Analysis of Thermal Protection System in Flex Seal of a Rocket Motor
Charitha Krishna P1, Balakrishna Murthy V2, Chandra Mohan R3
1Charitha Krishna P, Assistant Professor, Department of Mechanical Engineering, SVIET, Nandamuru, Andhra Pradesh, India
2Balakrishna Murthy V, Professor, Department of Mechanical Engineering, VRSEC, Vijayawada, Andhra Pradesh, India.
3Chandra Mohan R, Chairman, Resins & Allied Products, Nidamanuru, Vijayawada, Andhra Pradesh, India..
Manuscript received on October 16, 2019. | Revised Manuscript received on 26 October, 2019. | Manuscript published on November 10, 2019. | PP: 4933-4936 | Volume-9 Issue-1, November 2019. | Retrieval Number: A8117119119/2019©BEIESP | DOI: 10.35940/ijitee.A8117.119119
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: A Thermal protection system is used to protect the rocket from the heat generated by the hot gases. A thermal boot is used as the thermal protection system at the outside of the nozzle to protect the flex seal. The objective of the present work is to design the thermal protection system for flex seal using different composite materials for single time of flight and to study the ablation of the materials. The problem is modelled using commercial ANSYS software. 3-D Axi-symmetric transient thermal analysis is performed for the flex seal along with thermal protection system made of composite materials. The initial and boundary conditions are applied to meet the industrial requirement. From this analysis, thermal protection system made of different composite materials is studied and one is suggested based on ablation and weight reduction.
Keywords: FEM, Flex Seal, Thermal Protection System, Axi-Symmetry
Scope of the Article: Thermal Engineering