The goal of this project is to develop a design of a glider configuration which when mounted on the torpedo can assist it to glide. The specified objective is to achieve a minimum range of 25 Km in a maximum duration of 250 sec when the whole assembly is launched from an altitude of 6 Km with a circular error probability of 500m. This study posed interesting problems in terms of high wing loading and development of compact mechanisms owing to the space constraints. Mechanisms are required to set the wing and tail in positions after launch, which otherwise are aligned with the torpedo and folded respectively, so that the system can fit in the bomb bay. Indigenous mechanisms are proposed to meet the requirements. Wing loading is very high resulting from the heavy weight of torpedo and geometrical constraints on design of wing. The assembly after launch has to be controlled with the help of an on-board autopilot using integrated GPS-INS so as to accommodate it in the flight envelop provided by NSTL, Visakhapatnam. Apart from glider design, this project involves evaluation of stability of the entire system during flight, trajectory simulation and performance against atmospheric disturbances.The mechanisms are developed using Autodesk Inventor software and the stress analysis on them for different loads is also carried out using the same software.