Volume 37 Issue 8
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LIANG Xiaoyang，SU Yifei，LE Guigao.Numerical analysis of hot launch of missile from a launch canister［J］.Journal of Aerospace Power，2022，37（8）：1643‑1653. doi: 10.13224/j.cnki.jasp.20210308
Citation: LIANG Xiaoyang，SU Yifei，LE Guigao.Numerical analysis of hot launch of missile from a launch canister［J］.Journal of Aerospace Power，2022，37（8）：1643‑1653. doi: 10.13224/j.cnki.jasp.20210308
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Numerical analysis of hot launch of missile from a launch canister

doi: 10.13224/j.cnki.jasp.20210308

  • School of Mechanical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China

  • Received Date: 2021-06-17
    Abstract

  • Based on the three⁃dimensional compressible Reynolds⁃averaged Navier⁃Stokes equation and the k⁃ε turbulence model，the environment around the bottom of the missile and the flow field characteristics in the launch canister after deflection of the missile attitude were investigated.Firstly，the effectiveness of the numerical method was verified by the experiment of supersonic jet impinging on a flat plate.Secondly，the flow characteristics of the launch canister in the constrained and semi⁃confined periods were investigated respectively.The results showed that significant entrainment effect of the exhaust gas can be found in the launch canister.Meanwhile，a backflow area near the bottom of the missile can be observed，which may cause additional drag force on the missile during the launching process.After considering the deflection，the impact load on the launcher was increased by more than two times and the pressure on the launch box wall was increased by 40%.Moreover，the flow field distribution inside the box was no longer symmetrical during the semi⁃confinement period，making the missile subject to additional unbalanced moments.

     

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    • References(18)
  • [1]
    BERTIN J,BERTIN R,YUNG A,et al.The launch⁃tube flow⁃field for a vertical launching system[R].AIAA 88⁃0332,1988.
    [2]
    SAMIMY M,TURNER W,ADDY A.Backflow induced unsteady aerodynamic forces during tube launch[R].AIAA 87⁃0464,1987.
    [3]
    BOUSLOG S A,BERTIN J J,WINGERT W B.Flowfield produced by rocket exhaust impingement of a multitube launcher[J].Journal of Spacecraft and Rockets,1984,21（4）:323⁃329.
    [4]
    BERLIN J J,BATSON J L.Experimentally determined rocket⁃exhaust flowfield in a constrictivetube launcher[J].Journal of Spacecraft and Rockets,1975,12（12）:711⁃717.
    [5]
    张程,李新田,廖选平,等.固体火箭发动机后效推力对导弹底阻影响的数值仿真[J].航空动力学报,2017,32（6）:1530⁃1536.

    ZHANG Cheng,LI Xintian,LIAO Xuanping,et al.Numerical simulation of influences of solid rocket motor post⁃thrust on missile base drag[J].Journal of Aerospace Power,2017,32（6）:1530⁃1536.（in Chinese）
    [6]
    LAMONT P J,HUNT B L.The impingement of underexpanded,axisymmetric jets on perpendicular and inclined flat plates[J].Journal of Fluid Mechanics,1980,100（3）:471⁃511.
    [7]
    NAKAI Y,FUJIMATSU N,FUJII K.Flow classification of the under⁃expanded super sonic jet impinging on a flat plate[R].AIAA 2003⁃3467,2003.
    [8]
    NAKAI Y,FUJIMATSU N,FUJII K.Experimental study of underexpanded supersonic jet impingement on an inclined flat plate[J].AIAA Journal,2006,44（11）:2691⁃2699.
    [9]
    BERLIN J J,BATSON J L.Experimentally determined rocket⁃exhaust flowfield in a constrictivetube launcher[J].Journal of Spacecraft and Rockets,1975,12（12）:711⁃717.
    [10]
    SINHA P K,CHAKRABORTY D.Numerical study of hot launch of missile inside a tube[J].Journal of Aerospace Engineering,2014,228（14）:2604⁃2611.
    [11]
    KORST H H,BERTIN J J.Analysis of secondary flows for tube⁃launched rocket configurations[J].Journal of Spacecraft and Rockets,1983,20（1）:35⁃42.
    [12]
    VATSA V N,WEDAN B W.Development of a multigrid code for 3⁃D Navier⁃Stokes equations and its application to a grid⁃refinement study[J].Computers & Fluids,1990,18（4）:391⁃403.
    [13]
    BUSH M B,TANNER R I.Numerical solution of viscous flows using integral equation methods[J].International Journal for Numerical Methods in Fluids,1983,3（1）:71⁃92.
    [14]
    SHIH T H,LIOU W W,SHABBIR A,et al.A new k⁃ϵ eddy viscosity model for high reynolds number turbulent flows[J] Computers & Fluids 1995,24（3）:227‑238.
    [15]
    EL⁃AMIN,M F,SUN S,HEIDEMANN W,et al.Analysis of a turbulent buoyant confined jet modeled using realizable k‑ɛ model[J].Heat and Mass Transfer,2010,46（8）:943⁃960.
    [16]
    CHIMA R,LIOU M S.Comparison of the AUSM+ and H⁃CUSP schemes for turbomachinery applications[R].AIAA 2003⁃4120,2003.
    [17]
    VENKATAKRISHNAN V.Convergence to steady state solutions of the Euler equations on unstructured grids with limiters[J].Journal of Computational Physics,1995,118（1）:120‑130.
    [18]
    ALVI F,IYER K.Mean and unsteady flowfield properties of supersonic impinging jets with lift plates[R].AIAA 99⁃1829,1999.
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