Analysis of the Anisotropic Heat-Protective Material Application Effectiveness in the Implementation of Trajectories with Multiple Re-entries into the Atmosphere

In the case of full implementation of the programs of studying and developing the Moon, announced in recent years (“Luna”, Artemis, Chang’e), significant increase in cargo turnover between the Moon and the Earth is expected. Therefore the research and development of appropriate spacecrafts and their structural elements is believed to be promising, especially thermal protection coatings ensuring spacecraft safety during movement (descent) in the dense atmosphere layers. A special characteristic of the trajectory of the spacecraft returning from the Moon’s orbit is the closeness of the speed of its entry into the Earth’s atmosphere to the parabolic one. This circumstance significantly complicates solving the problem of creating thermal protection for such a vehicle, because of higher convective and radiative heat flows compared to those acting on orbital landers. The analysis showed that when implementing the trajectory of the return of spacecraft with multiple re-entries into the Earth’s atmosphere, a trajectory can be selected (at least for cargo flights) so that the intensity of heat exchange on the surface of the coating does not exceed the permissible level. In this case, use of modern and advanced anisotropic heat-protective composite materials can reduce the spacecraft surface temperature to a level that does not cause destruction of the thermal protection coating.

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