Abstract
The engineering calculation method has been developed for investigation of the process of thermal destruction of “Fregat” upper stage at deorbiting and descent into the Earth's atmosphere. The results of calculation of its descent trajectory and characteristics of aerodynamic heating are presented. Within the framework of the thermodynamic approach, the authors investigated the process of pressure increase in the tanks due to heating and evaporation of the liquid phase of fuel. Stresses in the shells, the height and the energy equivalent of explosive destruction of tanks were calculated depending on the degree of their filling with remains of the components of liquid fuel.
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