Neural network and response surface methodology for rocket engine component optimization

Vaidyanathan, Rajkumar; Papita, Nilay; Shyy, Wei; Tucker, P. Kevin; Griffin, Lisa W.; Haftka, Raphael T.; Fitz-Coy, Norman; Mcconnaughey, H. V.

doi:10.2514/6.2000-4880

Cited by 23 publications

(15 citation statements)

References 8 publications

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“…The efficiency of response surface method is verified by Shyy et al [20], Papila and Shyy [21], Madsen et al [22], and Vaidyanathan et al [23] in their works of designing rocket engine injector, supersonic turbines, diffuser, and rocket engine component, respectively. Prescribed set of design points, so called training points, is selected by D-optimal design [2].…”

Section: Optimization Techniquesmentioning

confidence: 82%

Design optimization of rib-roughened channel to enhance turbulent heat transfer

Kim

2004

International Journal of Heat and Mass Transfer

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Section: Optimization Techniquesmentioning

confidence: 82%

Design optimization of rib-roughened channel to enhance turbulent heat transfer

Kim

2004

International Journal of Heat and Mass Transfer

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“…Efficiency of the response surface based optimization was verified by Shyy et al [15], Papila and Shyy [16], Madsen et al [17], and Vaidyanathan et al [18] in their works of designing rocket engine injector, supersonic turbines, diffuser, and rocket engine component, respectively. Prescribed set of design points, so called training points, was selected by full-factorial design [8].…”

Section: Optimization Process Response Surface Methodsmentioning

confidence: 90%

Shape optimization of inclined ribs as heat transfer augmentation device

Kim

2006

J. of Therm. Sci.

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This work presents numerical optimization techniques for the design of a rectangular channel with inclined ribs to enhance turbulent heat transfer. The response surface method with Reynolds-averaged Navier-Stokes analysis is used for optimization. Shear stress transport turbulence model is used as a turbulence closure. Computational results for local heat transfer rate show a reasonable agreement with the experimental data. Width-to-rib height ratio and attack angle of the rib are chosen as design variables. The objective function is defined as a linear combination of heat-transfer and friction-loss related terms with the weighting factor. Full-factorial experimental design method is used to determine the data points. Optimum shapes of the channel have been obtained in a range of the weighting factor.

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“…Since the RSA model coefficients vector b is an unbiased estimate of coefficients vector (1) , it is expected that the error in the prediction will be a function of coefficients in vector (2) , and this is indeed observed from Equation (12).…”

Section: Estimation Of Bias Error Boundsmentioning

confidence: 91%

“…Madsen et al [7], Papila et al [8,9], Shyy et al [10,11] and, Vaidyanathan et al [12,13] used RSAs as design evaluators for the optimization of propulsion components including a turbulent flow diffuser, supersonic turbine, swirl coaxial injector element and liquid rocket injector designs. Redhe et al [14,15] and Craig et al [16] used RSAs in design of vehicles for crashworthiness.…”

Section: T Goel Et Almentioning

confidence: 99%

Generalized pointwise bias error bounds for response surface approximations

Goel

Haftka

Papila

et al. 2005

Numerical Meth Engineering

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SUMMARYThis paper proposes a generalized pointwise bias error bounds estimation method for polynomialbased response surface approximations when bias errors are substantial. A relaxation parameter is introduced to account for inconsistencies between the data and the assumed true model. The method is demonstrated with a polynomial example where the model is a quadratic polynomial while the true function is assumed to be cubic polynomial. The effect of relaxation parameter is studied. It is demonstrated that when bias errors dominate, the bias error bounds characterize the actual error field better than the standard error. The bias error bound estimates also help to identify regions in the design space where the accuracy of the response surface approximations is inadequate. It is demonstrated that this information can be utilized for adaptive sampling in order to improve accuracy in such regions.

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Neural network and response surface methodology for rocket engine component optimization

Cited by 23 publications

References 8 publications

Design optimization of rib-roughened channel to enhance turbulent heat transfer

Design optimization of rib-roughened channel to enhance turbulent heat transfer

Shape optimization of inclined ribs as heat transfer augmentation device

Generalized pointwise bias error bounds for response surface approximations

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