Here, a derivation of the Tsiolkovsky rocket equation from Newton’s Second Law is shown. As a disclaimer, this is not original work and is not intended to be. It is shown for reference purposes. In fact multiple derivations of the equation can be found here.
We begin with the Newton’s Second Law .
However, this is a simplification of the Second Law where the mass is equal to zero. Newton’s Second Law is in fact conservation of momentum and, as a reminder, momentum is defined by mass times velocity . Thus, Newton’s Second Law in its more general form is expressed as:
In the case of a rocket, the we are analyzing the change in velocity of the rocket by the engine, which is part of the rocket. Therefore, thrust is not an external force and no external forces are acting on the rocket and the sum of forces is zero (consider a rocket in orbit rather than one flying through the atmosphere).
The term on the right hand side of the equation is the exhaust velocity of the rocket engine (denoted from here on), which is assumed to be constant. We can now integrate both side of the equation.
This gives us the following equation for the velocity change of the rocket.
Where and are the initial mass and final mass of the rocket, respectively. Note that the negative sign indicates the the velocity change of the rocket will be in the opposite direction of the rocket’s exhaust (which makes sense).
Finally, we will rewrite this in its more common form, which replaces with . Where is the rocket’s specific impulse, a measure of a rocket engine’s fuel efficiency, and is Earth’s surface gravity (). Therefore, our final form of the equation is
 Principia - F=ma
 Principia - Momentum = mv
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