High Reduction Ratio Drive System for Small Unmanned Aerial Vehicle (UAV)

Advanced military UAV vehicles can benefit from compact, lightweight, quiet turbine engines that operate on heavy fuels. A critical requirement in utilizing these engines is an efficient, lightweight, high reduction ratio drive system. The proposedprogram will provide the detailed design of two attractive concepts that will be fabricated and ground tested with a 70 hp class small turbine engine to assess performance and limited endurance.This Phase II drive system program will provide the Army witha high reduction ratio, geared small turbine engine system in the under 100 hp power class that is powered by heavy fuel. When compared to current gas fueled reciprocating piston engine, this turbine system will be: easier to start, lighter & morecompact, lower noise & vibration, have lower parts count, and use fuel that is readily available on the battlefield. In the civilian marketplace, this geared engine system will be used where lightweight, heavy fuel alternates are needed for ground power,aero and marine propulsive applications.