Ion thrusters operate by accelerating ions to high velocities using electric fields. The thrust is generated by the expulsion of these accelerated ions. The mass flow rate of the propellant and the exhaust velocity are key parameters influencing the specific impulse.
If you have specific data on thrust, burn time, and the mass of propellant consumed during the operation of an electrostatic ion thruster, you can use these formulas to calculate the specific impulse.
Ion thrusters are known for their relatively high specific impulse compared to traditional chemical rockets, making them suitable for long-duration space missions. The specific impulse for a specific ion 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