Initial weight estimation of twin-fuselage configuration in aircraft conceptual design
Initial weight estimation of twin-fuselage configuration in aircraft conceptual design
The Ultra-High Aspect Ratio Wing (UHARW) concept can improve the aircraft’s aerodynamic efficiency and reduce fuel consumption. The Twin-Fuselage (TF) configuration is one of the promising concepts for the UHARW design to reduce the wing bending moments and shear forces. This paper presents the development of a semi-empirical method for the weight estimation of TF aircraft in the initial sizing stage. A physics-based wing weight estimation method is improved for higher fidelity aerodynamic analysis and modified for composite material structures of TF aircraft. This method is used in the design of experiments and the results are applied for regression analysis to establish a semi-empirical method. Eventually, the established semi-empirical weight estimation method is integrated into a TF aircraft conceptual design and performance analysis framework. A mid-range TF aircraft and a long-range TF aircraft are designed and sized to illustrate its application and efficiency in rapidly estimating the TF aircraft weight breakdown.
aircraft conceptual design, composite materials, initial weight estimation, Twin-fuselage configuration, vortex lattice method
130-140
Ma, Yiyuan
b0523048-df03-4269-af67-8fd7ef9780a8
Yan, Jin
4a13d956-d215-43ed-9f73-3f2cc73a8829
Elham, Ali
676043c6-547a-4081-8521-1567885ad41a
January 2023
Ma, Yiyuan
b0523048-df03-4269-af67-8fd7ef9780a8
Yan, Jin
4a13d956-d215-43ed-9f73-3f2cc73a8829
Elham, Ali
676043c6-547a-4081-8521-1567885ad41a
Ma, Yiyuan, Yan, Jin and Elham, Ali
(2023)
Initial weight estimation of twin-fuselage configuration in aircraft conceptual design.
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 237 (1), .
(doi:10.1177/09544100221095370).
Abstract
The Ultra-High Aspect Ratio Wing (UHARW) concept can improve the aircraft’s aerodynamic efficiency and reduce fuel consumption. The Twin-Fuselage (TF) configuration is one of the promising concepts for the UHARW design to reduce the wing bending moments and shear forces. This paper presents the development of a semi-empirical method for the weight estimation of TF aircraft in the initial sizing stage. A physics-based wing weight estimation method is improved for higher fidelity aerodynamic analysis and modified for composite material structures of TF aircraft. This method is used in the design of experiments and the results are applied for regression analysis to establish a semi-empirical method. Eventually, the established semi-empirical weight estimation method is integrated into a TF aircraft conceptual design and performance analysis framework. A mid-range TF aircraft and a long-range TF aircraft are designed and sized to illustrate its application and efficiency in rapidly estimating the TF aircraft weight breakdown.
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09544100221095370
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Accepted/In Press date: 31 March 2022
e-pub ahead of print date: 6 May 2022
Published date: January 2023
Additional Information:
Funding Information:
The author(s) disclosed receipt of the following financial support for the research, authorship, and/or publication of this article: This project has received funding from the Clean Sky 2 Joint Undertaking (JU) under grant agreement No 883670. The JU receives support from the European Union’s Horizon 2020 research and innovation programme and the Clean Sky 2 JU members other than the Union.
Publisher Copyright:
© IMechE 2022.
Keywords:
aircraft conceptual design, composite materials, initial weight estimation, Twin-fuselage configuration, vortex lattice method
Identifiers
Local EPrints ID: 468867
URI: http://eprints.soton.ac.uk/id/eprint/468867
ISSN: 0954-4100
PURE UUID: c0698c47-d3c7-4912-b0a8-cfb5750f828d
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Date deposited: 30 Aug 2022 16:58
Last modified: 17 Mar 2024 13:04
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Author:
Yiyuan Ma
Author:
Jin Yan
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