1 , Manko Т. V., Manko Т. Ракетное вооружение. V., Manko Т. Ракетное вооружение. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft Автори: Husarova I. V., Manko Т. Ракетное вооружение. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft Автори: Husarova I. V., Manko Т. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft Автори: Husarova I. V., Manko Т. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft Автори: Husarova I. V., Manko Т. More Citation Formats Harvard Chicago IEEE AIP ДСТУ 8302:2015 ДСТУ ГОСТ 7.1:2006 (ВАК) ISO 690:2010 BibTeX на сайт ДП «КБ «Південне»
]]>21. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2017 (2); 121-126
Language: Russian
Annotation: 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.
Key words:
Bibliography:
1. Aerothermal performance and structural integrity of a René-41 thermal protection system at Mach 6.6 / W. D. Deveikis, R. Miserentino, I. Weinstein, J. L. Schideler. NASA-TN-D-7943, NASA, Washington DC. 1975. 105 р.
2. Poteet C. C., Blosser M. L. Improving Metallic Thermal-Protection-System Hypervelocity Impact Resistance Through Numerical Simulation. Journal of Spacecraft and Rockets. 2004. Vol. 41, No. 2. Р. 221-232.
3. Advanced metallic thermal protection system development / M. L. Blosser, R. R. Chen, I. H. Schmidt et al. AIAA-2002-0504; AIAA, Washington DC. 2002. 56 р.
4. David E. European Directions for Hypersonic Thermal Protection Systems and Hot Structures. 31st Annual Conference on Composite Materials and Structures (Daytona Beach, FL, January 22, 2007). 44 р.
5. Gusarova I. A. Selection of Scheme of Heat Protection Tile Attachment to Reusable Spacecraft Body. Problems of Designing and Manufacturing Flying Vehicle Structures. 2016. No. 4 (88). P. 105-113.
6. Gusarova I. A. Evaluation of Thermal Resistance of Three-Layer Honeycomb Panel Produced from YuIPM-1200 Alloy by Method of Diffusion Welding in Vacuum / I. A. Gusarova, М. Parko, А. М. Potapov, Y. V. Fal’chenko, L. V. Petrushinets, Т. V. Melnichenko, V. E. Fedorchuk. Automatic Welding. 2016. No. 12 (759). P. 31-35.
7. Patent 108096 Ukraine. Method of Producing Heat-Resistant Alloy Based on Nichrome / V. V. Skorokhod, V. P. Solntsev, G. O. Frolov, Т. O. Solntseva, О. М. Potapov, V. G. Tikhiy, I. A. Gusarova, Y. M. Litvinenko / Application No. а2012 11691; Claimed 04.10.2012; Published 25.03.2015, Bulletin No. 6. 4 p.
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1 , Manko Т. V., Manko Т. V., Manko Т. Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle Автори: Husarova I. V., Manko Т. Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle Автори: Husarova I. V., Manko Т. Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle Автори: Husarova I. V., Manko Т. Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle Автори: Husarova I. V., Manko Т. More Citation Formats Harvard Chicago IEEE AIP ДСТУ 8302:2015 ДСТУ ГОСТ 7.1:2006 (ВАК) ISO 690:2010 BibTeX на сайт ДП «КБ «Південне»
]]>4. Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2017 (1); 23-29
Language: Russian
Annotation: The thermal analysis was made for external surfaces of a reusable high-altitude supersonic flying vehicle being a part of a space transportation system. The basic criteria were determined for selection of its heat-resistant and heat-protective structures.
Key words:
Bibliography:
1. Kondratenko F. I. et al. Aerodynamic Heating and Thermal Protection of Intercontinental Ballistic Missiles / F. I. Kondratenko, P. S. Savoysky, V. I. Sidov, I. M. Fomishenko. М, 1973. 288 p.
2 Avduyevsky V. S. et al. Fundamentals of Heat Transfer in Aerospace Engineering / V. S. Avduyevsky, B. M. Galitseisky, G. A. Glebov. М., 1975. 624 p.
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