– The purpose of this paper is to explore some of the challenges associated with the integration of an LH2-fuelled advanced hybrid-electric distributed propulsion system with the airframe. The airframe chosen as a case study is an ultra-high-capacity blended wing body configuration. It is designed to represent an A-380 class vehicle but in the 2025-2030 timeframe. The distributed propulsion system is a hybrid-electric concept that utilizes high-temperature superconducting technologies. The focus of the study is the application of LH2 as a fuel, with comment being given to kerosene and LCH4.
– The study consists of a conceptual design developed through the preliminary design phase and part way into the detailed design phase.
– The relationship between passenger capacity and fuel capacity is developed. Some remaining challenges are identified.
– The study supports further conceptual design studies and more detailed system studies.
– The study contributes to the development of more environmentally benign aviation technologies. The study may assist the development of solutions to the peak oil challenge.
– The study explores the integration of a number of complex systems into an advanced airframe to an unusual depth of engineering detail.
Airframe integration for an LH2 hybrid-electric propulsion system
Aircraft Engineering and Aerospace Technology: An International Journal ; 86 , 6 ; 562-567
2014-09-30
6 pages
Article (Journal)
Electronic Resource
English
Airframe integration for an LH2 hybrid-electric propulsion system
Online Contents | 2014
|Propulsion airframe integration
NTRS | 1975
|Propulsion Airframe Integration Overview
NTRS | 2001
Transonic Airframe Propulsion Integration
NTIS | 1992
|Transonic airframe propulsion integration
NTRS | 1992
|