This proposal outlines the design and development of a uniflow two stroke Aero-Diesel engine core in response to the NASA SBIR solicitation for a general aviation aircraft propulsion system. The proposed engine will offer increased power density, simplified operation, reduced emissions, noise, and vibration, while enhancing reliability and safety when compared to currently available general aviation aircraft engines. Important innovations are:* Reciprocating, uniflow sleeve valve to control intake and exhaust ports. * Hypocycloidal crank design that reduces engine size, weight and vibration. * Electronic fuel injection/engine management system. * Governor controlled single lever variable pitch integration system. These innovations are aimed at the NASA supplied objectives "to improve performance, safety and reliability, simplify operations, reduce maintenance and costs, and improve environmental compatibility." and address the limitations with current general aviation powerplants.Potential commercial applications of the proposed work are: 1) UAV/RPV propulsion capable of running on heavy fuel, 2) small marine engines for military, commercial, and recreational markets, 3) auxiliary power units (generators) and portable fire pumps, and 4) advanced, clean burning, two stroke diesel engines for automotive and motorcycle markets.hypocycloidal, sleeve valve, uniflow, diesel, two cycle, synergism, lightweight, compound
