21. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft

21. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft

Gusarova I. А., Potapov А. М., Shevtsov Е. I., Onofrienko V. I., Gusev V. V., Manko Т. А.

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Oles Honchar Dnipro National University, Dnipro, Ukraine

Kosm. teh. Raket. vooruž. 2017 (2); 121-126
Language: Russian
The paper considers the TZS-U design developed by Yuzhnoye SDO specialists for windward part of reusable spacecraft with external metal three-layer panel, U-like joint and tiled thermal protection, in which the problem is solved of compensation of thermal expansions and sealing of gaps; for optimization of structural mass. The specially created dispersion-hardened powder alloy based on nichrome and aluminum with yttrium dioxide with decreased specific mass of 7500 kg/m3 and lighter felt of MKRF brand are used , and honeycomb filler of three-layer panel is replaced by the filler with square cell.


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