If a rocket's thrust $F$ is given by $F = \dot{m}v_e$, where $\dot{m}$ is mass flow rate ($kg/s$) and $v_e$ is effective exhaust velocity ($m/s$), find the required mass flow rate in $kg/min$ to maintain $500 \text{ kN}$ of thrust with an exhaust velocity of $3000 \text{ m/s}$.