Author : P. Mahesh Babu, G. Bala Krishna and B Siva Prasad

In rocketry the designing of casing & hardware plays a vital role which is the replication of pressure vessel design. The temperatures induced inside the casing are of the order of 1000oC to 3000oC. The final temperature experienced by the casing at it’s external surface (after insulation) is 100oC .To withstand these high temperatures some ablative liners are provided inside the casing. In this paper, structural analysis for the ablative layers materials Maraging Steel, A-286 Iron based alloy, D6AC Steel, Haynes 255 was done. Further, thermal analysis has been carried out with ANSYS for the material which had been selected after structural analysis. Modeling was done by AUTOCAD. The design of rocket Motor Casing is done using ASME section VIII methods for the given input parameters. The structural & the stresses and FOS are arrived from analysis and compared with design values.

Keywords: Solid Rocket motor, Casing, D6AC, Maraging Steel, Haynes 255, ANSYS, Thermo structural Analysis, Ablative liners

Article published in International Journal of Current Engineering and Technology, Vol.5, No.3 (June-2015)