Thermal Stress Analysis for Carbon/Carbon Material Throat Lining Based on Finite Element Analysis

Abstract

As a key part of the solid rocket motor, the nozzle always withstands a series of problems such as high-temperature, high-pressure, and chemical erosion and faces more severer environmental challenges. So its Stability plays a vital role in the normal operation of the engine. This paper takes the engine nozzle throat lining as the research object, uses the ANSYS to establish a carbon/carbon composite throat lining model in the ACP module, and analyzes the stress and displacement of the throat lining in a high-temperature and high-pressure environment. The experimental results show that under the high-temperature condition of 3500°C, the maximum stress value is 2734.8MPa, and more than 96% of the area is below 1000MPa, lower than the prescribed stress threshold. The superiority in the performance of the throat lining prepared for carbon/carbon materials is verified, and the structural integrity of the throat lining can still be guaranteed under high-temperature conditions.