Implementation of a Rule-Based Open-Loop Control Strategy for a Hybrid-Electric Propulsions System on a Small RPA

Currently-fielded small electric-powered remotely-piloted aircraft (RPA) lack endurance desired by warfighters, and internal combustion engine (ICE) RPAs generate undesirable acoustic and thermal signatures. Hybrid-electric (HE) propulsion systems would use ICE power for cruise, electric power for endurance, and combine both electric power and ICE power for takeoff, climbing, and recharging onboard battery packs. Use of HE systems would eliminate undesirable signatures in addition to providing considerable fuel savings over time. Various combinations of six components were used in this HE system: the ICE, electric motor (EM), electromagnetic clutch, a one-way bearing, battery pack, and a propeller. Control of such a system in a small RPA has never been attempted before. A rule-based controller was developed in C code to manage this HE system. This system and its various sensors were analyzed on a custom-built dynamometer test stand that was developed in conjunction with other students. LabView screens were developed to aid this testing and interface with the sensor suite. The controller’s performance over 9 distinct operating modes, including 4 operational flying states, were validated to provide the most optimal operation of a HE-RPA system of about 13.6 kg (30.0

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