Optimization of Compression Moulding Process Parameters to Enhance the Performance of Solid Rocket Nozzle Convergent Liners Using Taguchis Robust Design Methodology

Abstract

The ablative liners are used to protect the nozzle structural members from the severe thermal environment in solid rocket nozzles. The ablative liners are made with carbon phenolic prepreg flakes by compression moulding process. The objective of this work is to demonstrate the optimization of process parameters of compression moulding process to achieve better erosion resistance using Taguchi's robust design methodology. In this method four control factors Pressure applied, Charge Temperature, Tool Pre heat Temperature, Number of charges, were investigated for the compression moulding process. The presented work was to study the cogency and acceptability of Taguchi's methodology in manufacturing of ablative liners. The quality characteristic identified was erosion rate. Experiments carried out using L9 Orthogonal array with four different levels of control factors. The test results were analyzed using smaller the better criteria for S/N ratio in order to optimize the process. The experimental results were analyzed conformed and successfully used to achieve the minimum erosion rate of the ablative liners. The enhancement in performance of the ablative liners were observed by carrying out the oxy acetylene tests. The influence of erosion rate on the performance of ablative liners was verified by ground firing test.