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

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 propellerpowered,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, transmissionefficiency, 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 programin 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 drivesystem 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 willbe used where light weight, heavy fuel alternatives are needed for aero, marine, business, or home applications.