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Numerical investigation into flight dynamics of an agile aircraft

Autorzy
Treść / Zawartość
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
The aim of this study is to prove practical applicability of a numerical simulation technique in highlights some of the features of the flight under extreme conditions. dynamics of spatial motion of an agile aircraft is considered. After a brief description of an aircraft mathematical model, the numerical analyses are presented. There have been considered various flight events (such as airdrop or aircraft accident) and manoeuvres (in particular, those performed at high angles of attack).
PL
Numeryczne badanie dynamiki lotu samolotów o podwyższonej sterowności. Rozpatrzono dynamikę samolotu o podwyższonej sterowności. Badania prowadzono stosując symulację komputerową. Zaprezentowano wyniki dynamiki ruchu samolotu w różnych stanach lotu i manewrach.
Rocznik
Strony
167--187
Opis fizyczny
Bibliogr. 30 poz., rys.
Twórcy
autor
  • Military University of Technology, Warsaw
Bibliografia
  • 1. CAO J., GARRETT F. JR., HOFFMAN F., STAFFORD H., 1990, Analytical Aerodynamic Model of a High Alpha Research Vehicle Wind-Tunnel Model, NASA-CR 187469.
  • 2. DAT R., TRAN C.T., PETOT D., 1979, Modèle Phénoménologique de Décrochage Dynamique sur Profil de Pale d'Hélicoptère, ONERA T. P. No. 1979-149.
  • 3. Duc J.M., VERGNE M., 1987, Retrospective de Récents Symposiums Agard Sous l'Angle de la Manoeuvrabile des Avions de Combat, AGARD-CP-319.
  • 4. DZYGADLO Z., BOLDAK R., 1985, Numerical Modelling of the Dynamics of Aerobatics Manoeuvres, Journal of Technical Physics, 26, 2.
  • 5. DZYGADLO Z., KOWALECZKO G., SlBILSKi K., 1996, Method of Control of a Streaked Wing Aircraft For Cobra Manoeuvres, ICAS-96-3.7.4, Proceedings 20th WAS Congress, 1566-1573.
  • 6. DZYGADLO Z., SlBILSKi K., 1988, Dynamics of Spatial Motion of an Aeroplane After Drop of Loads, Journal of Technical Physics, 29, 3, 399-415.
  • 7. DZYGADLO Z., SIBILSKI K., 1990, Analysis of Aircraft Flight Dynamics After Failure of the Tailplane, Bulletin of the Military University of Technology, 40, 11, 95-111.
  • 8. GAJDA J., 1990, Application of Quaternions in Algorithms of the Spatial Orientation of Moving Objects, Journal of Theoretical and Applied Mechanics, 28, 3-4, 583-592.
  • 9. GOLDIEZ B., KUO-CHI LIN, 1991, The Orientation in the Representation in the Draft Military Standard for Disturbed Interactive Simulation, AIAA Flight Simulation Technologies Conference, AIAA-91-2944-CP.
  • 10. GORAJ Z., PIETRUCHA J., 1995, Classical Panel Methods: A Routine Tool for Aerodynamic Calculations of Complex Configurations: From Concepts to Codes, Journal of Theoretical and Applied Mechanics, 33, 4, 47-66.
  • 11. GOSZCZYŃSKI J., MARYNIAK J., NIEPSUJ P., 1996, Simulation as Used to Study Aircraft 3-D Motion with Euler Co-Ordinates to Describe Kinematics Relations, Bulletin of the Air Force Fesearch Institute, 334, 101-110.
  • 12. GUGLIERI G., QUAGLIOTTI F.B., 1994, Static and Oscillatory Tests on a Generic Combat Aircraft Model in Flow Speed Wind Tunnel, ICAS-94-3.6.1, Proceedings 19th WAS Congress, 1940-1949.
  • 13. HERBST W.B., 1980, Dynamics of Air Combat, Journal of Aircraft, 20, 7.
  • 14. KATZ J., PLOTKIN A., 1991, Low-Speed Aerodynamics. From Wing Theory to Panel Methods, McGraw-Hill, N.Y.
  • 15. MARTINA A.P., 1947a, Method for Calculating the Rolling and Yawing Moments Due to Rolling for Unswept Wings with and Without Flaps or Ailerons by Use of Non-Linear Lift Data, NACA TR 1167.
  • 16. MARTINA A.P., 1947b, Method of Calculating Lift Distribution for Unswept Wings With Flaps and Ailerons by Use of Non-Linear Section Lift Data, NACA TR 1090.
  • 17. MARYNIAK J., 1975, Dynamic Theory of Mobile Objects, Scientific Works of Warsaw University of Technology, Mechanics, 45, Warsaw.
  • 18. NARKIEWICZ J., 1994, Rotorcraft Aeromechanical and Aeroelastic Stability, Scientific Works of Warsaw University of Technology, Mechanics, 158, Warsaw
  • 19. NARKIEWICZ J., SYRYCZYŃSKI J, BATLER T., 1993, Circulation ONERA Model for Dynamic Airfoil Stall, Transactions of Institut of Aviation, 1/2, 132-133.
  • 20. O'LEARY CO., WEIR B., WALKER J.M., 1996, Static and Forced Oscillation Tests on a Generic Combat Aircraft Model, Proceedings 20th ICAS Congress, ICAS-96-1.8.3, 1768-1778.
  • 21. PAINLAVE P., BOREL E., 1911, Theorie und Praxis der Flugmechanik, Richard Carl Schmigt & Co, Berlin.
  • 22. ROM J., 1992, High Angle of Attack Aerodynamics, Subsonic, Transonic and Supersonic, Springer-Verlag.
  • 23. Samoliot MiG-29, Rukovodstvo po Tekhnicheskoi Ekspluatacli (The MiG-29 Figther Aircraft Technical Exploitatiom Manual), 1983.
  • 24. Samoliot Su-22 UM3K, Rukovodstvo po Tekhnicheskoi Ekspluatacli; Kniga 1-Osnovnye kharakterystiki (The Su-22UM3K Aircraft Technical Exploitation Manual, Vol. 1 Basic Aerodynamic Characteristics), 1978.
  • 25. SAMOYLOVICH 0., 1997, Aerodynamic Configuration of Contemporary and Perspective Fighters, Proceedings of the Second Seminar on RRDPAE'96, Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, Research Bulletin, 7, 233-244.
  • 26. SlBILSKi K., 1996, Modelling of Aeroplane Dynamics in Extreme Flight Conditions, Proceedings 20th ICAS Congress, ICAS-96-3.7.2, 1547-1557.
  • 27. SIBILSKI K., 1997a, Numerical Investigations of Aircraft Dynamics During Transgression of Several Limits of Usage, Bulletin of the Military University of Technology, 46, 6, 89-111.
  • 28. SIBILSKI K., 1997b, Some thoughts on Mathematical Models for Aircraft Accidents Simulation, Proceedings of International Aviation Safety Conference, IASC'97, H. Soekha (edit.), VSP Publishing Company, Utrecht, The Netherlands, 675-694.
  • 29. SIBILSKI K., 1998a, Method for Calculating Wing aerodynamic Loads by Lifting Line Theory Using Non-Linear and Non-Stationary Airfoil Characteristics, Proc. 8th Conference "Mechanics in Aviation ML-VIH", 405-417.
  • 30. SIBILSKI K., 1998b, Modelling of High Augmented Aircraft Dynamics, Military University of Technology, Warsaw.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-BWM2-0009-0054
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