Design Methodology and Mission Assessment of Parallel Hybrid Electric Propulsion Systems

Abstract An integrated engine cycle design methodology and mission assessment for parallel hybrid electric propulsion architectures are presented in this paper. The aircraft case study considered is inspired by Fokker 100, boosted an motor on the low-pressure shaft of gas turbine. fuel burn benefits arising from boosting discussed two different baseline technologies. A three-point method developed to redesign according degree hybridization. power management optimization employed identify potential hybridization multiple ranges. sensitivity these results has also been analyzed assumptions powertrain. With 1 MW a battery pack 2307 kg, 3% benefit can be obtained retrofitting turbine 400 nm range. Optimizing strategy improves 0.2-0.3%. Redesigning optimizing strategy, provides 4.2% nm. suggest that high power, low energy, ranges below 700 only cases where redesigned energy consumption relative aircraft. Finally, it found percentage configuration increases with improvement technology.