A rocket stage designed for deep$-$space missions con$-$sists of $200$ kg of fuel and $300$ kg of structure

and payload combined. In terms of burnout velocity, what would be the advantage of reducing the

structural $$payload mass by $1$ percent $(3$ kg$)$ and using that mass for additional fuel? Express your

answer in terms of a percent increase in burnout velocity. Repeat your calculation for a $5$ percent

reduction in the structural $$payload ma