Abstract

The advantages of multidisciplinary design are well understood, but not yet fully adopted by the industry where methods should be both fast and reliable. For such problems, minimum computational cost while providing global optimality and extensive design information at an early conceptual stage is desired. However, such a complex problem consisting of various objectives and interacting disciplines is associated with a challenging design space. This provides a large pool of possible designs, requiring an efficient exploration scheme with the ability to provide sufficient feedback early in the design process. This paper demonstrates a generalized optimization framework with rapid design space exploration capabilities in which a Multifidelity approach is directly adjusted to the emerging needs of the design. The methodology is developed to be easily applicable and efficient in computationally expensive multidisciplinary problems. To accelerate such a demanding process, Surrogate Based Optimization methods in the form of both Radial Basis Function and Kriging models are employed. In particular, a modification of the standard Kriging approach to account for Multifidelity data inputs is proposed, aiming to increasing its accuracy without increasing its training cost. The surrogate optimization problem is solved by a Particle Swarm Optimization algorithm and two constraint handling methods are implemented. The surrogate model modifications are visually demonstrated in a 1D and 2D test case, while the Rosenbrock and Sellar functions are used to examine the scalability and adaptability behaviour of the method. Our particular Multiobjective formulation is demonstrated in the common RAE2822 airfoil design problem. In this paper, the framework assessment focuses on our infill sampling approach in terms of design and objective space exploration for a given computational cost.

Highlights

  • Following several decades of continuous development, the aerodynamic design of conventional aircraft configurations has matured; seemingly reaching a plateau

  • A typical application of this decomposition within an Surrogate Based Optimization (SBO) framework Jones (2001) is the trust region Demange et al (2016a, b), Jarrett and Ghisu (2015) approach involving the generation of a locally accurate error surrogate to correct the Low Fidelity (LF) value according to eq

  • The airfoil design problem described above, allowed to assess how our proposed sampling method behaved. This was done through a comparison of the standard MO Expected Improvement (EI) methodology for improving the pareto front (see Forrester et al (2008) and Eq 33 from “Appendix A” for more details), against our parallel infill EI methodology of Sect. 2.2. This is within the scope of the demonstration included in this paper; further comparisons between our method and other Kriging/Co-Kriging-based ones, constraints handling approach and LF tool impact are provided in a follow-up paper

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Summary

Introduction

Following several decades of continuous development, the aerodynamic design of conventional aircraft configurations has matured; seemingly reaching a plateau. Development is achieved through many small and slow disciplinary improvements while—still as a typical industrial practice—a leading discipline dictates the design of the rest of them. This approach results to an inferior performance in terms of efficiency of the subsystems (due to the dominant discipline constraints) but in terms of overall system performance as well. Surpassing the current performance plateau requires a re-definition of the way conceptual and preliminary design is performed in order to take advantage of the synergy between the disciplines. A demonstration of this is found in the superiority of aerostructural wing design over aerodynamic wing design Chittick and Martins (2009)

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