H.E.R.O research

This study intends to identify and evaluate the reductions in fuel, carbon dioxide emissions, and operational costs that a specific hybrid power unit could provide in a typical small passenger aircraft, to be then scaled to bigger aircrafts (above 5 tons).
Researchers, professional pilots, and software experts engaged in the project to collect the following information:
The findings of this study will serve as the basis for further validations in practical applications.

Two engines, a Lycoming O-235 and the H.E.R.O. hybrid power unit, were compared during the analysis.

Interest in hybrid electric-thermal technology is sparked by two primary factors: the reduction of fuel consumption and emissions, and the need for a backup power source in single-engine aircraft for safety reasons.
Hybrid electric-thermal technologies are available and viable for addressing aviation industry obstacles.
Using two engines, the aircraft can use the electric engine during phases of high fuel consumption, such as takeoff and climb, and phases of noise reduction, such as landing near populated areas.
This technology was selected for the HERO power unit in order to provide the best alternative for passengers and freight aircrafts over the next decade and beyond.

All hybrid electric-thermal engines are parallel systems with low costs and simple production processes, but they are significantly larger than the series engine and permit fewer component modifications to optimize hybrid retrofit systems.
The HERO project will create a system of in-series power units with huge advantages for energy optimization and flying performances.

The specifications for the Lycoming O-235, a common engine in small and medium aircrafts, can be found at this link.
While H.E.R.O. is a series hybrid power unit, it is made of a thermal engine, an electric generator, a dedicated power management software, and other key components that are now under NDA protection.
Horizon funds will be used to test and develop the H.E.R.O. power unit.

In this study, the following hypotheses have been made:

• The flight in exam is split into the following phases: takeoff: 5 minutes; landing: 5 minutes; climb: 5 minutes; cruise: 45 minutes. 
• Regarding the cost of fuel we have accounted for 2,31 €/Lt, while the cost of electricity is fixed at 0.24 €/Kw h and we considered a cost of 60 €/L . These parameters are informative due to their periodic variations.
• The Lycoming power settings have been taken from the official engine manual which suggest the following: take-off and climbs power setting 100%, 43.18 L/h, output power 85,7Kw; cruise power setting 65%, 22.30 L/h, output power 55,74 Kw; landing power setting 5%, output power 4,3Kw, 2,4 L/h.
• The H.E.R.O. power settings are the following: take off and climbs power setting 100%, 20l/h output power 90Kw; cruise power setting 55% & 60%, 11 L/h & 12 L/h, output power 49.5 & 54 Kw; landing and idling power setting 5%, output power 4,5Kw, 0,78 L/h.
• The propulsion battery considered has capacity of 15Kwh.
• Electric engine power 85.7 Kwh.
• The H.E.R.O. thermal engine has a weight of 65Kg while the Lycoming O-235 L weights 112Kg.