Pulsed plasma thrusters (PPTs) are a type of electric propulsion system used in spacecraft. For pulsed plasma thrusters, the thrust is typically generated by the acceleration of ionized plasma. The mass flow rate of the propellant is influenced by the power applied to the thruster, the efficiency of ionization and acceleration, and the specific design parameters of the thruster.
Pulsed plasma thrusters are known for achieving relatively high specific impulse values compared to traditional chemical rockets, making them suitable for precision spacecraft maneuvers and attitude control. The specific impulse for a specific pulsed plasma thruster design can be determined through performance testing, simulations, or theoretical models based on the design parameters.
It is defined as the thrust generated per unit of propellant expended and is expressed in seconds.
where,
- is the specific impulse of the rocket engine (in seconds, s)
- F is the Thrust Produced
- ṁ is the mass flow rate of propellant in KG/Sec
- g0 is the acceleration due to gravity