Microwave Thermal Rocket Engines are a theoretical concept that involves using microwaves to heat a propellant, typically hydrogen, and then expelling the heated propellant to generate thrust. The thrust force in a Microwave Thermal Rocket Engine can be described using a modified version of the rocket thrust equation. This concept is more complex than traditional rocket engines, and the equations involved can be highly dependent on the specific design and technology used.
Microwave Thermal Rocket Engines are still in the theoretical and experimental stages of development, and the specific equations and parameters involved would depend on the specific design, microwave technology, and heating mechanism used in the system.
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).