A Parametric Multi-Fidelity Approach to Conceptual Airframe Design

Corman, Jason A.; Weston, Neil R.; Friedland, Coleby; Mavris, Dimitri N.; Laughlin, Trevor W.

doi:10.2514/6.2018-1930

Cited by 9 publications

(5 citation statements)

References 11 publications

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“…The EDS was initially developed with U.S. Federal Administration Office of Environment and Energy for specifically for assessing the aircraft level noise and emissions [158]. The vehicle modelling uses either NASA FLOPS code [158] or the recently developed Rapid Airframe Design Environment (RADE) is developed at the ASDL [159].…”

Section: Other Toolsmentioning

confidence: 99%

Towards the Design of Future Aircraft: A Critical Review On the Tools and Methodologies

Liu,

Zhang,

Zhang

et al. 2024

Aerosp. Res. Commun.

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This study reviews tools and approaches developed at universities and institutes for conceptual and preliminary aircraft design. Problem, solution, and behavioral space covered by each tool are discussed and a categorization for the methods underlying the different disciplinary tools is proposed. Special attention is given to the search method, if any, embedded in or supported by each tool to explore the proliferation of Multidisciplinary Design Optimization (MDO) in aircraft design tools. The study shows that many tools are available but most are proprietary and none covers all the aspects of the conceptual and preliminary design process. MDO is only a small element in most of the tools. The review can be used for the formulation of requirements and necessities for future aircraft design tools.

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Section: Other Toolsmentioning

confidence: 99%

Towards the Design of Future Aircraft: A Critical Review On the Tools and Methodologies

Liu,

Zhang,

Zhang

et al. 2024

Aerosp. Res. Commun.

View full text Add to dashboard Cite

show abstract

“…4) Subsystem Layout: For a given subsystem architecture, the logical connectivity between propulsion system, secondary power generation and distribution subsystems (PGDS), and power consuming subsystems (PCS) are established and mapped to physical connectivity based on OML. The geometry manager used in this work is facilitated through the RADE toolkit [16], developed at the Aerospace Systems Design Laboratory (ASDL). RADE contains a module for parametric variation of a baseline OML through the OpenVSP API, where aerodynamic shape variables such as span, sweep, chord, area, AR, twist, among others can be defined.…”

Section: A Geometry Managermentioning

confidence: 99%

“…The transfer of aerodynamic loads to the structure is performed through integration of surface pressures to reference points along the span of a wing-like component. A module in RADE [16,28] estimates the elastic axis and sets these reference points at the intersection of this line with rib components. The forces and moments associated with each reference point are then distributed to the structure via rigid body elements at key intersecting nodes between the rib and skin.…”

Section: F Structural Analysis and Sizingmentioning

confidence: 99%

A Certification-Driven Platform for Multidisciplinary Design Space Exploration in Airframe Early Preliminary Design

Sarojini

Xie

Cai

et al. 2020

Aiaa Aviation 2020 Forum

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Following the conceptual phase of aircraft design, sizing and performance estimations shift from historical-based empirical equations to physics-based simulations. The initial aircraft configuration is refined with a larger number of objectives and requirements, and certification regulations play a critical role in defining these. Analysis tools in the early phases of preliminary design have an important trade-off between accuracy, complexity, and computational efficiency. A number of analysis frameworks currently exist with varying levels of fidelity, multidisciplinary coupling, and limitations in the number of disciplines, degrees of freedom, and requirements they are able to implement. To enable efficient design space exploration (DSE), this paper proposes an integrated preliminary design framework that couples aerodynamics, structures, subsystems, aircraft performance, flight dynamics, and certification testing at varying levels of fidelity. This framework serves as a numerical testbed that can be used to explore the aircraft configuration and disciplinary design spaces, strength of disciplinary couplings, and propagate disciplinary uncertainties across the entire aircraft system. The framework is demonstrated using the horizontal tail of a large twin-aisle aircraft as a test case.

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“…An accurate estimation of the empty weight is critical in aircraft design process. Existing tools using physics-based methods include RADE which focuses on structural sizing and weight estimation of the airframe and lifting surfaces [28], ISSAAC which sizes major aircraft subsystems [29], and WATE++ which analytically computes engine weight and dimension [30], etc. However, to achieve a high fidelity, physics-based methods typically require a large amount of…”

Section: Fig 1 Geometry Comparison Between Benchmark Model and Bwb-00...mentioning

confidence: 99%

Integrated Sizing and Optimization of Hybrid Wing Body Aircraft in Conceptual Design

Xie

Cai

Chen

et al. 2019

AIAA Aviation 2019 Forum

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The hybrid wing body (HWB) configuration is a paradigm shift in commercial transport aircraft design in terms of environmentally responsible characteristics and significant performance improvements over the conventional tube-and-wing configuration. However, the sizing methods and analysis tools used in conceptual design of tube-and-wing aircraft are not fully compatible with HWB due to the highly integrated fuselage and wing. This paper proposes a novel approach to perform parametric sizing and optimization of HWB aircraft at the conceptual design phase, and develops an interdisciplinary design framework which integrates preliminary aerodynamic analysis, weight estimation, propulsion system sizing, and mission analysis. Enabled by the techniques of Design of Experiments and surrogate modeling, a design space exploration is conducted over the top-level aircraft design variables, including sensitivity assessment, feasible design space identification, and constrained multi-objective optimization. The impact of uncertainties in disciplinary analyses and novel technologies on aircraft-level performance is investigated through an uncertainty analysis.

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A Parametric Multi-Fidelity Approach to Conceptual Airframe Design

Cited by 9 publications

References 11 publications

Towards the Design of Future Aircraft: A Critical Review On the Tools and Methodologies

Towards the Design of Future Aircraft: A Critical Review On the Tools and Methodologies

A Certification-Driven Platform for Multidisciplinary Design Space Exploration in Airframe Early Preliminary Design

Integrated Sizing and Optimization of Hybrid Wing Body Aircraft in Conceptual Design

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