Multidisciplinary design optimization of a large transport aircraft wing

Tzong, T.; Sikes, G. D.; Loikkanen, Matti J.

doi:10.2514/6.1992-1002

Cited by 11 publications

(4 citation statements)

References 5 publications

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“…The structural analysis and optimization was performed in the ADOP [3,4] (Aeroelastic Design Optimization Program) code, using aeroelastic loads calculated in AILS [4,5] (Advanced Integrated Loads Subsystem). The structure was sized based on four steady maneuver conditions, representing 2.5g pull-ups at various flight conditions.…”

Section: Structural Baseline and Sensitivitiesmentioning

confidence: 99%

A practical approach to MDO and its application to an HSCT aircraft (Multidisciplinary Design Optimization)

Baker¹,

Giesing²

1995

Aircraft Engineering, Technology, and Operations Congress

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This paper contains an outline of a practical concurrent approach to multidisciplinary design optimization and an application of it to an HSCT aircraft. The disciplines chosen for the example presented are stmctures and aerodynamics. The Multidisciplinary Design Optimization (MDO) process (by adjusting the wing jig twist) successhlly decreased the takeoff gross weight of a baseline aircraft that was already optimized for aerodynamics and stmctures separately. This illustrates that the aircraft can be optimized even after the advanced design stage. The example chosen for this paper illustrates the classic tradeoff between aerodynamics and structures, and indicated that the optimal configuration has more washout (nose-down twist) than the minimum drag design.Onc of the most challenging issues in multilevel optimization schemes is the calculation of sensitivities of sub-discipline optima to global design variables. Finite difference sensitivities were used in this study, but an interesting new analytical procedure for estimating optimum sensitivities is presented.

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Section: Structural Baseline and Sensitivitiesmentioning

confidence: 99%

A practical approach to MDO and its application to an HSCT aircraft (Multidisciplinary Design Optimization)

Baker¹,

Giesing²

1995

Aircraft Engineering, Technology, and Operations Congress

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“…The structural optimization of the HSCT wing box structure was performed using automated structural optimization system (ASTROS) code [6]. A jig-shape optimization of an HSCT wing was also performed by Baker and Giesing [7] using aeroelastic design optimization (ADOP) [8] and advanced integrated loads subsystem (AILS) [9] codes. In the study by Baker and Giesing, the takeoff gross weight of the baseline HSCT aircraft was decreased by adjusting the wing jig twist.…”

Section: Introductionmentioning

confidence: 99%

Jig-Shape Optimization of Low-Boom Supersonic Aircraft

Pak

2018

Journal of Aircraft

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A simple approach for optimizing the jig-shape is proposed in this study. This simple approach is based on an unconstrained optimization problem and applied to a low-boom supersonic aircraft. In this study, the jig-shape optimization is performed using the two-step approach. First, starting design variables are computed using the least-squares surface fitting technique. Next, the jig-shape is further tuned using a numerical optimization procedure based on an in-house object-oriented optimization tool. During the numerical optimization procedure, a design jig-shape is determined by the baseline jig-shape and basis functions. A total of 12 symmetric mode shapes of the cruise-weight configuration, rigid pitch shape, rigid left and right stabilator rotation shapes, and a residual shape are selected as sixteen basis functions. After three optimization runs, the trim shape error distribution is improved, and the maximum trim shape error of 0.9844 inches of the starting configuration becomes 0.00367 inch by the end of the third optimization run.

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“…In literature, there have been many examples about flexible wings that the structural weight has been reduced and the aeroelastic performance improved effectively by structure optimization with considering multiple constraints [6,7]. However, the above-mentioned cases are all based on determinate general parameters and structural arrangement.…”

Section: Introductionmentioning

confidence: 99%

Studies on the influence of spar position on aeroelastic optimization of a large aircraft wing

Wan

Liu

Tang

et al. 2011

Sci. China Technol. Sci.

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Aeroelastic problems are encountered at the preliminary design stage of flexible wings for large aircraft. A three-dimensional finite element model of a high-aspect-ratio wing was built, and the influence of the front and rear spar positions on the results of the aeroelastic analysis and optimization was studied to improve the wing structure desgin. The most feasible and optimal solutions were effectively obtained by aeroelastic optimization. In particular, the position parameter of the front spar has a greater influence on the aeroelastic analysis and optimization than the rear spar. In addition, some key constraints became restrictive leading to a rapid increase in the structural weight. Therefore, reasonable constraints were necessary for the oprimization of results. large aircraft, aeroelasticity, optimization design, high-aspect-ratio wing, spar Citation: Wan Z Q, Liu D Y, Tang C H, et al. Studies on the influence of spar position on aeroelastic optimization of a large aircraft wing.

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Multidisciplinary design optimization of a large transport aircraft wing

Cited by 11 publications

References 5 publications

A practical approach to MDO and its application to an HSCT aircraft (Multidisciplinary Design Optimization)

A practical approach to MDO and its application to an HSCT aircraft (Multidisciplinary Design Optimization)

Jig-Shape Optimization of Low-Boom Supersonic Aircraft

Studies on the influence of spar position on aeroelastic optimization of a large aircraft wing

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