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Design of a canard configured TransCruiser using CEASIOM
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics.
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2011 (English)In: Progress in Aerospace Sciences, ISSN 0376-0421, E-ISSN 1873-1724, Vol. 47, no 8, 695-705 p.Article, review/survey (Refereed) Published
Abstract [en]

CEASIOM is a multidisciplinary software environment for aircraft design that has been developed as part of the European Framework 6 SimSAC project. It closely integrates discipline-specific tools such as those used for CAD, grid generation, CFD, stability analysis and control system design. The environment allows the user to take an initial design from geometry definition and aerodynamics generation through to full six degrees of freedom simulation and analysis. Key capabilities include variable fidelity aerodynamics tools and aeroelasticity modules. The purpose of this paper is to demonstrate the potential of CEASIOM by presenting the results of a Design, Simulate and Evaluate (DSE) exercise applied to a novel, project specific, transonic cruiser configuration called the TCR. The baseline TCR configuration is first defined using conventional methods, which is then refined and improved within the CEASIOM software environment. A wind tunnel model of this final configuration was then constructed, tested and used to verify the results generated using CEASIOM.

Place, publisher, year, edition, pages
2011. Vol. 47, no 8, 695-705 p.
Keyword [en]
Aircraft design, Aerodynamics, Flight dynamics, Flight control, CFD, Simulation
National Category
Engineering and Technology
URN: urn:nbn:se:kth:diva-61003DOI: 10.1016/j.paerosci.2011.08.011ISI: 000298126800010ScopusID: 2-s2.0-81155137799OAI: diva2:478471
QC 20120116Available from: 2012-01-16 Created: 2012-01-16 Last updated: 2015-05-28Bibliographically approved
In thesis
1. Contributions to Variable Fidelity MDO Framework for Collaborative and Integrated Aircraft Design
Open this publication in new window or tab >>Contributions to Variable Fidelity MDO Framework for Collaborative and Integrated Aircraft Design
2015 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

The thesis develops computational tools for early stages of the aircraft design process. The work focuses on a framework which allows several design teams concurrently to develop a baseline concept into a configuration which meets requirements and whose aerodynamics has been assessed by flight simulation. To this end, a data base format suggested by the German Aerospace Center DLR was adopted in the CEASIOM system, developed in the EU 6th Framework Program, enabling more accurate transonic analysis and tabulation of forces and moments as well as control surface authority assessment. Results from simple, fast models are combined with computationally expensive full CFD results by co-Kriging to speed up productionof the aero-data for flight simulation.

Non-linear optimization methods in wing design play an increasingly important role together with computational aerodynamics. High performance computing enables the use of high-fidelity non-linear flow predictions in optimization loops. It is argued that the optimization tools should allow the engineer to influence the process by setting up suitable target pressure distributions for the shape to approach, combined with steps to minimize drag under suitable constraints on geometry, forces, and moments. The simulation framework incorporated into CEASIOM was applied to a number of configurations, conventional as well as un-conventional, such as an a-symmetric twin prop, a canard-configured transonic cruiser, and a novel chinrudder concept for transonic airliners. Aerodynamic shape design by the developed methods was applied to the standard M6 benchmark wing, a joined-wing concept, a wing-tip, and a blended wing-body.

Abstract [sv]

Avhandlingen utvecklat beräkningsmoduler för tidiga stadier i flygplanskonstruktionsprocessen. Arbetet kocentreras på ett program-ramverk som låter flera designteam samtidigt utveckla en grund-modell till en konfiguration som uppfyller ställda krav och vars aerodynamik har undersökts med flygsimulering. För att nå detta mål antogs ett data-bas format utarbetat av DLR (German Aerospace Center) i CEASIOM-programpaketet som utvecklats i EUs sjätte ramprogram. Det möjliggjorde noggrannare analys och framtagning av tabeller över krafter och moment liksom bedömning av styrytors funktion i transoniskt fartområde. Resultat från enkla, snabba beräknngsmodeller kombineras via co-Kriging med beräkningsmässigt dyra CFD-körningar för att snabbt ta fram aero-data som behövs för flygsimuleringen.

Icke-linjär optimering spelar allt större roll i ving-formgivning, tillsammans med numerisk aerodynamik. Högpresterande datorer medger användning av noggranna icke-linjära strömningsmodeller också i optimerings-slingor. Det argumenteras för att optimerings-verktygen skall ge ingenjörerna direkt inflytande över processen genom definition av fördelaktiga tryckfördelningar som vingformen ska åstadkomma, kombinerat med steg som minimerar luftmotstånd under bivillkor på geometri, krafter och moment.

Simulerings-ramverket implementerat i CEASIOM tillämpas så på ett antal konfigurationer, konventionella såväl som o-konventionella: ett osymmetriskt tvåmotorigt propellerplan, och större transoniska flygplan, ett för Mach 0.97 med canardvinge, och ett nytt koncept med hak-roder.

Aerodynamisk formgivning med de utvecklade metoderna tillämpas på standardfallet M6-vingen, en transonisk dubbel-vinge, en vingtipp, och en flygande vinge.

Place, publisher, year, edition, pages
Stockholm: KTH Royal Institute of Technology, 2015. xx, 101 p.
TRITA-AVE, ISSN 1651-7660 ; 2015:27
National Category
Aerospace Engineering
Research subject
Aerospace Engineering
urn:nbn:se:kth:diva-168169 (URN)978-91-7595-606-0 (ISBN)
Public defence
2015-06-12, F3, Lindstedtsvägen 26, KTH, Stockholm, 10:15 (English)

QC 20150528

Available from: 2015-05-28 Created: 2015-05-27 Last updated: 2015-05-28Bibliographically approved

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