Thermo-Structure of Dual-Bell Nozzle

Abstract

A thermo-structural analysis was performed on a nozzle throat insert composed of a 3D carbon carbon ablative coating on 4D carbon carbon substrate. The analysis considered an environment produced by a solid rocket propellant at a chamber pressure of 1000 psi for duration of sixty seconds. The analysis showed the effect on the thermo-structural predictions and of the sensitivity of the stresses on the backside constraint, a dual-bell nozzle is considered to be feasible devices to improve performance of booster engines for near future reusable launch vehicles. Hot firing tests were conducted at a high altitude test stand. The objective of this paper is to establish the thermal stability and structural integrity of the nozzle. The combustion gas flow was sonic, supersonic, & hypersonic respectively, in the inlet, throat, and exit sections of the nozzle. The exit plane Mach number was 5.021. Thermal analysis by APDL Code and structural analysis by ANSYS. The recession life of thermal layer was 60 sec for 100 load steps. Stress analysis of the nozzle due to aerodynamic pressure and temperature resulted in low strains and presents no concern

Existing System

Proposed System

Architecture

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