PL EN


Preferencje help
Widoczny [Schowaj] Abstrakt
Liczba wyników
Tytuł artykułu

Influence of flight control law on spin dynamics of aerodynamically asymmetric aircraft

Treść / Zawartość
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
In this paper, we analyze the spin dynamics of an aerodynamically asymmetric aircraft in open-loop configuration and also evaluate the performance of gain scheduled flight control law in improving dynamic characteristics of aircraft spin. A look-up tables based aerodynamic model is developed from static, coning and oscillatory coning rotary balance wind tunnel test data. As a starting point, all possible steady spin modes are identified by solving the aircraft dynamic model comprising moment equations. The influence of high-alpha yawing moment asymmetry on predicted right and left spin modes is discussed. Six degree of freedom simulations of left and right flat spins are performed in open-loop and closed-loop configurations with the flight control law. Our studies reveal that large amplitude oscillations in the angle of attack and sideslip observed in the open-loop configuration are significantly damped by the control law. The control law reduces the recovery time of the left flat spin. However, the aircraft natural tendency to rotate rightwards due to yawing moment asymmetry at high angles of attack renders flight control law ineffective in aiding the recovery of the right flat spin.
Rocznik
Strony
963—975
Opis fizyczny
Bibliogr. 26 poz., rys., tab.
Twórcy
autor
  • Avionics Department, Institute of Avionics and Aeronautics, Air University, Islamabad, Pakistan
autor
  • Department of Avionics Engineering, CAE, NUST, Rislapur, Pakistan
autor
  • Mechanical Engineering Department, Institute of Avionics and Aeronautics, Air University, Islamabad, Pakistan
Bibliografia
  • 1. Abramov N., Goman M., Khrabrov A.N., 2004, Aircraft dynamics at high incidence flight with account of unsteady aerodynamic effects, AIAA Atmospheric Flight Mechanics Conference and Exhibit, Rhode Island
  • 2. Abzug M.J., Larrabee E.E., 2005, Airplane Stability and Control: a History of the Technologies that Made Aviation Possible, Cambridge University Press, England
  • 3. Bergmann A., 2009, Modern wind tunnel techniques for unsteady testing–development of dynamic test rigs, [In:] Hermann Schlichting – 100 Years, R. Radespiel, C.-C. Rossow, B.W. Brinkmann (Edit.), Springer Berlin Heidelberg, 59-77
  • 4. Bihrle W., 1990, Use of rotary balance data in the prediction of aircraft dynamics, AGARD Advisory Report, No. 265, 188-208
  • 5. Bihrle W., Barnhart B., 1983, Spin prediction techniques, Journal of Aircraft, 2, 97-101
  • 6. Bryan, Hartley G., 1911, Stability in Aviation: An Introduction to Dynamical Stability as Applied to the Motions of Aeroplanes, Macmillan and Co. Limited
  • 7. Cobleigh B.R., 1994, High angle of attack yawing moment asymmetry of the X-31 aircraft from flight test, NASA Contractor Report 186030, 1-36
  • 8. Crespo L.G., Matsutani M., Annaswamy A.M., 2012, Design of an adaptive controller for a remotely operated air vehicle, Journal of Guidance, Control, and Dynamics, 2, 406-422
  • 9. Ghoreyshi M., Jirasek A., Cummings R.M., 2014, Reduced order unsteady aerodynamic modeling for stability and control analysis using computational fluid dynamics, Progress in Aerospace Sciences, 71, 167-217
  • 10. Gill S.J., Lowenberg M.H., Neild S.A., Crespo L.G., Krauskopf B., Puyou G., 2015, Nonlinear dynamics of aircraft controller characteristics outside the standard flight envelope, Journal of Guidance, Control, and Dynamics, 12, 2301-2308
  • 11. Hewsom R., 2005, Sino-Pakistani fighter improved, Jane’s Defense Weekly, 99-100
  • 12. Ignatyev D.I., Khrabrov A.N., 2015, Neural network modeling of unsteady aerodynamic characteristics at high angles of attack, Aerospace Science and Technology, 41, 106-115
  • 13. Jin L., Nong C., Yuhui S., Jing H., Ke X., 2015, New dynamic stability rig for tri-sonic wind-tunnel, Procedia Engineering, 99, 1591-1596
  • 14. Khrabrov A., Sidoryuk M., Goman M., 2013, Aerodynamic model development and simulation of airliner spin for upset recovery, Progress in Flight Physics, 5, 621-636
  • 15. Kolesnikov E., Goman M., 2012, Analysis of aircraft nonlinear dynamics using non-gradient based numerical methods and attainable equilibrium sets, AIAA Atmospheric Flight Mechanics Conference, Minnesota
  • 16. Luchtenburg D.M., Rowley C.W., Lohry M.W., Martinelli L., Stengel R.F., 2015, Unsteady high-angle-of-attack aerodynamic models of a generic jet transport, Journal of Aircraft, 3, 890-895
  • 17. Murch A.M., Foster J.V., 2007, Recent NASA research on aerodynamic modeling of post-stall and spin dynamics of large transport airplanes, 45th AIAA Aerospace Sciences Meeting and Exhibit, Nevada
  • 18. Pamadi B.N., 2004, Performance, Stability, Dynamics, and Control of Airplanes, AIAA Education Series, USA
  • 19. Paranjape A.A., Ananthkrishnan N., 2010, Analytical criterion for aircraft spin susceptibility, Journal of Aircraft, 5, 1804-1807
  • 20. Paul R., Gopalarathnam A., 2012, Simulation of flight dynamics with an improved post-stall aerodynamics model, AIAA Atmospheric Flight Mechanics Conference, Minnesota
  • 21. Raghavendra P.K., Sahai T., Kumar P.A., Chauhan M., Ananthkrishnan N., 2005, Aircraft spin recovery, with and without thrust vectoring, using nonlinear dynamic inversion, Journal of Aircraft, 6, 1492-1503
  • 22. Sibilski K., Wróblewski W., 2012, Prediction of aircraft spin characteristics by continuation and bifurcation methods, AIAA Atmospheric Flight Mechanics Conference, Minnesota
  • 23. Slotine J.J., Li W., 1991, Applied Nonlinear Control, Prentice Hall, Engle-wood Cliffs, New Jersey
  • 24. Tischler M.B., Barlow J.B., 1981, Determination of the spin and recovery characteristics of a general aviation design, Journal of Aircraft, 4, 238-244
  • 25. Wang Q., Qian W., He K., 2015, Unsteady aerodynamic modeling at high angles of attack using support vector machines, Chinese Journal of Aeronautics, 3, 659-668
  • 26. Zhang J., Tang Y.K., Sun H.S., Liu Z.T., 2015, Dynamic test experiment system of single degree of freedom of ∅3.2 m wind tunnel, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 7, 1300-1309
Uwagi
Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017)
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-23ef4939-f696-4311-9eab-231539fb8ac1
JavaScript jest wyłączony w Twojej przeglądarce internetowej. Włącz go, a następnie odśwież stronę, aby móc w pełni z niej korzystać.