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Comment Post #284862 @#8049a Origin of thrust for the $n$'th engine is denoted $r_n$ in my scenario. It's also not quite as simple as it looks at first. Consider identical engines pointed the same direction. Easy to see the effective center of thrust is right between the two. Now throttle one of those engines down to 50%...
If I have a rocket with some known number of engines $n$, each producing thrust with arbitrary direction $Tn$ and center of thrust $rn$, the total thrust amount and direction $T{total}$ is equal to the sum of all thrust vectors: $$T{total}=\sumi^nTn$$ How is the center of thrust calculated fr...