Design of Nozzle and Fin Locking Unit for MRECM Rocket: A Study

Abstract

In view of the current strategic defense scenario of the world, specifically Asia, it is necessary to use modern security systems in air, land and water. One of the solutions is to have air security blanket or dome in the form of decoy missiles to intercept incoming enemy missiles. The current work was undertaken after the testing and analysis of the multi- nozzle stabilizer unit. A design for a single nozzle unit for the same rocket is now required. This paper covers the first half of a year- long effort which involves conceptualization and the initial design of the nozzle and stabilizing mechanism. Single nozzle design replaces seven-nozzle system in MRECM rocket, reducing weight and complexity. Convergent-divergent nozzle design with neutral burning grain provides required impulse for stable flight. From initial design of nozzle it can be concluded that it is feasible to replace multiple nozzle propulsion system with a single nozzle propulsion system for the required impulse which helps in keeping the skin friction losses to a minimum as skin contact area reduces.