Aircraft spin characteristics with high-alpha yawing moment asymmetry

Abstract

This paper analyzes the open-loop spin dynamics of a fighter configuration that exhibits yawing moment asymmetry at high angles of attack. High-fidelity aerodynamic model, in a look-up-tables form, is developed using the experimental data from static, coning, and oscillatory coning rotary balance wind tunnel tests. As a first step, all attainable equilibrium spin modes along with their sensitivity to control settings are predicted. Investigation of the dynamic characteristics of the predicted spin modes is performed using six degrees-of-freedom time history simulations, which showed that both, right and left flat spins are oscillatory and divergent. Influence of high-alpha yawing moment asymmetry on the spin recovery piloting strategies with control inputs is also studied with six degrees-of-freedom time history simulations. Our studies reveal that the proposed spin recovery strategies effectively reduce the recovery time for the left flat spins. However, aircraft’s inherent tendency to yaw rightwards due to high-alpha yawing moment asymmetry renders proposed spin recovery strategies ineffective in accelerating the recovery of the right flat spins.

Keywords

Aerodynamic asymmetry unsteady effects steady spin modes flat spin time history simulations dynamic stability

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References

Abzug

Larrabee

. Spinning and recovery. In: Airplane stability and control: A history of the technologies that made aviation possible, 2nd ed. Cambridge: Cambridge University Press, 2005, pp. 121–140.

Bryan

. Stability in aviation: An introduction to dynamical stability as applied to the motions of aero planes, London: Macmillan and Co. limited, 1911.

Bergmann

. Modern wind tunnel techniques for unsteady testing–Development of dynamic test rigs, New York: Springer Berlin Heidelberg, 2009, pp. 59–77.

Zhang

Tang

Sun

et al.

Dynamic test experiment system of single degree of freedom of Φ3. 2 m wind tunnel. Proc IMechE, Part G: J Aerospace Engineering 2015; 7: 1300–1309.

Tischler

Barlow

. Determination of the spin and recovery characteristics of a general aviation design. J Aircraft 1981; 4: 238–244.

Khrabrov

Sidoryuk

Goman

. Aerodynamic model development and simulation of airliner spin for upset recovery. Prog Flight Phys 2013; 5: 621–636.

Carroll

Mehra

. Bifurcation analysis of nonlinear aircraft dynamics. J Guid Control Dyn 1982; 5: 529–536.

Guicheteau P. Bifurcation theory in flight dynamics an application to a real combat aircraft. In: Proceedings of 17th congress of international council of the aeronautical sciences, ICAS Paper 90-5.10.4, Stockholm, Sweden, 1990.

Jahnke

Culick

. Application of bifurcation theory to the high-angle-of-attack dynamics of the F-14. J Aircraft 1994; 31: 26–34.

10.

Planeaux J. Bifurcation analysis of a model fighter aircraft with control augmentation. In: 17th atmospheric flight mechanics conference, Portland, OR, USA, 20–22 August 1990.

11.

Raghavendra

Sahai

Kumar

et al.

Aircraft spin recovery, with and without thrust vectoring, using nonlinear dynamic inversion. J Aircraft 2005; 42: 1492–1503.

12.

Goman

Khramtsovsky

Kolesnikov

. Evaluation of aircraft performance and maneuverability by computation of attainable equilibrium sets. J Guid Control Dyn 2008; 31: 329–339.

13.

Kolesnikov E and Goman M. Analysis of aircraft nonlinear dynamics using non-gradient based numerical methods and attainable equilibrium sets. In: AIAA atmospheric flight mechanics conference, Minneapolis, MN, USA, 13–16 August 2012.

14.

Kramer BR. Experimental evaluation of superposition techniques applied to dynamic aerodynamics. In: 40th AIAA aerospace sciences meeting & exhibit, Reno, NV, USA, 14–17 January 2002.

15.

Murch AM and Foster JV. Recent NASA research on aerodynamic modeling of post-stall and spin dynamics of large transport airplanes. In: 45th AIAA aerospace sciences meeting and exhibit, Reno, NV, USA, 8 January 2007.

16.

Hewsom R. Sino-Pakistani fighter improved. Jane’s Defense Weekly, December 2005, pp.99–100.

17.

Research and technology organization (NATO). Cooperative programme on dynamic wind tunnel experiments for maneuvering aircraft. AGARD Advisory Report No.305, 01 October 1996.

18.

Le Roy JF, Morgand S and Farcy D. Static and Dynamic Derivatives on generic UCAV without and with leading edge control. In: 32th AIAA applied aerodynamics conference, Atlanta, GA, USA, 16–20 June 2014.

19.

Bihrle

Barnhart

. Spin prediction techniques. J Aircraft 1983; 2: 97–101.

20.

Luchtenburg

Rowley

Lohry

et al.

Unsteady high-angle-of-attack aerodynamic models of a generic jet transport. J Aircraft 2015; 3: 890–895.

21.

Abramov N, Goman M and Khrabrov AN. Aircraft dynamics at high incidence flight with account of unsteady aerodynamic effects. In: AIAA atmospheric flight mechanics conference, Rhode Island, USA, 16–19 August 2004.

22.

Goman

Khrabrov

. State-space representation of aerodynamic characteristics of an aircraft at high angles of attack. J Aircraft 1994; 5: 1109–1115.

23.

Ignatyev

Khrabrov

. Neural network modeling of unsteady aerodynamic characteristics at high angles of attack. Aerosp Sci Technol 2015; 41: 106–115.

24.

Wang Z, Lan CE and Brandon JM. Fuzzy logic modeling of nonlinear unsteady aerodynamics. In: 23rd AIAA atmospheric flight mechanics conference, Boston, USA, 10–12 August 1998.

25.

Wang

Qian

. Unsteady aerodynamic modeling at high angles of attack using support vector machines. Chin J Aeronaut 2015; 28: 659–668.

26.

Pamadi BN. Inertia coupling and spin. In: Performance, stability, dynamics, and control of airplanes. AIAA Education Series, 2004, pp.646–664.

27.

Bowman JR and James S. Summary of spin technology as related to light general-aviation airplanes. NASA TND-7575, December 1971.