Aerodynamic heating of fuel tanks of a space upper stage at descent in the atmosphere

A technique for calculating the trajectory and aerodynamic heating characteristics of the Fregat upper stage at leading away from the working orbit and descent in the atmosphere of the Earth is presented. The problem about increasing pressure in fuel tanks caused by heat loading and by liquid fuel evaporation is solved using the thermodynamic approach. Thermodynamic parameters, tanks shells stress, height, and the trinitrotoluene equivalent of explosive destruction of tanks depending on liquid fuel filling are calculated by an example of leading away an upper stage from the sunsynchronous orbit.