Enhanced maneuver airloads simulation for the Automated Structural Optimization System - ATROS

Love, Michael; Barker, Daniel S.; Egle, D. D.; Neill, D. J.; Kolonay, Raymond M.

doi:10.2514/6.1997-1116

Cited by 10 publications

(15 citation statements)

References 4 publications

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“…The trim solution must then be formulated as an iterative problem to determine the "best" combination of control surface rotations that trim the aircraft. Older versions of ASTROS have solved Equation 6 for nonredundant control surfaces, but a new module of ASTROS poses the solution of Equation 6 for redundant control surfaces as an optimization problem to minimize an objective of interest to the structural designer 15 . In particular, one would desire to deflect the surfaces in such a way as to favorably modify the maneuver loads, so that ultimately weight might be reduced.…”

Section: Modeling Of Aaw By Trim Optimizationmentioning

confidence: 99%

“…Reference [15] discusses in detail the theory of the new ASTROS trim optimization module, and how it fits into the overall ASTROS framework. Figure 4 shows the structural model for the baseline geometry.…”

Section: Minimizementioning

confidence: 99%

“…It also contains paneling for the four wing control surfaces and horizontal tail to coincide with the control surfaces on the structural model. ASTROS has been modified to allow inclusion of Carmichael panel geometry and aerodynamic influence coefficients which then replace the existing aerodynamic database entities created by USSAERO, ASTROS' original aerodynamic module 15 .…”

Section: Figure 4 -Structural Model For Baseline Geometrymentioning

confidence: 99%

“…For the AAW cases, the process is not so simple, as multiple control surfaces are used and whose settings are dependent on results of a trim optimization. Originally, the intent was for the trim optimization process to be performed within the structural optimization loop 15 , as the optimal control surface deflections are a function of the structural design. In other words, for each iteration in the structural optimization, the control surface deflections for the current structural design would be optimized according to the formulation described earlier.…”

Section: Calculation Of Wing Weightmentioning

confidence: 99%

See 3 more Smart Citations

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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Section: Modeling Of Aaw By Trim Optimizationmentioning

confidence: 99%

Section: Minimizementioning

confidence: 99%

Section: Figure 4 -Structural Model For Baseline Geometrymentioning

confidence: 99%

Section: Calculation Of Wing Weightmentioning

confidence: 99%

See 2 more Smart Citations

Development of Wing Structural Weight Equation for Active Aeroelastic Wing Technology

Zink

Mavris

Flick

et al. 1999

SAE Technical Paper Series

View full text Add to dashboard Cite

show abstract

“…Historically, design of the gear ratios, more commonly known as trim optimization, has comprised of a direct gradientbased optimization formulation. By this approach, the gear ratios are optimized to minimize an objective of stress, component loads and/or control power 10,11,12,13,14 . The typical approach to the AAW design process then involves embedding trim optimization in an iterative process with structural optimization, to arrive at a simultaneous optimal control law and structural gauges.…”

Section: Introductionmentioning

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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Reducing Induced Drag and Maneuver Loads by Active Aeroelastic Alteration

Lin¹

2016

Journal of Aircraft

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Enhanced maneuver airloads simulation for the Automated Structural Optimization System - ATROS

Cited by 10 publications

References 4 publications

Development of Wing Structural Weight Equation for Active Aeroelastic Wing Technology

Development of Wing Structural Weight Equation for Active Aeroelastic Wing Technology

Robust structural design for Active Aeroelastic Wing with aerodynamic uncertainties

Reducing Induced Drag and Maneuver Loads by Active Aeroelastic Alteration

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