The combustion temperature of chemical fuel in a rocket engine is T = 3000 K, the average molar mass of the combustion products is µ = 30 g/mol. The outflow of combustion products occurs adiabatically. Molar heat capacity of the combustion products c = 33.4 J/(mol⋅K). The gas pressure at the rocket exit P is much lower than the gas pressure in the rocket. Determine the minimum mass fuel consumption that ensures the launch of a rocket of mass M = 1000 t from the Ground.