International Journal of Naval Architecture and Ocean Engineering

The Society of Naval Architects of Korea (대한조선학회)
권호 표지
DOI QR코드

DOI QR Code

Effects of the partially movable control fin with end plate of underwater vehicle

  • Jung, Chul-Min (The 6th Research and Development Institute, Agency for Defense Development) ;
  • Paik, Bu-Geun (Advanced Ship Research Division, KRISO, KIOST) ;
  • Park, Warn-Gyu (School of Mechanical Engineering, Pusan National University)
  • Received : 2016.02.02
  • Accepted : 2016.07.22
  • Published : 2017.01.31
Download PDF
⟨ Previous Next ⟩

Abstract

Underwater torpedo has control fin with very low aspect ratio due to launching from limited size of cylindrical torpedo tube. If the aspect ratio of control fin of underwater vehicle is very low three-dimensional flow around control fin largely reduces control forces. In this study, the end plate was applied to reduce the three-dimensional flow effects of partially movable control fin of underwater vehicle. Through numerical simulations the flow field around control fin was examined with and without end plate for different flap angles. The pressure, vorticity, lift and torque on the control fin were analyzed and compared to experiments. The comparison have shown a reasonable agreement between numerical and experimental results and the effect of end plate on a low aspect ratio control fin. When the end plate was attached to the movable control fin, the lift increased and the actuator shaft torque did not significantly change. As this means less consumption of the actuator shaft torque compared to the control fin that has the same control force, the inner actuator capacity can be reduced and energy consumption can be saved. Considering this, it is expected to be effectively applied to the control fin design of underwater vehicles such as torpedoes.

Keywords

References

  1. Briggs, M.M., Schwind, R.G., 1983. Augmentation of fighter aircraft lift and STOL capability by blowing outboard from the wing tips. In: AIAA 21st Aerospace Sciences Meeting, AIAA Paper No. 83-0078, January.
  2. Ceron-Munoz, H.D., Cosin, R., 2013. Experimental investigation of wing-tip devices on the reduction of induced drag. J. Aircr. 50 (2) (March-April).
  3. Hoerner, S.F., 1965. Fluid-dynamic Drag. Published by the author, 1965.
  4. Jarvinen, P.O., 1973. Aircraft wing tip vortex modification. J. Aircr. 10 (1), 63-64. https://doi.org/10.2514/3.44352
  5. Jung, C., Lee, K., Kim, C., 2011. The analysis of three dimensional flow around a low-aspect-ratio control fin with end plate. In: 64th Annual Meeting of the APS Division of Fluid Dynamics, Baltimore, November.
  6. Jung, C., Lee, K., Kim, C., 2012. Flow analysis around a partially movable control fin with end plate. In: The Korea Institute of Military Science and Technology 2015 General Conference, Gyeongju, Korea, June.
  7. Kauertz, S., Neuwerth, G., 2006. Excitation of instabilities in the wake of an airfoil with winglets. In: 24th Applied Aerodynamics Conference, 5-8 June. AIAA 2006-3470.
  8. Kravchenco, S.A., 1996. The application of the wingtip lifting surfaces for practical aerodynamic. In: Proceedings of the 20th Congress of the International Council of the Aeronautical Sciences, Sorrento, Italy.
  9. Kroo, I., 2005. Nonplanar Wing Concepts for Increased Aircraft Efficiency: VKI Lecture Series on Innovative Configurations and Advanced Concepts for Future Civil Aircraft.
  10. Margaris, P., Gursul, I., 2010. Vortex topology of wing tip blowing. Aerosp. Sci. Technol. 14, 143-160. https://doi.org/10.1016/j.ast.2009.11.008
  11. Mineck, R.E., 1995. Study of Potential Aerodynamic Benefits from Spanwise Blowing at Wingtip. NASATP 3515.
  12. Park, P. S. and Rokhsaz, K., 2003. Effects of a winglet rudder on lift-to-drag ratio and wake vortex frequency, AIAA 2003-4069, 21st Applied Aerodynamics Conference, 23-26 June.
  13. Savage, M.G., Larose, G.L., 2003. An experimental study of the aerodynamic influence of a pair of winglets on a flat plate model. J. Wind Eng. Industrial Aerodyn. 91, 113-126. https://doi.org/10.1016/S0167-6105(02)00339-2
  14. Simpson, G., Ahmed, N.A., Archer, R.D., 2000. Improvement of a wing's aerodynamic efficiency using Coanda tip jets. J. Aircr. 37 (1), 183-184. https://doi.org/10.2514/2.2579
  15. Smith, M.J., Komerath, N., Ames, R., Wong, O., Pearson, J., 2001. Performance analysis of a wing with multiple winglets. In: AIAA Paper 2001-2407.
  16. Spillman, J.J., 1978. The use of wing tip sails to reduce vortex drag. Aeronaut. J. 82 (813), 387-395.
  17. Whitcomb, R.T., 1976. A Design Approach and Selected Wind-tunnel Results at High Subsonic Speeds for Wing-Tip Mounted Winglets. NASATN D-8260.

Cited by

  1. A nonlinear controller based on saturation functions with variable parameters to stabilize an AUV vol.11, pp.1, 2017, https://doi.org/10.1016/j.ijnaoe.2018.04.002