Magnetoplasma thrusters, including designs like the Variable Specific Impulse Magnetoplasma Rocket (VASIMR), are types of electric propulsion systems that use magnetic and electric fields to ionize and accelerate propellant.
For magnetoplasma thrusters, the thrust is typically generated by the accelerated ions or 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.
Magnetoplasma thrusters are known for potentially achieving high specific impulse values compared to traditional chemical rockets, making them suitable for long-duration space missions. The specific impulse for a specific magnetoplasma 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