The specific impulse is a key performance parameter for rocket engines, measuring their efficiency in converting propellant mass into thrust. For hybrid rocket engines, which combine features of both solid and liquid propulsion systems, the specific impulse is influenced by factors such as the specific design and propellant combination.
For hybrid rocket engines, the mass flow rate can be influenced by the characteristics of both the liquid and solid propellants.
It’s important to note that the specific impulse of a hybrid rocket engine may depend on the specific design features, combustion characteristics, and efficiency of the combustion process. Hybrid rocket engines are known for their flexibility and safety features compared to some other propulsion systems.
It is defined as the thrust generated per unit of propellant expended and is expressed in seconds.
where,
- is the specific impulse of the rocket engine (in seconds, s)
- F is the Thrust Produced
- ṁ is the mass flow rate of propellant in KG/Sec
- g0 is the acceleration due to gravity