Mission optimisation for a conceptual coaxial rotorcraft for taxi applications

Simple item page
dc.contributor.authorEnconniere, Julien
dc.contributor.authorOrtiz-Carretero, Jesús
dc.contributor.authorPachidis, Vassilios
dc.date.accessioned2018-01-09T11:50:26Z
dc.date.available2018-01-09T11:50:26Z
dc.date.issued2017-10-31
dc.description.abstractThis paper presents the development and an application of a multidisciplinary methodology for the preliminary design assessment of compound coaxial rotorcraft with a counter-rotating rotor system and a rear-mounted propeller. A comprehensive optimisation strategy is deployed to evaluate the environmental and operational benefits of the aforementioned rotorcraft architecture. The code is validated against experimental data prior to the application of the methodology to the evaluation of a conceptual vehicle for intercity taxi applications. Response Surface Models (RSMs) are generated to mimic the rotorcraft performance in order to accelerate the optimisation process. The effects of the defined mission input parameters such as cruise speed, altitude, climb rate or mission length are evaluated. Pareto fronts for fuel burn, NOx emissions and mission duration are obtained. The method was applied to a hypothetical scenario of mission length ranging from 50 to 300 km. Best estimate mission scenario are selected from the Pareto fronts, providing on average 23%, 20%, and 13% simultaneous reductions in mission duration, fuel burn, and NOx emissions when compared to a conventional flight procedure. The picked scenarios coincide with the fuel optimised mission scenarios for each mission length, thus the multi-disciplinary environment was not required. Besides, an “improved” mission procedure is outlined, defining the mission characteristics independently of the mission's length. This procedure yields on average 22%, 14%, and 8% reductions in mission duration, fuel burn, and NOx emissions, respectively.en_UK
dc.identifier.citationEnconniere J, Ortiz-Carretero J, Pachidis V. (2018) Mission optimisation for a conceptual coaxial rotorcraft for taxi applications. Aerospace Science and Technology, Volume 72, January 2018, pp. 14-24en_UK
dc.identifier.cris18939509
dc.identifier.issn1270-9638
dc.identifier.urihttps://doi.org/10.1016/j.ast.2017.10.031
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/12865
dc.language.isoenen_UK
dc.publisherElsevieren_UK
dc.rightsAttribution-NonCommercial-NoDerivatives 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc-nd/4.0/*
dc.subjectCompound rotorcraften_UK
dc.subjectCoaxial rotoren_UK
dc.subjectPerformance simulationen_UK
dc.subjectMission analysisen_UK
dc.subjectGaseous emissionsen_UK
dc.subjectOptimisationen_UK
dc.titleMission optimisation for a conceptual coaxial rotorcraft for taxi applicationsen_UK
dc.typeArticleen_UK

Files

Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
mission_optimisation_for_a_conceptual_coaxial_rotorcraft-2017 (1).pdf
Size:
3.8 MB
Format:
Adobe Portable Document Format
Description:
Download
License bundle
Now showing 1 - 1 of 1
No Thumbnail Available
Name:
license.txt
Size:
1.63 KB
Format:
Item-specific license agreed upon to submission
Description:
Download

Collections

Staff publications (SATM)