Change search
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf
Enhancement of CEASIOM with Rapid-Meshing Tool for Aircraft Conceptual Design
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics. (flygteknik)ORCID iD: 0000-0003-4991-5503
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics.
2012 (English)In: The journal of Aerospace Science, Technology and Systems, Vol. 91, no 3/4, 79-85 p.Article in journal (Refereed) Published
Abstract [en]

This paper details the development and application of the RDS-SUMO-CEASIOM-EDGE rapid-CFD tool. It uses theRDS CAD model as geometry for automated meshing and CFD analysis to produce an aero-data base for control andstability analysis. It is applied to two non-conventional design proposals, an asymmetric twin-prop aircraft and anairliner with rear Open Rotor propulsion, retractable canard, and a “chin-rudder” instead of vertical tail. For bothconfigurations,yaw control is problematic, and the stability and control analysis is used to assess control surface sizing and stabilityaugmentation system.

Place, publisher, year, edition, pages
Associazione italiana di Aeronautica e Astronautica , 2012. Vol. 91, no 3/4, 79-85 p.
National Category
Aerospace Engineering
Research subject
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-168157OAI: oai:DiVA.org:kth-168157DiVA: diva2:814525
Note

QC 20150527

Available from: 2015-05-27 Created: 2015-05-27 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.
Series
TRITA-AVE, ISSN 1651-7660 ; 2015:27
National Category
Aerospace Engineering
Research subject
Aerospace Engineering
Identifiers
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)
Opponent
Supervisors
Projects
SimSACNOVEMOR
Note

QC 20150528

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

Open Access in DiVA

fulltext(3025 kB)92 downloads
File information
File name FULLTEXT01.pdfFile size 3025 kBChecksum SHA-512
60faf65635d77b36371a252689fb2e2a8036e2ccecc75fbe860bbfc242231e8ed4ee5ff9071da759dc1d47b37a64069596f937c80c0f49ac758041c5e1eff254
Type fulltextMimetype application/pdf

Search in DiVA

By author/editor
Mengmeng, ZhangRizzi, Arthur
By organisation
Aerodynamics
Aerospace Engineering

Search outside of DiVA

GoogleGoogle Scholar
Total: 92 downloads
The number of downloads is the sum of all downloads of full texts. It may include eg previous versions that are now no longer available

urn-nbn

Altmetric score

urn-nbn
Total: 115 hits
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf