Using modeling knowledge to guide design space search

Gelsey, Andrew; Schwabacher, Mark; Smith, Delia E.

doi:10.1016/s0004-3702(98)00012-5

Cited by 26 publications

(9 citation statements)

References 17 publications

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“…In addition to the design constraints, we use one model constraint. 21 This constraint speci es that the two line segments in Fig. 5, when extended into lines, cross at a horizontal location between x l and x l 1 Dx.…”

Section: Optimization Proceduresmentioning

confidence: 99%

Automated Design Optimization for the P2 and P8 Hypersonic Inlets

Shukla

Gelsey

Schwabacher

et al. 1997

Journal of Aircraft

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An automated design methodology incorporating industry-standard Navier -Stokes codes and a gradient-based optimizer has been developed. This system is used to redesign the well-known NASA P2 and P8 hypersonic inlets. First, the Navier -Stokes simulations of the original P 2 and P8 inlet designs are validated using numerical convergence studies and comparison with wind-tunnel experimental data for the original inlets published by NASA in the early 1970s. Second, the P 2 and P8 inlets are redesigned with the objective of canceling the cowl shock (and, in the case of the P8 inlet, the additional cowlgenerated compression) at the centerbody by appropriate contouring of the centerbody boundary. The original inlets were intended to achieve these same objectives, but detailed experimental measurements indicated that a substantial re ected shock system was present. The choice of the objective function, which is used to drive the optimization, has a signi cant impact on the nal design. Several different formulations for the objective function have been employed, and improvements of 60 -90% in the objective function have been achieved. This automated design system represents one of the rst successful combinations of numerical optimization methods with Reynolds-averaged Navier -Stokes uid dynamics simulation for high-speed inlets, and demonstrates a new area in which high-performance computing may have considerable impact on problems of military and industrial signi cance. Nomenclature

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Section: Optimization Proceduresmentioning

confidence: 99%

Automated Design Optimization for the P2 and P8 Hypersonic Inlets

Shukla

Gelsey

Schwabacher

et al. 1997

Journal of Aircraft

Self Cite

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“…We applied the method to this problem, varying the number of dimensions from 2 to 4 (k =2, 3,4) in order to study the variations in the number of correct cases returned and the number of missed cases not returned by the method.…”

Section: Figure 13: the Aircraft Concept Sizing Problemmentioning

confidence: 99%

Design Optimization Problem Reformulation Using Singular Value Decomposition

Sarkar

Dong

Gero

2009

Journal of Mechanical Design

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This paper presents a design optimization problem reformulation method based on Singular Value Decomposition (SVD), dimensionality reduction, and unsupervised clustering. The method calculates linear approximations of the associative patterns of symbol co-occurrences in a design problem representation to infer induced interaction/coupling strengths between variables and constraints. Unsupervised clustering of these approximations is used to identify useful reformulations. These two components of the method automate a range of reformulation tasks that have traditionally required different solution algorithms. We explain the method using an analytic model-based decomposition problem, and apply the method to an analytic hydraulic cylinder design problem as an example of heuristic design "case" identification, and to non-analytic problems expressed in FDT and DSM forms as examples of design decomposition. An Aircraft Concept Sizing (ACS) problem is used to empirically validate the method's performance. The results show that the method can be used to infer multiple well-formed reformulations starting from a single problem representation in a knowledge-lean and training lean manner.

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“…We summarize it briefly here; it is described in more detail elsewhere [5]. Figure 1 shows a diagram of a typical airplane automatically designed by our software system.…”

Section: Domain Descriptionmentioning

confidence: 99%