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- W2904252661 abstract "One of the ways of solving the problem of reducing the man-made impact of rocket and space activities on the environment, based on the reduction of the impact areas of separating launch vehicle component (LVC) in the process of launching payloads into orbit are considered. Known particular solutions to this problem, for example, the return of spent LV stage accelerators to the point of launch, a multiple reduction in the impact areas of spent LV stage accelerators due to their controlled descent, however, there is open the question of how to deal with such LVC as payload fairings (PF) and aft-interstage (AIS) having significant areas of the impact areas. The possibility of burning LVC, such as PF and AIS, made of a composite material based on carbon fiber is considered. The thermal conditions of LVC during their movement on the descent path are investigated, the necessary amount of heat for heating the LVC to the ignition temperature is determined and various options of energy materials (EM) are considered. On the example of a typical PF, having a design of a polymer composite material (carbon fiber) with an aluminum honeycomb core (AHC), another structure is proposed, where a filler based on a mixture of polymer films such as ABS structure and energy material is used instead of AHC. The proposed design of the polymer composite material allows to provide the necessary operation parameters of the PF (strength, thermal protection, etc.) at the stage of preparation of the PF for a launch, LV ascent in the active section of the trajectory. And the possibility of burning after the mission with minimal energy costs allows to provide." @default.
- W2904252661 created "2018-12-22" @default.
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- W2904252661 date "2018-11-01" @default.
- W2904252661 modified "2023-09-26" @default.
- W2904252661 title "Development of proposals for the synthesis of polymer composite materials capable of combustion after the mission" @default.
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- W2904252661 doi "https://doi.org/10.1088/1742-6596/1134/1/012061" @default.
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