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2015 №04 (08) DOI of Article
10.15407/tpwj2015.04.09
2015 №04 (10)

The Paton Welding Journal 2015 #04
TPWJ, 2015, #3/4, 63-68 pages

 
Thermal protection tile structures of shuttlecraft with different external load-carrying elements

Journal                   The Paton Welding Journal
Publisher                International Association «Welding»
ISSN                      0957-798X (print)
Issue                      № 3/4, 2015 (March/April)
Pages                     63-68
 
 
Authors
V.G. Tikhy1, V.V. Gusev1, A.M. Potapov1, E.I. Shevtsov1, I.A. Gusarova1, T.A. Manko2 and Yu.V. Falchenko3
1M.K. Yangel DB «Yuzhnoe». 3 Krivorozhskaya Str., 49008, Dnepropetrovsk, Ukraine. E-mail: info@juzhnoye.com
2O. Gonchar Dnepropetrovsk National University. 72 Yu. Gagarin Ave., 49050, Dnepropetrovsk, Ukraine
3E.O. Paton Electric Welding Institute, NASU. 11 Bozhenko Str., 03680, Kiev, Ukraine. E-mail: office@paton.kiev.ua
 
 
Abstract
Thermal protection tile structures, made from heat-resistant materials, are widely applied for protection of space vehicle bodies. Carbon-carbon composite materials, high-temperature metal alloys and structural ceramics can be used as high-temperature heat-resistant materials for manufacturing thermal protection structure tiles. The presented work gives calculation-theoretical assessment of strength properties of combined tiles of thermal protection structure of returnable space vehicles, having a metal external load-carrying element and body from carbon-carbon composite material, as well as tiles from carbon-carbon and ceramic materials. The advantages and disadvantages of each of the studied thermal protection tile systems are considered. Strength analysis is used to determine the dimensions of load-carrying elements for bodies of thermal protection structures, meeting the requirements of strength, stability and resistance to flutter, and weight of each structure. It is found that thermal protection tiles with a body from carbon-carbon composite materials and tiles with an external three layer honeycomb panel from YuIPM-1200 alloy have the best weight and strength characteristics. 6 Ref., 5 Tables, 9 Figures.
 
 
Keywords: returnable space vehicles, thermal protection tile structures, stress-strain state, carbon-carbon composite materials, high-temperature metal alloys
 
 
Received:               05.02.15
Published:               21.05.15
 
 
References
1. Gofin, M.Ya. (2003) Heat-resistant and thermal protection structures of shuttlecrafts. Moscow: Mir.
2. Koleda, V.V., Polozhaj, S.G., Potapov, A.M. et al. (2007) Thermal protection elements for shuttlecrafts. In: Proc. of 1st Int. Conf. on Advanced Space Technologies for Benefit of Mankind (18-20 April 2007, Dnepropetrovsk, Ukraine).
3. Tretiakov, Yu.D. Ceramics in the past, present and future. http://www.pereplet.ru
4. Krenkel, W. (2008) Ceramic matrix composites. Weinheim: Wiley-VCH. https://doi.org/10.1002/9783527622412
5. Glass, D.E., Capriotti, D.P., Reimer, T. et al. (2013) Testing of DLR C/C-SiC for HIFiRE & Scramjet Combustor. In: Proc. of 7th Europ. Workshop on Thermal Protection Systems and Hot Structures (8-10 April 2013, Noordwijk, The Netherlands).
6. Tikhy, V.G., Gusev, V.V., Potapov, A.M. et al. (2014) Prospective thermal protection structure of shuttlecrafts with metal load-carrying element. In: Transact. of N.E. Zhukovsky NAU on Problems of Design and Production of Flying Vehicles, 28-43. Kharkov: KhAI.
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