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

Document Type : Original Article

Authors

1 Mech.Engg. Dept. Faculty of Engg. Ferdowsi University of Mashhad

2 Mech. Engg. Dept. Faculty of Engg. Ferdowsi University of Mashhad

3 Mech.Engg.Dept.Faculity of Engg.Ferdowsi University of Mashhad

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

Smiley face

References

  1. Qu, X., Zhang, W., Shi, J., & 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., & 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., & 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., & 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., & 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., & Warsop, C. “A Novel Control Allocation Method for Yaw Control of Tailless Aircraft,” Aerospace, Vol. 7, No. 10, p. 150, 2020.
  8. Fulker, J., & 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., & 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., & 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. & 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. & 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., & 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., & 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., & 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., & 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., & Stenfelt, G. “Predictions of stability and control for a flying wing,” Aerosp Sci Technol, Vol. 39, pp. 179-186, 2014.
  18. Kelayeh, R. K., & 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.

 

 

 

 

 

Files

History

  • Receive Date: 22 February 2022
  • Revise Date: 31 May 2022
  • Accept Date: 09 July 2022
  • Publish Date: 22 September 2022

Share

How to cite

Statistics