Framework for Establishing Limits of Tabular Aerodynamic Models for Flight Dynamics Analysis

Ghoreyshi, Mehdi; Badcock, K. J.; Ronch, Andrea Da; Marques, Simão; Swift, A.; Ames, Nasa­

doi:10.2514/1.c001003

Cited by 38 publications

(18 citation statements)

References 27 publications

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“…Previous works 19,20 substantiated the limitations of tabular models when comparing to CFD and flight tests data, and this motivates the current study. The overall objective is to put in place a framework of different low-order models for representation of non-linear unsteady aerodynamic loads.…”

Section: -18mentioning

confidence: 97%

Modeling of Unsteady Aerodynamic Loads

Ronch

Badcock

Храбров

et al. 2011

AIAA Atmospheric Flight Mechanics Conference

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Time-accurate solutions of the Euler or Navier-Stokes equations are still nowadays a computationally expensive approach for applications where a magnitude of parameters has to be investigated. This work focuses on flight dynamics-related studies. The generation of several low-order models for the evaluation of unsteady and non-linear aerodynamic loads are investigated. The validity of low-order models presented is assessed by comparing the model output with unsteady time-accurate Computational Fluid-Dynamics (CFD) simulations. The test case is the NACA 0012 airfoil. The low-order models considered are: a non-linear model based on aerodynamic derivatives, a Volterra model, a surrogate-based recurrence-framework model, linear indicial functions and radial basis functions trained with neural networks.

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Section: -18mentioning

confidence: 97%

Modeling of Unsteady Aerodynamic Loads

Ronch

Badcock

Храбров

et al. 2011

AIAA Atmospheric Flight Mechanics Conference

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“…Works by the co-authors 20,30 have pinpointed the presence of vortical features in the flow field at 15.0…”

Section: B Standard Dynamics Model Aircraftmentioning

confidence: 99%

“…29 This model has been used for two previous studies related to dynamic derivatives. First, the development of a flight dynamics aerodynamic model using CFD was reported in Ghoreyshi et al 30 Forced manoeuvres were used to evaluate the applicability of the dynamic derivative model. The results of a study that considers the variation of the dynamic derivatives with various aerodynamic and motion parameters, based on time domain simulations is reported in Da Ronch et al 20 A block structured mesh was generated for the use with the PMB and HB solvers and it is shown in Fig.…”

Section: B Standard Dynamics Model Aircraftmentioning

confidence: 99%

Linear Frequency Domain and Harmonic Balance Predictions of Dynamic Derivatives

Ronch

McCracken

Badcock

et al. 2013

Journal of Aircraft

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“…This time lag cannot be predicted using Bryan's model because the quasi-steady lift change is synchronized with the angle of attack change. Bryan's initial model was later modified to include acceleration derivatives to somehow model the effects from the rate of change of incidence and sideslip angles in time, although this modified model cannot predict the unsteady forces and moments of a rapid maneuvering aircraft in the presence of shock waves and vortical flows [16]. Indeed, the unsteady aerodynamic forces and moments not only depend on the instantaneous states but also their time histories [57,58].…”

Section: Introductionmentioning

confidence: 99%

Computational approximation of nonlinear unsteady aerodynamics using an aerodynamic model hierarchy

Ghoreyshi

Jirasek

Cummings

2013

Aerospace Science and Technology

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, "Computational approximation of nonlinear unsteady aerodynamics using an aerodynamic model hierarchy" (2013 Modeling nonlinear unsteady aerodynamic effects in the simulation of modern fighter aircraft is still a very challenging task. A framework for approximating nonlinear unsteady aerodynamics with a Radial Basis Function neural network is provided. Training data were generated from a hierarchy of aerodynamic models. At the highest level, solutions of the discretized Reynolds-Averaged Navier-Stokes (RANS) equations provide the quantitative and qualitative solution of flow around aircraft, although the results are expensive in terms of computational resources. The Euler simulations are less expensive and provide qualitative data up to moderate angles of attack. The integration of these data is promising for generating accurate aerodynamic models at moderate computational cost. To illustrate the method, an airfoil undergoing pitching and plunging motion is considered. The primary and secondary aerodynamic model data are computed using RANS and Euler equations, respectively. A description for a mapping between the aerodynamic loads and the motion parameters based on the implicit function theorem is described. The mapping is then augmented by adding the secondary data to the input dataset. The selection of training data is then discussed. Once the network is trained, it can compute the unsteady aerodynamic loads from motion descriptions on the order of a few seconds. The framework is examined for different motions, and in all cases, the ROM predictions closely represent the actual aerodynamic responses. It is also demonstrated that the aerodynamic hierarchy aids in the rapid development of a reduced-order model.

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Framework for Establishing Limits of Tabular Aerodynamic Models for Flight Dynamics Analysis

Cited by 38 publications

References 27 publications

Modeling of Unsteady Aerodynamic Loads

Modeling of Unsteady Aerodynamic Loads

Linear Frequency Domain and Harmonic Balance Predictions of Dynamic Derivatives

Computational approximation of nonlinear unsteady aerodynamics using an aerodynamic model hierarchy

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