Airframe integration for an LH2 hybrid-electric propulsion system

Abstract

Purpose

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.

Design/methodology/approach

The study consists of a conceptual design developed through the preliminary design phase and part way into the detailed design phase.

Findings

The relationship between passenger capacity and fuel capacity is developed. Some remaining challenges are identified.

Practical implications

The study supports further conceptual design studies and more detailed system studies.

Social implications

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.

Originality/value

The study explores the integration of a number of complex systems into an advanced airframe to an unusual depth of engineering detail.

Citation

Smith, H. (2014), "Airframe integration for an LH2 hybrid-electric propulsion system", Aircraft Engineering and Aerospace Technology, Vol. 86 No. 6, pp. 562-567. https://doi.org/10.1108/AEAT-04-2014-0045