Optimization of split drag rudder mechanism at different angles of attack in a flying wing airplane

Document Type : Original Article

Authors

1 Master student of Ferdowsi University of Mashhad, Faculty of Engineering, Mashhad, Iran

2 Professor, Faculty of Engineering Ferdowsi University of Mashhad, Mashhad, Iran

3 Master's degree, Faculty of Engineering, Ferdowsi University of Mashhad, Mashhad, Iran

Abstract

In this research, the split drag system at different AOA for a flying wing aircraft has been simulated and optimized by a numerical method. The split drag system provides vertical axis control by creating asymmetric drag between the right and left wings. The aircraft under study is a lambda shape aircraft with a swept-back angle of 56. The split drag control system is made up of two surfaces on top of each other, by opening in the opposite direction on one side of the aircraft, it creates the drag necessary to produce yawing moment. Their installation position is at the tip of the wings and on the trailing edge. When using split drag, in addition to the yawing moment, a disturbing rolling moment is created, which is caused by the drag difference between the upper and lower surface of this system, and the reason for this is the change in the AOA of the aircraft. Asymmetric opening of the surfaces can reduce the induced roll to zero and in some cases to a minimum. The test was carried out in AOA of 0 to 12ᵒ for drag split opening angles of 10, 20, and 30ᵒ. Calculations based on equations (RANS) are discretized with the finite volume method. The obtained results show how much to add to the angle of the split drag surfaces depending on the AOA in order to find the most optimal mode to neutralize the roll, and finally, the optimized diagrams of this system are obtained.

Keywords

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References

  1.  

    1. Qu, X., Zhang, W., Shi, J., and Lyu, Y. “A Novel Yaw Control Method for Flying-Wing Aircraft in Low Speed Regime”, Aerosp Sci Technol, Vol. 69, pp. 636-649, 2017.
    2. Dehghan Manshadi, M., Ilbeigi, M., Bazazzadeh, M., and Vaziri, M.A. “Experimental Study of Aerodynamic Coefficients of a Lambda-Shaped Flying Aircraft Model by Changing the Backward Angle of the Wing Attack Edge”, Journal of Modares Mechanical Engineering, Vol. 16, No. 5, pp. 303-311, 2016. (In Persian)
    3. Anderson, Jr. J.D. “Fundamentals of Aerodynamics”, McGraw-Hill Education, University of Maryland, Penn Plaza, New York, 2010.
    4. Ko, A., Chang, K., Sheen, D.J., Jo, Y.H., and Shim, H.J. “CFD Analysis of the Sideslip Angle Effect Around a BWB Type Configuration”, Int J Aerosp Eng, vol. 2019, 2019.
    5. Ramezanizadeh, M., and Mohammadi, A. “Numerical Investigation of Delta Wings Leading Edge Configuration Effects on the Flow Behavior Using Large Eddy Simulation Approach”, Journal of Fluid Mechanics and Aerdynamics, Vol. 3, No. 3, pp. 49-60, 2014. (In Persian)
    6. Li, Z. J., and Ma, D. L. “Control Characteristics Analysis of Split-Drag-Rudder”, Appl. Mech. Mater, Vol. 472, pp. 185-190, 2014.
    7. Shearwood, T. R., Nabawy, M. R. A., Crowther, W. J., and Warsop, C. “A Novel Control Allocation Method for Yaw Control of Tailless Aircraft”, Aerospace, Vol. 7, No. 10, p. 150, 2020.
    8. Fulker, J., and Alderman, J. “Three- Dimensional Compliant Flows for Lateral Control Applications”, AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 2005.
    9. Yue, T., Zhang, X., Wang, L., and Ai, J. “Flight Dynamic Modeling and Control for a Telescopic Wing Morphing Aircraft via Asymmetric Wing Morphing”, Aerosp Sci Technol, Vol. 70, pp. 328-338, 2017.
    10. Stenfelt, G., and Ringertz, U. “Lateral Stability and Control of a Tailless Aircraft Configuration”, J Aircr, Vol. 46, No. 6, pp. 2161-2164, 2009.
    11. Gillard, W., Dorsett, K., Gillard, W. and Dorsett, K. “Directional Control for Tailless Aircraft Using All Moving Wing Tips”, Atmospheric Flight Mechanics Conf, New Orleans, LA, U.S.A, 2006.
    12. Huber, K.C., Vicroy, D.D., Schuette, A. and Huebner, A. “UCAV Model Design and Static Experimental Investigations to Estimate Control Device Effectiveness and S&C Capabilities”, AIAA Applied Aerodynamics Conf, Atlanta, Georgia, 2014.
    13. Rajput, J., Zhang, W. G., and Qu, X. B. “A Differential Configuration of Split Drag-Rudders with Variable Bias for Directional Control of Flying-Wing”, Appl. Mech. Mater. Vol. 643, pp. 54-59, 2014.
    14. Li, D., Liu, Q., Wu, Y., and Xiang, J. “Design and Analysis of a Morphing Drag Rudder on the Aerodynamics, Structural Deformation, and the Required Actuating Moment”, J. Intell. Mater. Syst. Struct. Vol. 29, No. 6, pp. 1038-1049, 2018.
    15. Mohamad, F., Wisnoe, W., Nasir, R. E. M., Sainan, K. I., and Jenal, N. “Yaw stability Analysis for UiTM’s BWB Baseline-II UAV E-4”, Appl. Mech. Mater. Vol. 393, pp. 323-328, 2013.
    16. Djavarshkian, M.H., and Karimi Kalayeh, R., “Evaluation of Aerodynamic Performance of Geometric Torsion by Changing Reynolds Number in a Flying Aircraft Model”, Journal of Aviation Engineering, Vol. 22, No. 1, pp. 30-45, 2021. (In Persian)
    17. Tomac, M., and Stenfelt, G. “Predictions of Stability and Control for a Flying Wing”, Aerosp Sci Technol, Vol. 39, pp. 179-186, 2014.
    18. Kelayeh, R. K., and Djavareshkian, M. H. “Aerodynamic Investigation of Twist Angle Variation Based on Wing Smarting for a Flying Wing”, Chinese J Aeronaut. Vol. 34, pp. 201-216, 2021.
    19. ANSYS, Inc I., “Ansys Fluent Theory Guide R17”, Southpointe, Pennsylvania, United States, 2016.

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History

  • Receive Date: 22 February 2022
  • Revise Date: 10 June 2022
  • Accept Date: 09 July 2022
  • Publish Date: 11 July 2022

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