• Title/Summary/Keyword: Canard-Controlled Missile

Search Result 5, Processing Time 0.018 seconds

A Study on the Roll-Rate of a Canard-Controlled Missile with Freely Spinning Tailfins (자유회전 테일핀의 회전율 및 Roll-Lock 현상 연구)

  • Yang, Young-Rok;Lee, Jin-Hee;Kim, Mun-Seok;Park, Chan-Hyuk;Myong, Rho-Shin;Cho, Tae-Hwan
    • 한국전산유체공학회:학술대회논문집
    • /
    • 2008.03b
    • /
    • pp.126-129
    • /
    • 2008
  • In this study the aerodynamic characteristics of a canard-controlled missile with freely spinning tailfins were investigated by using a CFD code. The aerodynamic coefficients and roll-rate of freely spinning tailfins were calculated by an analysis of 6-DOF and the Euler code. Results were in good agreement with experimental data, and the roll-rates of freely spinning tailfins were also in good agreement with the experimental data for the roll and yaw canard control inputs. This indicates that the CFD Euler code can be applied to predict the canard-controlled missile with freely spinning tailfins.

  • PDF

Range Sensitivity Analysis of a Canard Controlled Missile (유도 미사일의 사거리 민감도 연구)

  • Yang, Young-Rok;Cho, Tae-Hwan;Myong, Rho-Shin
    • Journal of the Korea Institute of Military Science and Technology
    • /
    • v.14 no.1
    • /
    • pp.39-48
    • /
    • 2011
  • This study describes a range sensitivity of a canard controlled missile. An investigation was conducted into the relative importance of aerodynamic parameters on a guided missile. Also this study was analyzed by quantifying their effects on the missile range. To analyze the range sensitivity of a guided missile, a trajectory analysis program of a guided missile was developed. The range sensitivity analysis was conducted on a thrust, weight, drag and lift. The result of the range sensitivity analysis shows that the design parameters with the greatest effect on the missile range are thrust, drag, weight, and lift, in descending order of importance. The thrust on range extension is quite obvious to extend a range of a guided missile. In particular, the drag exhibited greater range sensitivity than lift at a guided flight. The result also shows that missile range could be maximized by applying the appropriate launch angle and canard pitch-up control.

Aerodynamic Characteristics of a Canard-Controlled Missile with Freely Spinning Tailfins Using a Semi-Empirical Method and a CFD Code (반실험적 기법 및 CFD 코드를 이용한 자유회전 테일핀을 갖는 커나드 조종 미사일에 관한 공력해석)

  • Yang, Young-Rok;Lee, Jin-Hee;Kim, Mun-Seok;Jung, Jae-Hong;Myong, Rho-Shin;Cho, Tae-Hwan
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.36 no.3
    • /
    • pp.220-228
    • /
    • 2008
  • In this study the aerodynamic characteristics of a canard-controlled missile with freely spinning tailfins were investigated by using a semi-empirical method and a CFD code. The mean aerodynamic coefficients for the rolling and roll damping moments were first calculated and then used to predict the roll-rate of freely spinning tailfins. The calculation of roll-rate in the CFD code was carried out by combining a Chimera overset grid system and 6-DOF analysis module. The predicted roll-rate was in good agreement with the experimental data for the roll and yaw canard control inputs. It was also shown that the results are in good agreement with the prediction by a CFD code. This indicates that the semi-empirical method can be used to predict the roll-rate of a canard-controlled missile with freely spinning tailfins.

A NUMERICAL STUDY ON THE ROLL LOCK-IN OF A CANARD-CONTROLLED MISSILE WITH FREELY SPINNING TAILFINS (자유회전 테일핀을 갖는 미사일에 대한 Roll Lock-in 현상의 수치적 연구)

  • Yang, Y.R.;Kim, M.S.;Myong, R.S.;Cho, T.H.
    • Journal of computational fluids engineering
    • /
    • v.14 no.4
    • /
    • pp.48-55
    • /
    • 2009
  • In this study, roll lock-in phenomena of freely spinning tailfins were investigated by a CFD code. To analyze a motion of freely spinning tailfins, this research use a Chimera method, an Euler code and a 6 degrees of freedom analysis. The numerical results of aerodynamic characteristics and roll rates of a canard-controlled missile with freely spinning tailfins show a good agreement with wind tunnel test results. Using the roll rates calculation result of freely spinning tailfins, roll lock-in phenomena is confirmed. Roll lock-in phenomena and Roll lock-in states can be predicted through effects of the induced vortex of the canards control and the analysis of the rolling moments of tailfins due to the bank angle.

A Prediction Study on the Roll Lock-in Phenomena of Freely Spinning Tailfins (자유회전 테일핀의 Roll Lock-in 현상 예측 연구)

  • Yang, Young-Rok;Cho, Tae-Hwan;Myong, Rho-Shin
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.38 no.9
    • /
    • pp.849-855
    • /
    • 2010
  • This paper investigated the roll lock-in phenomena of a canard-controlled missile with freely spinning tailfins by applying Falanga's roll-rate equation. To confirm and validate the accuracy of the results of the roll-rate and roll lock-in prediction for freely spinning tailfins, the results were compared with Blair's wind tunnel test data. For calculation of the roll-rate of freely spinning tailfins, rolling moment coefficients of the tailfins were obtained from the wind tunnel test data and roll-damping coefficients were calculated by missile DATCOM. The roll-rate and roll lock-in of the freely spinning tailfins were calculated by applying these values to the roll-rate equation for freely spinning tailfins. The calculation results showed good agreement with the wind tunnel test data, and the roll lock-in could be anticipated as well.