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Partial answer, waiting for a rocket scientist to chime in. This is a cool question! Celta-v calculated from exhaust velocity using the Tsiolkovsky rocket equation for each stage would be a huge overestimate because it doesn't account for things like atmospheric drag or gravity. So you'd have to numerically integrate over a specific trajectory for a final ...


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TL;DR It works for a very large amount of orbit changes First, let's take your equation and rearrange it to get rid of inconvenient values like force, time and mass. $$\frac{\Delta v_{\text{orb}}}{\Delta t} = \frac{F_{\text{retro}}}{m}$$ $$\Delta v_{\text{orb}} = \frac{F_{\text{retro}} \Delta t}{m} = - \Delta v_{\text{maneuver}}$$ $\frac{F\cdot t}{m}$ is ...


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