The term “Liquid Flyback Booster” typically refers to a reusable booster stage of a rocket that uses liquid propulsion and is designed to return to Earth for recovery and reuse. Liquid Flyback Boosters are designed for reusability, and their thrust force equations would include additional parameters related to their return and landing phases, such as control surfaces, aerodynamic considerations, and propulsion for controlled descent. The specific details of the engine’s performance depend on the choice of propellants, combustion efficiency, and the design of the engine components, as well as the overall booster design for reusability.
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).