Evaluation of Mechanical Properties and Material Modelling for a Rocket Thrust Chamber

Author(s):

Reeba Jacob , Mar Baselios College of Engineering; A.K. Asraff, SDAG/LPSC/ISRO,Trivandrum ; Jean Molly Simon, Mar Baselios College of Engineering Trivandrum; Krishnajith Jayamani, SDAG/LPSC/ISRO Trivandrum

Keywords:

ANSYS, Semi-Cryo, Thrust Chamber, UTM, Stress Analysis

Abstract:

High thrust rocket engines are employed in satellite launch vehicles delivering heavy satellites and space-crafts. The thrust chamber of such engines are generally of double walled construction in which the inner wall is of a high conductivity high ductility material like a copper alloy and outer wall of stainless steel. During engine operation, the chamber will be subjected to thermal and pressure loads. Due to severe thermal and pressure loads, inner wall operates in the elasto-plastic condition. Repeated operation of the engine will thus cause cyclic plastic deformations inducing low cycle fatigue. The thrust chamber investigated is of double walled construction in which four metallic materials are used at different zones: three stainless steels (designated as 12X21H5T, 12X18H10T and 06X15H10T respectively which have varying strength properties) and a high conductivity copper alloy which contains traces of Chromium, Zirconium and Titanium. A material characterization program is initiated to evaluate the monotonic tensile properties of the above materials at room temperature, in a Universal Testing Machine. This paper presents the constitutive modeling of the above materials followed by finite element modelling and thermo structural analysis of the thrust chamber.

Other Details:

Manuscript Id	:	IJSTEV3I2101
Published in	:	Volume : 3, Issue : 2
Publication Date	:	01/09/2016
Page(s)	:	341-345

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