

## **Chapter 2**
