Advertisement

Multiple Discipline Take-Off Weight Minimization for a Supersonic Transport Aircraft

  • U. Herrmann
Conference paper
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) book series (NNFM, volume 96)

Abstract

Starting from a mixed fidelity multiple discipline analysis process for high-speed transport aircraft, a multiple discipline optimisation scenario is set-up aiming to obtain minimum weight configurations. A new, more realistic objective function driving the optimisation is implemented. A realistic flight mission for a supersonic transport aircraft (from take-off to landing) is modelled using that process. For supersonic cruise conditions -were most flight time is spent-the disciplines aerodynamics and structures are modelled at high fidelity while other contributing disciplines and flight phases are modelled less accurate. For a generic long-range mission the impact of the supersonic cruise-speed on the minimal take-off weight (enabling to cruise this long range mission) is addressed.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. [1]
    Herrmann, U., CISAP: ”Cruise Speed impact on Supersonic Aircraft Planform-a Project Overview”, AIAA 2004–4539, 10th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Albany, New York, 2004.Google Scholar
  2. [2]
    Laban, M., ”Multi-Disciplinary Analysis and Optimization of Supersonic Transport Aircraft Wing Planforms”, 10th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Albany, New York, AIAA 2004–4542, 2004.Google Scholar
  3. [3]
    Torenbeek, E., Jesse, E., Laban, M., ”Conceptual design of a Mach 1.6 European Commercial Transport”, AIAA 2004–4541, 10th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Albany, New York, 2004.Google Scholar
  4. [4]
    Synaps Ingenieur-Gesellschaft mbH, SynapsPointer Pro V2.50, Synaps Ingenieur-Gesellschaft mbH, Bremen, Germany, 2002.Google Scholar
  5. [5]
    MSC.NASTRAN 2001 Quick Reference Guide, MSC.Software Corporation, USA, 2002, www.mscsoftware.com.Google Scholar
  6. [6]
    Rowan, T. H., ”Functional Stability Analysis Of Numerical Algorithms”, Ph.D. Thesis, Department of Computer Sciences, University of Texas at Austin, USA, May 1990.Google Scholar
  7. [7]
    Brodersen, O., M. Hepperle, A. Ronzheimer, C.-C. Rossow and B. Schöning, ”The Parametric Grid Generation System MegaCads” In: Soni, B.K., J.F. Thompson, J. Häuser and P. Eisemann (Ed.): ”5th International Conference on Numerical Grid Generation in Computational Field Simulation”. National Science Foundation (NSF), 1996, pp. 3535–3562. http://www.megacads.dlr.deGoogle Scholar
  8. [8]
    Kroll, N., C.-C. Rossow, K. Becker and F. Thiele, ”MEGAFLOW-A Numerical How Simulation System”, Aerospace Science Technology, Vol. 4, pp. 223–237, 2000.zbMATHCrossRefGoogle Scholar
  9. [9]
    Herrmann, U., ”MDO Design and Aerodynamic Off-Design Analysis of a Mach=1.6 Aircraft”, Paper 17 of the KATnet/CEAS Conference, 20–22 June 2005, Bremen, Germany.Google Scholar
  10. [10]
    Herrmann, U., Frhr. von Geyr, H., Werner-Westphal, Ch.: ”Mixed Fidelity Multi Discipline Optimization of a Supersonic Transport Aircraft”, AIAA 2005-534, 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, Jan. 2005.Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2007

Authors and Affiliations

  • U. Herrmann
    • 1
  1. 1.Institute of Aerodynamics and Flow TechnologyDLRBraunschweigGermany

Personalised recommendations