Laser Thermal Rocket Engines are a theoretical concept that involves using a laser beam to heat a propellant, typically hydrogen, to generate thrust. The thrust force in a Laser 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.
Laser 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, laser technology, and heating mechanism used in the system. These engines are being explored as a potential means of achieving high thrust efficiency and specific impulse for deep space exploration missions.
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).