Light Weight Propulsion System Development for UAVS

Abstract

UAV has established itself as one of the major force multipliers for many applications of various armies throughout the world. These UAVs employ different kinds of machines as propulsion systems. Both the Reciprocating and Rotary engines are the leading contenders amongst these machines. Performance parameters like power to weight ratio, specific fuel consumption and the limited number of requirement of UAV engines call for a development methodology very specific to these engines. Related aspects of development methodology and proving of a modular series of single, twin and four cylinder two-stroke engines indigenously developed for UAV are reported in the paper. Technologies so developed for said series of UAV engines are presented in this paper. Endurance tests as well as limited trials conducted with airframe are also included. Grey areas as foreseen in the indigenous development technologies of rotary engines have been brought out.