Multidisciplinary Design Optimization of Twin-Fuselage Aircraft with Boundary-Layer-Ingesting Distributed Propulsion

Ma, Yiyuan; Zhang, Wei; Elham, Ali

doi:10.2514/1.c036559

Cited by 10 publications

(3 citation statements)

References 36 publications

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“…Further details on the multidisciplinary design activities of this demonstrator are available in refs. [187,188]. The tandem lifting architecture consists of two wings staggered both vertically and horizontally and provides advantages in terms of aerodynamics, i.e., more lift generated compared to an equivalent monoplane and stall stability.…”

Section: Experimental Assessment: Scaled Demonstratorsmentioning

confidence: 99%

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A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

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The aim of this review paper is to collect and discuss the most relevant and updated contributions in the literature regarding studies on new or non-conventional technologies for propulsion–airframe integration. Specifically, the focus is given to both evolutionary technologies, such as ultra-high bypass ratio turbofan engines, and breakthrough propulsive concepts, represented in this frame by boundary layer ingestion engines and distributed propulsion architectures. The discussion focuses mainly on the integration effects of these propulsion technologies, with the aim of defining performance interactions with the overall aircraft, in terms of aerodynamic, propulsive, operating and mission performance. Hence, this work aims to analyse these technologies from a general perspective, related to the effects they have on overall aircraft design and performance, primarily considering the fuel consumption as a main metric. Potential advantages but also possible drawbacks or detected showstoppers are proposed and discussed with the aim of providing as broad a framework as possible for the aircraft design development roadmap for these emerging propulsive technologies.

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Section: Experimental Assessment: Scaled Demonstratorsmentioning

confidence: 99%

“…Further details on the multidisciplinary design activities of this demonstrator are available in refs. [187,188].…”

Section: Experimental Assessment: Scaled Demonstratorsmentioning

confidence: 99%

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Abu Salem,

Palaia,

Bravo-Mosquera

et al. 2024

Designs

View full text Add to dashboard Cite

show abstract

“…In addition, the TF transport aircraft makes better use of fuselage volume than the single wide-body configuration, allowing for significant reductions in fuselage structural mass [7]. The TF configuration has been realized and flight-tested on different types of aircraft, such as the general aircraft HY4 [21], a TF UAV [22,23], and Stratolaunch carrier aircraft [24]. A TF aircraft preliminary case study with similar parameter values to the reference conventional aircraft was presented by Chiesa et al [8].…”

Section: Introductionmentioning

confidence: 99%

Aerostructural Optimization and Comparative Study of Twin-Fuselage and Strut-Braced-Wing Aircraft Configurations

Ma,

Abouhamzeh,

Elham

2024

Journal of Aircraft

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The ultrahigh-aspect-ratio wing (UHARW) concept is a promising configuration to achieve future sustainable aviation goals. Twin-fuselage (TF) and strut-braced-wing (SBW) configurations are characterized by smaller structural bending moments and shear forces in the wing and are promising concepts for realizing UHARW designs. This paper addresses the aerostructural optimization problem of TF and SBW configurations with UHARW by using a coupled adjoint aerostructural optimization tool, which is composed of a geometrically nonlinear structural solver and a quasi-three-dimensional natural laminar flow (NLF) aerodynamic solver. The optimization results show significant improvements in fuel efficiency and performance for the TF and SBW aircraft, with fuel mass reductions of 13 and 10%, respectively, compared to the corresponding baseline aircraft designed in the conceptual design phase. In comparison to the original reference aircraft A320neo, the optimized TF and SBW have 48 and 31% lower fuel weights, respectively. The NLF range of both upper and lower wing surfaces is expanded during optimization. The optimized SBW configuration has a wing aspect ratio of 26.01, while the optimized TF has a wing aspect ratio of 20.74, indicating that the SBW concept is more conducive to realizing UHARW design compared with the TF configuration studied in this work. The optimized TF aircraft has a lighter fuel weight and gross weight compared to the optimized SBW aircraft, which is because the TF aircraft has a lighter operational empty weight, including a lighter fuselage structural weight, landing gear weight, etc., whereas the top-level aircraft requirements are the same for both aircraft, including range, payload, and cruise Mach.

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A Rapid Evaluation Method for the Aero-Propulsion Coupling Characteristics of a Distributed Electric Propulsion Aircraft

Yu,

Lei,

et al. 2024

2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings

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Multidisciplinary Design Optimization of Twin-Fuselage Aircraft with Boundary-Layer-Ingesting Distributed Propulsion

Cited by 10 publications

References 36 publications

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft

Aerostructural Optimization and Comparative Study of Twin-Fuselage and Strut-Braced-Wing Aircraft Configurations

A Rapid Evaluation Method for the Aero-Propulsion Coupling Characteristics of a Distributed Electric Propulsion Aircraft

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