José María Rimada Carrasco

PhD Thesis

Design and optimisation methodology for hydrogen-powered aircraft development and environmental impact assessment

Supervisors

Andrea Cini (UC3M) & Marco Raiola (UC3M)

Abstract

An efficient powertrain/airframe integration is required to offset the weight and performance penalties caused by the technology lack of maturity. All the aircraft conceptual design and optimisation modules will be adapted to allow the H2-fuelled powertrain integration and the airliner performance and operational capability assessment. Structural weight will be computed by means of GFEM-based airframe sizing procedures owing to the lack of experience-based weight estimation correlation formulas for H2-fuelled airliner. Reduced Order Models (ROMs) will be generated from the FE sizing and implemented on the optimisation for fast and computational cost-effective weight estimations.

A tool, able to predict the acoustic footprint has to be integrated within the optimisation. Different models for propeller noise and aerodynamics with different degrees of fidelity will be identified and implemented. While simplest model can be based on semiempirical correlations, more refined implementations can rely on physically grounded low-fidelity models for the aerodynamics (e.g. Blade-Element Momentum Theory, Blade Vortex Theory) and aeroacoustics analogies (e.g. Ffowcs Williams-Hawkings Analogy) and derived models (e.g. Hanson’s method) for the noise. Blade-wake and wake-airframe interaction problems will be accounted in the modelling. The models will be then validated against high fidelity data, either proceeding form simulations or experiments where available. To this purpose high-fidelity propeller URANS/LES simulations in commercial CFD solvers which will serve as a baseline for the assessment of the developed models will be developed.

The optimisation platform will also allow airliner mission performance evaluation and operational capabilities review. Airworthiness requirements will drive the powertrain configuration sizing and selection in terms of engine inoperative conditions, fire protection and reliability. Operation capability prediction methods and strategies will be implemented to evaluate aircraft turnaround time, 24h flight capabilities, and the impact of ground handling on airport infrastructures and procedure. A conceptual design cost model will be developed as well to assess the economic viability of H2 powered short-range airliner. The environmental benefits of the novel H2 powered airliners will be quantified by Life Cycle Assessment (LCA) method, assessing the potential environmental impact of a product system during its entire life cycle.

Doctoral Meetings