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The article considers the transfer of utilization technologies for detachable elements of the launch vehicle (LV) structures during the launch at the powered phase after their detachment at the unpowered phase of the descent trajectory to the utilization of tanks for fuel and lubrication materials (FLM) delivered to outlying regions of the Arctic. Opposed to detachable LV structures, utilization of FLM tanks is carried out under ground conditions by burning fuel elements prepared from FLM tank structures in conventional boilers and domestic heating furnaces. The research task has been set considering the possibility of implementing the requirements in the design and construction of polymeric composite material (PCM) to manufacture combustible tanks for the FLM storage. The requirements have been formulated for the production stages of combustible PCM and utilization system including the definition of design and construction parameters of PCM. The results of preliminary experimental studies in terms of determining the combustibility of the proposed PCM and their strength characteristics have shown the possibility of developing combustible structures.

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Abstract. The experimental research of the carbon composite material sample of payload fairing half structural element was carried out under different types of loading. Mathematical and physical modeling of the sample loading using aerodynamic flow was conducted. Heat loading was researched by the method of a thermal analysis during which typical heat dots corresponding to the changes in the sample structure were determined. Ultrasonic influence on the sample characteristics was considered. As a result, the value of heat leak to the structure surface while moving in the atmospheric phase of the descent was determined.