Electrostatic Ion Thrusters, commonly known as ion thrusters or electrostatic ion propulsion systems, use electric fields to accelerate ions and generate thrust. The thrust force in an electrostatic ion thruster can be described using the basic rocket thrust equation with some modifications to account for the electrostatic acceleration.
Electrostatic ion thrusters are known for their high specific impulse and efficiency, making them suitable for long-duration space missions. The specific details of the thruster’s performance depend on the design of the ionization and acceleration mechanisms, as well as the choice of propellant.
The thrust equation for a turbojet engine using control volume analysis is expressed as:
where,
- is the thrust force,
- ṁe is the mass flow rate of exhaust gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle exit in meters per second (m/s).
- ṁ0 is the mass flow rate of inlet gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle Inlet in meters per second (m/s).
- is the Pressure at the nozzle exit in pascals (Pa).
- is the Pressure at the nozzle inlet in pascals (Pa).
- is the Area of the nozzle exit in square meters (m²).