High-Fidelity Multidisciplinary Design Optimization Methodology with Application to Rotor Blades

Wang, Li; Diskin, Boris; Biedron, Robert T.; Nielsen, Eric J.; Sonneville, Valentin; Bauchau, Olivier A.

doi:10.4050/jahs.64.032002

Cited by 7 publications

(2 citation statements)

References 14 publications

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“…The framework also enables explorations of the results so that designers can see the influence of the design variables for all involved disciplines simultaneously. Highfidelity rotorcraft computations are performed in [6] by means of a multidisciplinary design and optimization framework. The involved disciplinary models include computational fluid dynamic codes and have, for example, been used with optimizations to reduce rotor torque while maintaining other desired rotor blade parameters, such as rolling and pitching moments.…”

Section: Introductionmentioning

confidence: 99%

Optimization Framework for Early Conceptual Design of Helicopters

et al. 2022

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This work illustrates how a proposed method can be used to create optimization frameworks for early conceptual design studies and to increase overall knowledge at an early design stage. The method is intended to facilitate concept selection in challenging domains that typically involve multidisciplinary design problems with contradictory requirements. The main focus of the work presented here is on the conceptual design of helicopters; however, the method is intended to be applicable to early design studies in other domains as well. In short, statistics about existing helicopters are collected and compiled to provide a basis for various regression analyses. The purpose of this is to unravel relationships in the data and to obtain simple estimation models from statistical regressions that can be used in conjunction with existing formulas and equations to generate an initial helicopter design estimate. Models for each discipline, such as aerodynamics, are then created using the outcomes of the regression analyses and existing equations. Lastly, the method is used to define a multidisciplinary design optimization framework incorporating all the models obtained from the different disciplines. A case study based on search and rescue operations is used to test the proposed framework in order to obtain possible first suggestions for the baseline design of a new general-purpose search and rescue helicopter.

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Section: Introductionmentioning

confidence: 99%

Optimization Framework for Early Conceptual Design of Helicopters

et al. 2022

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“…Flight test measurements [3,4] and wind tunnel investigations [10] provide data for verification the analytical methods applied for defining loads of helicopter rotor. Introduction CFD/CSD methods [1,9] which couple computational fluid dynamics and analysis of flexible body dynamics allows to improve the accuracy of prediction the rotor blades loads.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Boundary States of Helicopter Flight

Stanisławski

2019

Journal of KONES

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Results of simulation of main rotor blade loads and deformations, which can be generated during boundary states of helicopter flight, are presented. Concerned cases of flight envelope include hover at maximum height, level flight at high velocity, pull-up manoeuvres applying cyclic pitch and mixed collective and cyclic control. The simulation calculations were executed for data of light helicopter with three-bladed articulated rotor. For analysis, the real blades are treated as elastic axes with distributed masses of blade segments. The model of deformable blade allows for out-of-plane bending, in plane bending, and torsion. For assumed flight state of helicopter, the equations of rotor blades motion are solved applying Runge-Kutta method. According to Galerkin method, for each concerned azimuthal position of blade the parameters of its motions are assumed as a combination of considered bending and torsion eigen modes of the blade. The loads of rotor blades generated during flight depend due to velocity of flight, helicopter mass, position of rotor axis in air and deflections of swashplate that correspond to collective and cyclic pitch angle applied to rotor blades. The results of simulations presenting rotor loads and blade deformations are shown in form of time-runs and as plots of rotor-disk distributions. The simulations of helicopter flight states may be useful for prediction the conditions of flight-tests without exceeding safety boundaries or may help to define limitations for manoeuvre and control of helicopter.

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Adaptive sampling assisted surrogate modeling of initial failure envelopes of composite structures

Tian

2021

Composite Structures

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High-Fidelity Multidisciplinary Design Optimization Methodology with Application to Rotor Blades

Cited by 7 publications

References 14 publications

Optimization Framework for Early Conceptual Design of Helicopters

Optimization Framework for Early Conceptual Design of Helicopters

Simulation of Boundary States of Helicopter Flight

Adaptive sampling assisted surrogate modeling of initial failure envelopes of composite structures

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