TY - CHAP
T1 - Design and Feasibility of Electrical Version of Search-and-Rescue Helicopter Based on Eurocopter
AU - Bolvashenkov, Igor
AU - Kammermann, Jörg
AU - Rubinraut, Alexander
AU - Herzog, Hans Georg
AU - Frenkel, Ilia
N1 - Publisher Copyright:
© 2022, The Author(s), under exclusive license to Springer Nature Switzerland AG.
PY - 2022
Y1 - 2022
N2 - Currently, the developers of various companies in accordance with the program more electric aircraft (MEA) consider the electrification of aircraft of different types and purposes, such as the airplanes as well as the helicopters, as one of the most promising directions in the development of aviation technology. The chapter is concerned with the investigation of the actual feasibility and prospects of creating an innovative type of electrical helicopter’s propulsion system based on battery electric storage fuel cell electric energy source, ultracapacitors, and a superconducting electric motor for the conventional airbus helicopter EC135 with two gas turbine engines and a speed reducer. The chapter discusses the advantages and technological problems, which are associated with the thoroughgoing transformation of the conventional propulsion system of helicopter with two turbine engines to the novel non-conventional traction drive topologies. The feasibility evaluation of helicopter's electric propulsion is provided based on comprehensive analysis, its weight, volume, efficiency, and reliability features. The feasibility of the realization of the electric version of the helicopter's propulsion system depends entirely on the optimal selection and placement of each component of the traction drive.
AB - Currently, the developers of various companies in accordance with the program more electric aircraft (MEA) consider the electrification of aircraft of different types and purposes, such as the airplanes as well as the helicopters, as one of the most promising directions in the development of aviation technology. The chapter is concerned with the investigation of the actual feasibility and prospects of creating an innovative type of electrical helicopter’s propulsion system based on battery electric storage fuel cell electric energy source, ultracapacitors, and a superconducting electric motor for the conventional airbus helicopter EC135 with two gas turbine engines and a speed reducer. The chapter discusses the advantages and technological problems, which are associated with the thoroughgoing transformation of the conventional propulsion system of helicopter with two turbine engines to the novel non-conventional traction drive topologies. The feasibility evaluation of helicopter's electric propulsion is provided based on comprehensive analysis, its weight, volume, efficiency, and reliability features. The feasibility of the realization of the electric version of the helicopter's propulsion system depends entirely on the optimal selection and placement of each component of the traction drive.
KW - Electrical helicopter
KW - Fault tolerance
KW - Multi-state system Markov model
KW - Multilevel inverter
KW - Reliability
KW - Traction multi-phase motor
UR - http://www.scopus.com/inward/record.url?scp=85115441317&partnerID=8YFLogxK
U2 - 10.1007/978-3-030-81740-4_3
DO - 10.1007/978-3-030-81740-4_3
M3 - Chapter
AN - SCOPUS:85115441317
T3 - SpringerBriefs in Applied Sciences and Technology
SP - 41
EP - 61
BT - SpringerBriefs in Applied Sciences and Technology
PB - Springer Science and Business Media Deutschland GmbH
ER -