Latest revision as of 10:56, 3 December 2019

Published in Computational Methods and Models for Transport. Computational Methods in Applied Sciences, Diez, P., Neittaanmäki, P., Periaux, J., Tuovinen, T., Bräysy, O., (Eds.) Vol. 45, pp. 147-167, Springer, Cham, 2018
DOI: 10.1007/978-3-319-54490-8_10

Abstract

Aircraft emission targets worldwide and their climatic effects have put pressure in government agencies, aircraft manufacturers and airlines to reduce water vapour, carbon dioxide (${\displaystyle CO_{2}}$) and oxides of nitrogen (${\displaystyle NO_{x}}$) resulting from aircraft emissions. The difficulty of reducing emissions including water vapor, carbon dioxide (${\displaystyle CO_{2}}$) and oxides of nitrogen (${\displaystyle NO_{x}}$) is mainly due to the fact that a commercial aircraft is usually designed for a particular optimal cruise altitude but may be requested or required to operate and deviate at different altitudes and speeds to archive a desired or commanded flight plan, resulting in increased emissions. This is a multi- disciplinary problem with multiple trade-offs such as optimizing engine efficiency, minimizing fuel burnt and emissions while maintaining prescribed aircraft trajectories, altitude profiles and air safety. There are possible attempts to solve such problems by designing new wing/aircraft shape, new efficient engine, ATM technology, or modifying the aircraft flight plan. Based on the rough data provided by an air carrier company, who was willing to assess the methodology, this paper will present the coupling of an advanced optimization technique with mathematical models and algorithms for aircraft emission, and fuel burnt reduction through flight plan optimization. Two different approaches are presented; the first one describes a deterministic optimization of the flight plan and altitude profile in order to reduce the fuel consumption while reducing time and distance. The second approach presents the robust design optimization of the previous case considering uncertainties on several parameters. Numerical results will show that the methods are able to capture a set of useful trade-offs solutions between aircraft range and fuel consumption, as well as fuel consumption and flight time.