Failure Mode Effect and Critically Analysis of Divert Attitude Control System of Launch Vehicle

Abstract

Divert and Attitude Control System (DACS) is a Liquid Propulsion based Control system, and it is used accurately for positioning the flight vehicle and its payload against disturbing forces. DACS is a very critical system and should have very high reliability. Constant adequate efforts must be made to predict the failures so that it can increase the safety of the system in the detailed design phase by using suitable reliability prediction tools. Failure Mode and Effect Analysis is the best technique to capture the design anomalies/risks systematically. The study of DACS subsystem has carried out with Failure Mode and Effects analysis in a qualitative manner by identifying failure modes followed by tabulating them. Further quantitative Criticality Analysis has carried out, and quantitative risk has been identified. The high-risk components were identified using FMECA, and the associated risk was brought down to an optimum level.