Mission optimisation for a conceptual coaxial rotorcraft for taxi applications.
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| Title: | Mission optimisation for a conceptual coaxial rotorcraft for taxi applications. |
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| Authors: | Enconniere, J.1 j.p.enconniere@cranfield.ac.uk, Ortiz-Carretero, J.1, Pachidis, V.1 |
| Source: | Aerospace Science & Technology. Jan2018, Vol. 72, p14-24. 11p. |
| Subjects: | Rotorcraft, Propeller-driven aircraft, Helicopter rotor aerodynamics, Rotors (Helicopters), Interdisciplinary research, Vehicle design & construction |
| Abstract: | This 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, N O x 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 N O x 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 N O x emissions, respectively. [ABSTRACT FROM AUTHOR] |
| Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
| FullText | Text: Availability: 0 |
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| Header | DbId: egs DbLabel: Engineering Source An: 126898214 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
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| Items | – Name: Title Label: Title Group: Ti Data: Mission optimisation for a conceptual coaxial rotorcraft for taxi applications. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Enconniere%2C+J%2E%22">Enconniere, J.</searchLink><relatesTo>1</relatesTo><i> j.p.enconniere@cranfield.ac.uk</i><br /><searchLink fieldCode="AR" term="%22Ortiz-Carretero%2C+J%2E%22">Ortiz-Carretero, J.</searchLink><relatesTo>1</relatesTo><br /><searchLink fieldCode="AR" term="%22Pachidis%2C+V%2E%22">Pachidis, V.</searchLink><relatesTo>1</relatesTo> – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Aerospace+Science+%26+Technology%22">Aerospace Science & Technology</searchLink>. Jan2018, Vol. 72, p14-24. 11p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Rotorcraft%22">Rotorcraft</searchLink><br /><searchLink fieldCode="DE" term="%22Propeller-driven+aircraft%22">Propeller-driven aircraft</searchLink><br /><searchLink fieldCode="DE" term="%22Helicopter+rotor+aerodynamics%22">Helicopter rotor aerodynamics</searchLink><br /><searchLink fieldCode="DE" term="%22Rotors+%28Helicopters%29%22">Rotors (Helicopters)</searchLink><br /><searchLink fieldCode="DE" term="%22Interdisciplinary+research%22">Interdisciplinary research</searchLink><br /><searchLink fieldCode="DE" term="%22Vehicle+design+%26+construction%22">Vehicle design & construction</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: This 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, N O x 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 N O x 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 N O x emissions, respectively. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1016/j.ast.2017.10.031 Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 11 StartPage: 14 Subjects: – SubjectFull: Rotorcraft Type: general – SubjectFull: Propeller-driven aircraft Type: general – SubjectFull: Helicopter rotor aerodynamics Type: general – SubjectFull: Rotors (Helicopters) Type: general – SubjectFull: Interdisciplinary research Type: general – SubjectFull: Vehicle design & construction Type: general Titles: – TitleFull: Mission optimisation for a conceptual coaxial rotorcraft for taxi applications. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Enconniere, J. – PersonEntity: Name: NameFull: Ortiz-Carretero, J. – PersonEntity: Name: NameFull: Pachidis, V. IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 01 Text: Jan2018 Type: published Y: 2018 Identifiers: – Type: issn-print Value: 12709638 Numbering: – Type: volume Value: 72 Titles: – TitleFull: Aerospace Science & Technology Type: main |
| ResultId | 1 |
