In the field of astronautics and aerospace engineering, the rocket equation, also known as the Tsiolkovsky rocket equation, plays a fundamental role in describing the motion of vehicles that utilize rocket propulsion. It establishes a relationship between the velocity of a rocket, the effective exhaust velocity of its propulsion system, and the natural logarithm of the ratio of the initial mass (including fuel) to the final mass (after fuel expenditure).
The equation is expressed as:
Where:
- is the change in velocity of the rocket (delta-v).
- is the effective exhaust velocity of the propulsion system (specific impulse multiplied by gravitational acceleration).
- is the initial mass of the rocket (including fuel).
- is the final mass of the rocket (after the fuel is expended).