Coupling Parametric Aircraft Lofting to CFD &amp; CSM Grid Generation for Conceptual Design

Rizzi, Arthur; Oppelstrup, Jesper; Zhang, Mengmeng; Tomac, Maximillian

doi:10.2514/6.2011-160

Cited by 7 publications

(10 citation statements)

References 4 publications

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“…The RDS link was used to re-visit the Airbus A320 look-alike studied in 26 and with respect to trim and drag divergence in 28 and. 27 The VAMPzero link gives experience of geometry translation and investigates the further development of the CEASIOM ACbuilder to an interactive, graphical editor for CPACS XML files.…”

Section: Cpacs Import and Exportmentioning

confidence: 99%

“…58 As discussed in ? and 27 we have chosen to work with customized in-house and open source software instead. Although the link to generic CAD systems has not been explored in the experiments reported here, CEASIOM models can be handed over to later design phases as IGES files.…”

Section: Export To Generic Cadmentioning

confidence: 99%

“…. Table of analysis disciplines (tools) versus their fidelity for aircraft design according to Nickol 63 The work by Rizzi et al 27 and Zhang 28 on coupling parametric aircraft lofting to CFD and CSM grid generations was carried out in the CEASIOM design environment. The CEASIOM software system developed in the EU-funded collaborative research project SimSAC 5 generates stability and control data for preliminary aircraft design using a choice of numerical methods of varying fidelity.…”

mentioning

confidence: 99%

“…The toolset in CEASIOM is integrated under control by a Matlab 'HUB' routine with information flow through a XML dataset all of which has been cobbled together in a working but rather ad hoc fashion. However, when Rizzi et al 27 extended its functionality by interfacing CEASIOM with Raymer's RDS software, 26 it became evident that the ad hoc XML dataset was not sufficiently general and not well enough structured to offer the extensibility of the system desired for continued development.…”

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confidence: 99%

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Towards a Unified Framework using CPACS for Geometry Management in Aircraft Design

Rizzi

Zhang

Nagel

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The performance requirements for the next generations of airliners are stringent and require invention and design of unconventional configurations departing from the classical Cayley functional decomposition. The break with tradition calls for higher fidelity physicsbased predictions of performance early on in the project. The paper makes the case for a unified, open, data-centric software environment for aircraft design and describes the merge of the CEASIOM conceptual design software package, developed by a number of partners including KTH, with the CPACS formalized data management system developed at DLR. The system provides multi-fidelity and multi-disciplinary analysis capabilities for concurrent design by geographically distributed expert teams. The data-centric architecture uses the CPACS schema and access mechanisms for management of design data across all disciplines and fidelity levels. This makes the system extensible and mitigates the problems encountered in handing over the model to later design phases. The concepts have been tested by interfacing external modules to CEASIOM/CPACS through a graphical CPACS XML editor, the ACbuilder gateway. Results of comparative analyses on models imported in this way from the RDS and VAMPzero conceptual design packages are reported here. CPACS will be released to the general public in spring '12. The CEASIOM team experience of joining forces via CPACS with DLR is altogether positive and further in-house development of software for aircraft performance prediction and design by the CEASIOM team will use the CPACS system. I. Introduction & Overview A. Classical Conceptual-Preliminary DesignPresent trends in aircraft design towards lighter more flexible airframes flying expanded flight envelopes with augmented stability call for more tightly-coupled multi-disciplinary design procedures to efficiently evaluate the flying qualities of the aero-servo-elastic aircraft. Numerous textbooks 1-4 explain in detail how the entire aircraft design process can be categorized into three distinct phases, each with its own distinct objectives and tasks: (1) conceptual definition at the aircraft level; (2) preliminary definition of its components; and (3), detailed definition for flight. The tools and how they are used, and even the people using them, usually change between the phases.Conceptual design is primarily a search process to formulate a set of design variable quantities, which, according to appropriate modeling principles, define a vehicle that fulfills a set of minimum requirements determined by its mission. The tools for the search are provided by mathematical modeling (usually empirically based) to find a quantified description of the aircraft concept and its size, weight, and performance. The first step sizes the aircraft, i.e calculates the aircraft takeoff gross weight, empty weight and fuel weight so that it achieves the range called for in the design specification. This results in a quantification of design parameters that determine the aircraft configuration involvin...

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Section: Cpacs Import and Exportmentioning

confidence: 99%

Section: Export To Generic Cadmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Towards a Unified Framework using CPACS for Geometry Management in Aircraft Design

Rizzi

Zhang

Nagel

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…The structural model for aero-elastic analysis is illustrated by a beam model with point masses (Figure 2(b)). A higher-fidelity shell model can be produced from the CFD-meshed surfaces and information on locations of spars and other important structural members (Rizzi et al, 2011). 2 Aerodynamic module AMB-CFD:…”

Section: Rds Conceptual Design Toolmentioning

confidence: 99%

RDS‐SUMO: from lofting to physics‐based grids

Zhang

Rizzi

2012

Aircraft Engineering and Aerospace Technology

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Purpose -The goal for this paper is to bring the easy-to-use geometry drawing software RDS to a "solid" mesh, which could be analyzed and simulated in CEASIOM, to enhance both CEASIOM and RDS's capabilities. Design/methodology/approach -The RDS-SUMO interface is developed based on the feature that both RDS and SUMO define their geometric model using cross-sectional information, i.e. their "universe" shapes are close to each other. Findings -The translation is automated and allows the engineer to easily modify and augment the geometry in the process. Two test cases are shown, with their high quality Euler mesh and CFD computations. The A321-look-alike test case tests the mesh quality for transonic aerodynamics, such as high-speed trim and drag divergence; the twin-prop asymmetric aircraft is a "diffi+cult" non-conventional configuration analyzed for yaw stability in one-engine out mode.Practical implications -This paper shows that the CFD solutions based on solid grids could be obtained once the design is proposed and the RDS wireframe model is available. The aerodynamic properties can then be predicted in early design stage, which is very efficient for preliminary aircraft design. Originality/value -This fast meshing tool could obtain "working" grids of a new design within hours. Nomenclature SymbolsDefinitions, acronyms and abbreviations CAPRI ¼ computational analysis programming interface RDS ¼ Raymer's design software SUMO ¼ surface modeler software DXF ¼ drawing interchange format CFD ¼ computational fluid dynamics DLM ¼ design layout module CEASIOM ¼ computerized environment for aircraft synthesis and integrated optimisation methods AMB ¼ aerodynamic model builder ACBuilder ¼ aircraft builder NeoCASS ¼ next generation conceptual aero-structural sizing suite SDSA ¼ simulation and dynamic stability analyser S&C ¼ stability and control OEO ¼ one engine out CPACS ¼ the common parametric aircraft configuration schema copyright holder's express written permission. However, users may print, download, or email articles for individual use.

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The case for open source software in aeronautics

Ziemer

Stenz²

2012

Aircraft Engineering and Aerospace Technology

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PurposeThe purpose of this paper is to promote the opportunities of open source software (OSS) development in aeronautics. Using the development of an open source framework for conceptual aircraft design as an example, this paper discusses how an inter‐organizational collaboration between industry and academia can build an environment for multi‐disciplinary aircraft design projects.Design/methodology/approachThe paper takes the form of a literature study and comparison of software tools.FindingsThe open source model can facilitate the emergence of a large inter‐organizational community in aeronautics for developing a comprehensive software framework.Practical implicationsDeveloping a general OSS framework for conceptual aircraft design has the potential of attracting a large community for inter‐organizational collaboration on software tools for a multi‐disciplinary optimization (MDO) environment.Originality/valueUsing the concepts of open source in aeronautics has the potential to improve the collaboration among industry and academia on developing software tools for an MDO environment.

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Coupling Parametric Aircraft Lofting to CFD & CSM Grid Generation for Conceptual Design

Cited by 7 publications

References 4 publications

Towards a Unified Framework using CPACS for Geometry Management in Aircraft Design

Towards a Unified Framework using CPACS for Geometry Management in Aircraft Design

RDS‐SUMO: from lofting to physics‐based grids

The case for open source software in aeronautics

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