A mathematical model of the heat protective coating mass ablation is formed to determine the necessary thickness of the coating under conditions of total stagnation of the gas-dynamic flow on the coating surface. The maximal linear loss of heat protective coating mass and the necessary thickness of the coating at the total stagnation point were determined. A line was revealed to improve the accuracy of the mathematical model of the heat protective coating mass loss and reduce the number of assumptions adopted in the calculation.
Assessing the Applicability of Ablative Thermal Protection Coating for an Ultralight Launch Vehicle
Russ. Aeronaut.
Russian Aeronautics ; 66 , 4 ; 683-690
01.12.2023
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
ULTRALIGHT SPACE LAUNCH VEHICLE FUSELAGE AND MANUFACTURING METHOD THEREOF
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