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The Application of Cyclic Symmetry and the Substructure Method in the Thermal Stress Analysis of the Combustion Chamber of the Liquid-Propellant Rocket Engine with LOX Cooling
| Authors: Korotkaya O.V., Gavryushin S.S. | Published: 20.01.2016 |
| Published in issue: #1(670)/2016 | |
| Category: Technology and Process Machines | |
| Keywords: mathematical modeling, finite element method, substructure, cyclic symmetry, stress-strain state, nozzle, combustion chamber, liquid-propellant rocket engine, cooling channels, LOX-cooling |
