The thermal behavior of a magnetic induction thruster utilizing a solid conducting ring as the reaction mass is analyzed. Electrical energy initially stored in a capacitor is discharged through a coil in close proximity to the reaction mass. Opposing magnetic fields subsequently accelerate the reaction mass to a high exit velocity. During the acceleration process, the reaction mass is resistively heated and the effects of the varying temperaturedependent electrical conductivity, specific heat, and density are analyzed and compared to the constant property case. The effects of thruster geometry and reaction-mass phase changes are also examined.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science