A “hydrazine thruster” is a type of rocket engine that uses hydrazine as a propellant. These thrusters are commonly used in spacecraft for various purposes, such as attitude control, orbital maneuvers, and spacecraft station-keeping.
Hydrazine is often used as a monopropellant or as one component of a bipropellant system. In the context of monopropellant hydrazine thrusters, the mass flow rate of the hydrazine and the efficiency of the propulsion system influence the specific impulse.
If you have specific data on thrust, burn time, and the mass of hydrazine consumed during the burn for a particular thruster, you can use the formula to calculate the specific impulse. Keep in mind that the specific impulse may vary based on the specific design and operational conditions of the thruster.
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