A pulse-fed engine is a type of rocket engine that receives propellant in discrete pulses rather than continuously. These engines are commonly used in certain spacecraft propulsion systems, particularly those requiring precise control and modulation of thrust.
In a pulse-fed engine, the mass flow rate of exhaust gases during each pulse is determined by the rate at which propellant is fed into the combustion chamber. The exhaust velocity and pressure during each pulse are influenced by the combustion process and the specific design of the rocket engine.
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).