<?xml version="1.0" encoding="UTF-8"?> <article key="pdf/9998025" mdate="2014-03-01 00:00:00"> <author>Olga V. Korotkaya</author> <title>Substructure Method for ThermalStress Analysis of LiquidPropellant Rocket Engine Combustion Chamber</title> <pages>739 - 742</pages> <year>2014</year> <volume>8</volume> <number>4</number> <journal>International Journal of Aerospace and Mechanical Engineering</journal> <ee>https://publications.waset.org/9998025.pdf</ee> <url>https://publications.waset.org/vol/88</url> <publisher>World Academy of Science, Engineering and Technology</publisher> <abstract>This article is devoted to an important problem of calculation of deflected mode of the combustion chamber and the nozzle end of a new liquidpropellant rocket cruise engine. A special attention is given to the methodology of calculation. Three operating modes are considered. The analysis has been conducted in ANSYS software. The methods of conducted research are mathematical modeling, substructure method, cyclic symmetry, finite element method. The calculation has been carried out to order of S.P. Korolev Rocket and Space Corporation &amp;amp;laquo;Energia&amp;amp;raquo;. The main results are practical. Proposed methodology and created models would be able to use for a wide range of strength problems. </abstract> <index>Open Science Index 88, 2014</index> </article>