SBIR-STTR Award

The proposed program will evaluate and compare different drive concepts, and will deliver a preliminary design of the most attractive concept for achieving the high speed reduction ratio required by small UAV turbine engines appropriate for UAV propeller powered,or rotor driven aircraft. Several conventional inline and offset gearbox concepts will be assessed along with unconventional traction, harmonic, and cycloidal drive concepts. The concepts will be compared based on size, weight, transmission efficiency, cost, and predicted reliability. A 25 to 1 gear ratio, efficiency of 98% and input shaft speed of 105,000 rpm will be addressed in this program. A refined preliminary design will be completed, and will provide the basis for a Phase II program in which the drive concept will be detailed, fabricated and tested. This Phase I program will provide the Army with a complete preliminary design of a high reduction ratio drive system suitable for small UAV engines. In Phase II a prototype of this drive system will be built and tested. With the growing interest in UAV aircraft this drive system along with small turbine engines should find numerous applications in the Army and other DOD organizations. In the civilian marketplace, this drive system will be used where light weight, heavy fuel alternatives are needed for aero, marine, business, or home applications.

Keywords:
Uav, Gearboxes, Transmissions, Microturbines, Uav Propulsion

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 proposed program 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 with a 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 & more compact, 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

Keywords:
UAV, GEARBOXES, TRANSMISSIONS, MICROTURBINES, UAV PROPULSION