Robust design for aeroelastically tailored/active aeroelastic wing

Zink, P. Scott; Mavris, Dimitri N.; Love, Michael; Karpel, Moti

doi:10.2514/6.1998-4781

Cited by 21 publications

(13 citation statements)

References 10 publications

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“…In order to account for uncertainties in predicting maneuver loads and the effect of control surfaces, an optimization method for minimizing the weight and maximizing the invariance to random load effects is presented by Zink et al [103,104]. The uncertainties of the aerodynamic loads are quantified by comparing the results of linear and nonlinear aerodynamics.…”

Section: Aerodynamics and Aeroelasticitymentioning

confidence: 99%

Reliability-Based Optimization of Civil and Aerospace Structural Systems

Maute¹,

Frangopol²

2004

Engineering Design Reliability Handbook

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Section: Aerodynamics and Aeroelasticitymentioning

confidence: 99%

Reliability-Based Optimization of Civil and Aerospace Structural Systems

Maute¹,

Frangopol²

2004

Engineering Design Reliability Handbook

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“…The modal-based static aeroelastic module [13] that integrated with ASTROS was applied in [34] in a method for robust design of aeroelastically tailored active aeroelastic wings. Probabilistic methods were used to evaluate the wing structure robustness to changes in gearing ratios in control surface blending in dynamic aircraft maneuvers.…”

Section: Static Aeroelastic Considerationsmentioning

confidence: 99%

Procedures and Models for Aeroservoelastic Analysis and Design

Karpel

2001

Z. angew. Math. Mech.

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The multi‐disciplinary area that deals with the interaction of the structural, aerodynamic, and control systems of flight vehicles is called aeroservoelasticity. The various aircraft design aspects which are affected by aeroservoelastic interaction are presented with a common modal‐based formulation. The disciplinary and interaction techniques are reviewed and combined for an integrated design optimization scheme where stress, static‐aeroelastic, closed‐loop flutter, control margins, time response, and continuous gust constraints are treated with a common basic model. The structure is represented in the basic model by a set of low‐frequency normal modes of a baseline design. Design changes are adequately addressed without changing the generalized coordinates. Typical difficulties of the modal approach are alleviated by various optional fictitious‐mass and modal perturbation techniques. Static modes can be added during the optimization process for better convergence to the optimal solution. Minimum‐state rational approximation of the unsteady aerodynamics leads to an efficient state‐space model which can be augmented by any combination of linear control components. Physical weighting algorithm is used to improve the aerodynamic approximations and to select modes for truncation or residualization. Linear reduced‐size models and the associated analytic sensitivities to design changes facilitate extremely efficient and adequately accurate on‐line design sessions. The linear models can be integrated with computational aerodynamics codes for the evaluation of important non‐linear aerodynamic effects early in the design process.

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“…Although the desired stability derivative is calculated by ASTROS during an antisymmetric aeroelastic trim analysis (and even printed in the output), it is not stored in the database that is created by the standard version of the program. This feature was added to the AANDE version of ASTROS [11]. However, because this project uses the standard version of the program, another method was found to retrieve the stability derivative information from ASTROS.…”

Section: Determination Of Stability Derivatives For the Wingmentioning

confidence: 99%

Structural and control surface design for wings using the adaptive modeling language

Zweber¹,

Hartong

1998

7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization

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Computerized engineering environments promise to significantly improve the processes for designing complex mechanical systems. This paper investigates the application of the Adaptive Modeling Language® (AML™) to the aircraft design process. Models were developed in AML to perform a limited trade study between the sizing of a wing box for high speed maneuvers and the available roll control power at landing speeds. This project has build upon some previous efforts that also used AML. While the results of the trade study were not very interesting, the project did illustrate the advantages of combining diverse disciplines in a single engineering environment. It demonstrated the ease with which existing capabilities in the environment can be reconfigured and applied to a new engineering problem. This project also added to the confidence that a much more expansive system can be developed.

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Robust design for aeroelastically tailored/active aeroelastic wing

Cited by 21 publications

References 10 publications

Reliability-Based Optimization of Civil and Aerospace Structural Systems

Reliability-Based Optimization of Civil and Aerospace Structural Systems

Procedures and Models for Aeroservoelastic Analysis and Design

Structural and control surface design for wings using the adaptive modeling language

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