A Modern CORBA-Based Approach to Ad Hoc Distributed Process Orchestrations Applied to MDO

Ratcliff, Robert R.; LeDoux, Stephen T.; Herling, W. W.

doi:10.2514/6.2005-7143

Cited by 4 publications

(4 citation statements)

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“…19,20 The multi-disciplinary tool MDOPT is a parallel response surface method that has been applied to complex turbulent aero-structural design problems. 21,22,23 SYN107, OPTIMAS, and MDOPT were applied to a common design problem and their respective performance compared by Epstein et al; 24 the study showed similar improvements in drag at the main design point while satisfying a set of aerodynamic and geometric constraints for all three tools, as well as good performance at off-design conditions.…”

Section: Introductionmentioning

confidence: 90%

Application of an efficient Newton-Krylov algorithm for aerodynamic shape optimization based on the Reynolds-Averaged Navier-Stokes equations

Osusky

Zingg

2013

21st AIAA Computational Fluid Dynamics Conference

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An efficient, high-fidelity numerical aerodynamic shape optimization tool is presented. The algorithm includes an integrated geometry parameterization and mesh movement scheme based on B-spline volumes, an efficient parallel Newton-Krylov-Schur algorithm for solving the three-dimensional Reynolds-Averaged Navier-Stokes (RANS) equations, a discrete-adjoint gradient evaluation, and a gradient-based optimizer which is capable of performing large-scale optimizations subject to linear and nonlinear constraints. Several cases are presented to demonstrate the performance of the algorithm. First, an optimization is performed for a rectangular wing that is initially fit with NACA0012 sections in order to demonstrate the robustness of the mesh movement and flow analysis given substantial changes in the geometry. The optimizer is able to achieve substantial drag reduction at the target lift by altering the camber and by increasing the sweep angle. We then present a study of the wing geometry extracted from the Common Research Model (CRM) wing-body geometry; we consider the CRM wing with a sharp trailing edge, as well as a wing with the same planform, but given NACA0012 sections. Given section and twist design variables, each initial geometry yields an optimized design that demonstrates improved drag compared to the initial shape. The optimizations of the planar wing with NACA0012 sections and the CRM wings were additionally run with an Euler-based algorithm; RANS analyses were performed on the Euler-optimized geometries such that they could be compared directly with the results of the RANS-based optimizations. In the case of the planar wing with NACA0012 sections, which specified a low target lift coefficient, the Euler-based optimizer produced a very similar design which yielded the same drag coefficient as the RANS-based optimization. However, the CRM study shows that the RANS-based optimizations result in designs with much lower drag compared to the Eulerbased optimizations. We conclude that, in general, viscous and turbulent effects should be taken into account when performing aerodynamic shape optimization.

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Section: Introductionmentioning

confidence: 90%

Application of an efficient Newton-Krylov algorithm for aerodynamic shape optimization based on the Reynolds-Averaged Navier-Stokes equations

Osusky

Zingg

2013

21st AIAA Computational Fluid Dynamics Conference

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“…As can be seen from [16], many robotic middlewares aim at not only improving the reusability and flexibility but also at decoupling robotic software design and implementation through modular structure platforms and component-based development approaches, such as Orocos, Orca, OpenRTMaist (that is the implementation of RT-Middleware), MARIE, SmartSoft, etc. In the distributed system domain, the distributed computing middleware CORBA has been widely used to address the challenges of heterogeneity, network-centric operation and dynamic operating conditions [17], [18], [19], [20]. Its interfaces are used at mission control centers for spacecraft operations [21], [22].…”

Section: Related Workmentioning

confidence: 99%

A Component-Based Middleware for a Reliable Distributed and Reconfigurable Spacecraft Onboard Computer

Peng

Höflinger

Weps

et al. 2016

2016 IEEE 35th Symposium on Reliable Distributed Systems (SRDS)

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Emerging applications for space missions require increasing processing performance from the onboard computers. DLR's project "Onboard Computer-Next Generation" (OBC-NG) develops a distributed, reconfigurable computer architecture to provide increased performance while maintaining the high reliability of classical spacecraft computer architectures. Growing system complexity requires an advanced onboard middleware, handling distributed (real-time) applications and error mitigation by reconfiguration. The OBC-NG middleware follows the Component-Based Software Engineering (CBSE) approach. Using composite components, applications and management tasks can easily be distributed and relocated on the processing nodes of the network. Additionally, reuse of components for future missions is facilitated. This paper presents the flexible middleware architecture, the composite component framework, the middleware services and the model-driven Application Programming Interface (API) design of OBC-NG. Tests are conducted to validate the middleware concept and to investigate the reconfiguration efficiency as well as the reliability of the system. A relevant use case shows the advantages of CBSE for the development of distributed reconfigurable onboard software.

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“…Parallelization of the optimization process was implemented within most domains, providing a capability to use large-scale multiple-CPU computing platforms in a computationally efficient manner. The Interdomain Communication Facility (ICF) maintains the underlying process control [24]. It is constructed using TCL1 scripts, the MICO2 CORBA Orb, and the Combat3 TCL to CORBA4 Bridge.…”

Section: B Optimization Tool Mdoptmentioning

confidence: 99%

Comparative Study of Three-Dimensional Wing Drag Minimization by Different Optimization Techniques

Epstein

Jameson

Peigin

et al. 2009

Journal of Aircraft

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The main goal of this paper is to document a comparative study of different computational-fluid-dynamics-based optimization techniques applied to the solution of a three-dimensional wing drag minimization problem. To achieve this objective, three optimization tools were used: SYN107 (Intelligent Aerodynamics International), MDOPT (The Boeing Company), and OPTIMAS (Israel Aerospace Industries). The first tool employs gradient-based search techniques using the continuous adjoint equation, the second one is a response-surface method, and the last one uses a floating-point genetic algorithm as its search engine. As the starting geometry, the public domain DPW-W1 wing (a test case for the Third AIAA Drag Prediction Workshop) was used. The comparisons included herein are provided in three stages: cross analysis of the initial geometry by the computational fluid dynamics tools employed in the optimizations, optimization of the initial geometry to minimum drag, and cross analysis of optimal shapes achieved by the optimization tools using all computational fluid dynamics tools employed. The cross analysis also includes results from an independent computational fluid dynamics method that was not used in any of the optimization efforts. These results help quantify the level of variation that is inherent in, and can be expected from, application of the current state-of-the-art aerodynamic optimization methods. The present work may be regarded as a move toward the construction of reliable test cases for an aerodynamic shape optimization problem. Another goal of this collaborative investigation is to collect lessons learned from this pilot project to help develop a model for an aerodynamic optimization workshop.

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A Modern CORBA-Based Approach to Ad Hoc Distributed Process Orchestrations Applied to MDO

Cited by 4 publications

References 1 publication

Application of an efficient Newton-Krylov algorithm for aerodynamic shape optimization based on the Reynolds-Averaged Navier-Stokes equations

Application of an efficient Newton-Krylov algorithm for aerodynamic shape optimization based on the Reynolds-Averaged Navier-Stokes equations

A Component-Based Middleware for a Reliable Distributed and Reconfigurable Spacecraft Onboard Computer

Comparative Study of Three-Dimensional Wing Drag Minimization by Different Optimization Techniques

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