ASTROS - A multidisciplinary automated structural design tool

Neill, D. J.

doi:10.2514/6.1987-713

Cited by 25 publications

(4 citation statements)

References 5 publications

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“…In this study, the unconstrained optimization in Eqs. (5), (6), and (7) with the least-squares surface-fitting technique in Eq. (15) is used to minimize the trim shape error.…”

Section: Jig-shape Optimizationsmentioning

confidence: 99%

“…Their optimum wing twist and camber distribution is designed using WINGDES code [5], based on a linearized potential flow solver. 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.…”

Section: Introductionmentioning

confidence: 99%

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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 this study, the unconstrained optimization in Eqs. (5), (6), and (7) with the least-squares surface-fitting technique in Eq. (15) is used to minimize the trim shape error.…”

Section: Jig-shape Optimizationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Jig-Shape Optimization of Low-Boom Supersonic Aircraft

Pak

2018

Journal of Aircraft

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“…The skins of the wing are made up of 4 composite orientations, 0°, ±45°, and 90° plies, where the thickness of the -45° and +45° orientations are constrained to be equal. The composite wing skin plies are designed in thickness, via the structural optimization tool, ASTROS 27,28 . American Institute of Aeronautics and Astronautics The wing section of the nonlinear aerodynamic model is shown in Figure 5.…”

Section: Numerical Examplementioning

confidence: 99%

Robust structural design for Active Aeroelastic Wing with aerodynamic uncertainties

Zink

Raveh

Mavris

2000

41st Structures, Structural Dynamics, and Materials Conference and Exhibit

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A multidisciplinary design study for Active Aeroelastic Wing technology considering the uncertainty in maneuver loads estimated by linear aerodynamic theory is presented. The study makes use of a design of experiments/response surface methodology and modal-based structural optimization to construct deterministic relationships between wing structural weight and control laws design, based on linear aerodynamics. CFD Navier-Stokes analysis is then used to define typical differences between rigid aerodynamic loads as predicted by nonlinear and linear theory. These differences are then used to define aerodynamic uncertainties in a probabilistic manner, which are propagated, through Latin Hypercube Sampling and modal-based static aeroelastic analysis, to a response function that represents the magnitude of structural redesign. Structural designs then are sought that are both low weight and whose performance is relatively invariant in the presence of load uncertainty. The motivation for this study is derived by the frequent inability to accurately represent maneuver loads on an aircraft structure, which often requires redesign (sometimes major) late in the design process as loads predictions become more accurate.

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“…The wing weight is estimated for several wing geometries by means of the multidisciplinary optimization tool, Automated Structural Optimization System (ASTROS) 13 . ASTROS combines finite element methods with aerodynamic and trim modules, in conjunction with gradient-based optimization routines to optimize the thickness of structural members to minimum weight while meeting user-defined constraints, such as static and dynamic aeroelastic requirements.…”

Section: Parameterization Of Finite Element and Aerodynamic Modelsmentioning

confidence: 99%

Development of Wing Structural Weight Equation for Active Aeroelastic Wing Technology

Zink

Mavris

Flick

et al. 1999

SAE Technical Paper Series

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A multidisciplinary design study considering the impact of Active Aeroelastic Wing (AAW) technology on the structural wing weight of a lightweight fighter concept is presented.The study incorporates multidisciplinary design optimization (MDO) and response surface methods to characterize wing weight as a function of wing geometry. The study involves the sizing of the wing box skins of several fighter configurations to minimum weight subject to static aeroelastic requirements. In addition, the MDO problem makes use of a new capability, trim optimization for redundant control surfaces, to accurately model AAW technology. The response surface methodology incorporates design of experiments, least squares regression, and makes use of the parametric definition of a structural finite element model and aerodynamic model to build response surface equations of wing weight as a function of wing geometric parameters for both AAW technology and conventional control technology. The goal for this design study is to demonstrate a process by which some of the benefits associated with AAW technology can be quantified over the wing geometry design space, so that future conceptual designers may make the best use of the technology.

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ASTROS - A multidisciplinary automated structural design tool

Cited by 25 publications

References 5 publications

Jig-Shape Optimization of Low-Boom Supersonic Aircraft

Jig-Shape Optimization of Low-Boom Supersonic Aircraft

Robust structural design for Active Aeroelastic Wing with aerodynamic uncertainties

Development of Wing Structural Weight Equation for Active Aeroelastic Wing Technology

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