Parametric analysis of a hybrid power system for rotorcraft emergency landing sequence. (October 2017)

• Record Type: Journal Article
• Authors: Avanzini, G; Carlà, A; Donateo, T
• Is Part Of: Proceedings of the Institution of Mechanical Engineers. Volume 231:Number 12(2017:Dec.)
• Page Start: 2282
• Page End: 2294
• Publication Date: 2017-10
• Subjects: Hybrid rotorcraft -- hybrid powertrain -- helicopter safety -- electric powertrain design -- battery sizing; Aeronautics -- Periodicals; Astronautics -- Periodicals; Airplanes -- Design and construction -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1177/0954410017726810
• Languages: English
• ISSNs: 0954-4100

Abstract

The use of a hybrid powertrain for a conventional single main rotor helicopter is investigated, with the objective of assessing its feasibility and its potential impact on improving safety, especially for single-engine rotorcraft. The study is focused on the characteristics of the powertrain and required battery pack. It is based on a simple analysis of power required in forward flight and the estimate of the total energy required for a powered landing manoeuvre after thermal engine failure. Current technologies are considered as well as expected improvements, especially as far as energy density and power density of the battery are concerned. The latter analysis is based on current trends for battery and motors technologies, in order to determine the technological breakthrough limit.