A conceptual design of an experimental demonstration model of three-layer structure of a launch vehicle body is proposed, based on the replacement of aluminum honeycomb filler with an energy-related material, in particular, based on composite solid rocket propellants. When energy-related material is burned under vacuum conditions, pyrolysis occurs in the experimental demonstration model material, including thermal destruction of the experimental demonstration model material. The efficiency criterion for the heat and mass exchange process during the energy-related material combustion inside the experimental demonstrator and, accordingly, the design concept of the experimental demonstrator, is the skin temperature. After the thermal destruction process is completed in the experimental demonstrator pyrolysis process, in accordance with the proposed concept of creating the experimental demonstrator aerodynamic loading is carried out to assess the degree of dispersion of the experimental demonstrator. The conducted numerical experiments showed the fundamental possibility of significant influence of the design concept of the experimental demonstrator on the skin temperature and, accordingly, an increase in the degree of thermal destruction of the skin material and the possibility of dispersion of the experimental demonstrator under aerodynamic influence. Comparisons were made with the results of physical modeling of burning the experimental demonstrator with specific energy material, which were close to the results of numerical experiments.