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A Fast MDO tool for Aeroelastic Optimization in Aircraft Conceptual Design
Dipartimento di Ingegneria Aerospaziale, Politecnico di Milano.
Dipartimento di Ingegneria Aerospaziale, Politecnico di Milano.
Dipartimento di Ingegneria Aerospaziale, Politecnico di Milano.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics.
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2008 (English)Conference paper, Published paper (Other academic)
Abstract [en]

This paper presents a design tool based on computational methods for the aero-structural analysis and optimization of aircraft layouts at the conceptual design stage. The whole methodology is based upon the integration of geometry construction, aerodynamic and structural analysis codes that combine depictive, computational, analytical, and semiempirical methods, validated in an aircraft design environment. The two primary modules are presented: CADac (Computer Aided Design Aircraft) for parametric geometry handling and NeoCASS (Next generation Conceptual Aero-Structural Sizing Suite) for structural sizing and numerical aeroelastic analysis. The aero-structural numerical kernel enables the creation of efficient low-order, high fidelity models which makes particularly suitable to be succesfully used within an MDO framework to drive the optimization tool into the most appropriate direction. Indeed, solving adverse aeroelastic issues like divergence, control surfaces reversal, flutter, increased drag at cruise speed due to structural deformability may require considerable changes in the structural design, limitations in flight envelope or weight penalties. The late discovery of this type of issues may result in significant cost increases and, in some cases, it may even require to actually close the project. In order to overcome the insurgence of these issues, the influence of deformability on flight and handling performances, on structural weight and on design costs needs to be taken into account as early as possible in the design process.

Place, publisher, year, edition, pages
2008. AIAA-2008-5911- p.
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-9277Scopus ID: 2-s2.0-78049525231OAI: oai:DiVA.org:kth-9277DiVA: diva2:54412
Conference
12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference
Note
QC 20101104Available from: 2008-10-16 Created: 2008-10-16 Last updated: 2010-11-04Bibliographically approved
In thesis
1. Method Development for Computer Aided Engineering for Aircraft Conceptual Design
Open this publication in new window or tab >>Method Development for Computer Aided Engineering for Aircraft Conceptual Design
2008 (English)Licentiate thesis, comprehensive summary (Other scientific)
Abstract [en]

This thesis presents the work done to implement new computational tools and methods dedicated to aircraft conceptual design sizing and optimization. These tools have been exercised on different aircraft concepts in order to validate them and assess their relevance and applicability to practical cases. First, a geometry construction protocol has been developed. It is indeed essential to have a geometry description that supports the derivation of all discretizations and idealizations used by the different analysis modules (aerodynamics, weights and balance, stability and control, etc.) for which an aircraft concept is evaluated. The geometry should also be intuitive to the user, general enough to describe a wide array of morphologies and suitable for optimization. All these conditions are fulfilled by an appropriate parameterization of the geometry. In addition, a tool named CADac (Computer Aided Design aircraft) has been created in order to produce automatically a closed and consistent CAD solid model of the designs under study. The produced CAD model is easily meshable and therefore high-fidelity Computational Fluid Dynamics (CFD) computations can be performed effortlessly without need for tedious and time-consuming post-CAD geometry repair.Second, an unsteady vortex-lattice method based on TORNADO has been implemented in order to enlarge to scope of flight conditions that can be analyzed. It has been validated satisfactorily for the sudden acceleration of a flat plate as well as for the static and dynamic derivatives of the Saab 105/SK 60.Finally, a methodology has been developed to compute quickly in a semi-empirical way the buffet envelope of new aircraft geometries at the conceptual stage. The parameters that demonstrate functional sensitivity to buffet onset have been identified and their relative effect quantified. The method uses a combination of simple sweep theory and fractional change theory as well as the buffet onset of a seed aircraft or a provided generic buffet onset to estimate the buffet envelope of any target geometry. The method proves to be flexible and robust enough to predict within mainly 5% (and in any case 9%) the buffet onset for a wide variety of aircrafts, from regional turboprop to long-haul wide body or high-speed business jets.This work was done within the 6th European framework project SimSAC (Simulating Stability And Control) whose task is to create a multidisciplinary simulation environment named CEASIOM (Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods), oriented toward stability and control and specially suited for aircraft conceptual design sizing and optimization.

Place, publisher, year, edition, pages
Stockholm: KTH, 2008. ix, 37 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2008-57
Keyword
Aircraft conceptual design, Computer Aided Design (CAD), buffet onset, unsteady vortex-lattice method
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-9240 (URN)978-91-7415-137-4 (ISBN)
Presentation
2008-10-27, S 40, Teknikringen 8, Stockholm, 15:15 (English)
Opponent
Supervisors
Projects
SimSAC
Note
QC 20101104Available from: 2008-10-14 Created: 2008-10-10 Last updated: 2010-11-04Bibliographically approved

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  • apa
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