Abstract
This paper discusses the selection, integration, and testing of five components for a parallel hybrid-electric (HE) propulsion system for a small remotely-piloted aircraft (RPA). The components include an internal combustion engine (ICE), electromagnetic clutch, an electric motor (EM), battery pack, and a propeller. Due to the number of nonlinear, interacting devices in the HE propulsion system (HE-PS), an optimization tool was developed to size the devices to assist in the selection of commercial off-the-shelf (COTS) components. The RPA’s required power and velocity for the endurance mission segment drive the EM design which must be matched with a commercial off-the-shelf (COTS) propeller for maximum efficiency. A performance map for a small ICE was derived correlating torque, engine speed, and fuel consumption. The ICE and EM performance maps were used as lookup tables in a C-based controller that was developed to maximize the efficiency of the HE propulsion system. Based on user input and data from sensors monitoring engine and motor operation, the controller manages the HE power-plant to optimize the mission performance of the RPA. Components for the HE-PS were successfully selected, matched and tested. A COTS Honda ICE and Maxon EM were selected as best suited for incorporation into the HE-PS. Configuring and dynamometer testing these selected HE-PS components showed they satisfy mission performance requirements.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call