DOI QR코드

DOI QR Code

Aerodynamic Design of a Canard Controlled 2D Course Correction Fuze for Smart Munition

카나드 기반의 지능탄 조종 장치 공력설계

  • Park, Ji-Hwan (Department of Aerospace and System Engineering and Research Center for Aircraft Parts Technology, Gyeongsang National University) ;
  • Bae, Ju-Hyeon (Agency for Defense Development) ;
  • Song, Min-Sup (Agency for Defense Development) ;
  • Myong, Rho-Shin (Department of Aerospace and System Engineering and Research Center for Aircraft Parts Technology, Gyeongsang National University) ;
  • Cho, Tae-Hwan (Department of Aerospace and System Engineering and Research Center for Aircraft Parts Technology, Gyeongsang National University)
  • Received : 2014.11.05
  • Accepted : 2015.02.06
  • Published : 2015.03.01

Abstract

Course correction munition is a smart projectile which improves its accuracy by the control mechanism equipped in the fuze section with canard. In this paper, various aerodynamic configurations of the fuze section were analysed by utilizing a semi-empirical method and a CFD method. A final canard configuration showing the least drag was then determined. During the CFD simulation, it was found that the k-${\omega}$ SST turbulence model combined with O-type grid base is suitable for the prediction of the base drag. Finally, the aerodynamic characteristics of the smart munition and the change of drag due to the canard installation were analysed.

탄도수정탄은 기존 포탄의 신관에 카나드가 장착된 조종 장치를 탑재하여 정확도를 향상시키는 지능탄이다. 본 논문에서는 2D 탄도수정탄의 카나드를 설계하기 위하여 다양한 형상 변수에 대한 공력성능을 반실험적 기법을 이용하여 분석하였으며, 이를 바탕으로 초음속에서 항력이 상대적으로 더 적은 카나드 형상을 설계하였다. 또한 CFD 기법을 통한 탄도수정탄의 공력해석 기법을 연구하였으며, 포탄의 탄저 부분 기저항력 예측에 O-type 격자를 바탕으로 한 k-${\omega}$ SST 난류모델이 적합함을 확인하였다. 최종적으로 앞서 개발한 해석 기법을 바탕으로 2D 탄도수정탄의 공력특성 및 탄도조종장치 장착에 따른 항력변화를 계산하였다.

Keywords

References

  1. Park, W. D. and Lee, J. M., "Review on Current Status and Development Direction for the Smart Munition," Journal of the Korea Association of Defense Industry Studies, Vol. 14, No. 1, 2007, pp. 141-161.
  2. Je, S. E., "A Study on the Aerodynamic Characteristics for a Spin-Stabilized Projectile with Control Surface," Gyeongang National University, Ph.D. Thesis, 2009.
  3. Kim, K. P., Chung, M. J. and Hong, J., "A Study on Configuration Design of the 2D Course Correction Munition," Journal of the Korea Institute of Military Science and Technology, Vol. 11, No. 4, 2008, pp. 5-12.
  4. Storsved, D., "PGK and the Impact of Affordable Precision on the Fires Mission," 43rd Annual Guns & Missiles Symposium, 2008.
  5. Kim, K. P., "A Study on Course Correction Performance Expectation & Algorithm Implementation of 1D CCM," Journal of the The Korea Institute of Military Science and Technology, Vol. 10, No. 1, 2007, pp. 5-13.
  6. Clancy, J. A., Bybee, T. D. and Friedrich, W. A., "Fixed Canard 2-D Guidance of Artillery Projectiles," U.S. Patent 6,981,672 B2, 2006.
  7. Yang, Y. R., Myong, R. S. and Cho, T. H., "Range Sensitivity Analysis of a Canard Controlled Missile," Journal of the The Korea Institute of Military Science and Technology, Vol. 14, No. 1, 2011, pp. 39-48. https://doi.org/10.9766/KIMST.2011.14.1.039
  8. Han, M. S., Myong, R. S., Cho, T. H., Hwang, J. S. and Park, C. W., "Analysis of the Aerodynamic Characteristics of Missile Configurations Using a Semi-Empirical Method," Journal of the Korean Society for Aeronautical & Space Sciences, Vol. 33, No. 3, 2005, pp. 26-31. https://doi.org/10.5139/JKSAS.2005.33.3.026
  9. Yang, Y. R., Hu, S. B., Je, S. Y., Park, C. W., Myong, R. S., Cho, T. H., Hwang, U. C. and Je, S. E., "An External Shape Optimization Study to Maximize the Range of a Guided Missile in Atmospheric Flight," Journal of the Korean Society for Aeronautical & Space Sciences, Vol. 37, No. 6, 2009, pp. 519-526. https://doi.org/10.5139/JKSAS.2009.37.6.519
  10. PRODASV3 Technical Manual, Arrow Tech, 1992.
  11. McCoy, R. L., "McDrag-A Computer Program for Estimating the Drag Coefficients of Projectiles," ARLBRL-TR-02293, U.S. Army Ballistic Research Laboratory, Aberdeen Proving Ground, Maryland, 1981.
  12. Sahu, J., "Drag Prediction for Projectiles at Transonic and Supersonic Speeds," BRL-MR-3523, U.S. Army Ballistic Research Laboratory, Aberdeen Proving Ground, Maryland, June 1986.
  13. ANSYS V13 FLUENT Basic, TSNE, 2011.
  14. Silton, S. I., "Navier-Stokes Computations for a Spinning Projectile from Subsonic to Supersonic Speeds," Journal of Spacecraft Rockets, Vol. 42, No. 2, 2005, pp. 223-231. https://doi.org/10.2514/1.4175