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高超聲速氣流非結(jié)構(gòu)化網(wǎng)格DSMC算法研究

DSMC method of unstructurized grids for hypersonic gas now

  • 摘要: 高超聲速氣動(dòng)熱力學(xué)環(huán)境的研究是直接涉及飛行器軌道控制、熱防護(hù)設(shè)計(jì)的關(guān)鍵問題之一。文章通過研究稀薄氣體熱化學(xué)非平衡態(tài)中的熱力學(xué)環(huán)境，采用非結(jié)構(gòu)化DSMC程序?qū)Α盎鹦翘铰氛咛?hào)”（Mars Pathfinder）探測(cè)器的Ballute減速裝置在地球大氣層和火星大氣層中的高超聲速飛行進(jìn)行了數(shù)值模擬，計(jì)算得到了流場(chǎng)的溫度分布、探測(cè)器壁面的熱流密度分布，分析表明稀薄氣體熱化學(xué)非平衡態(tài)對(duì)飛行器流場(chǎng)有影響。將仿真結(jié)果與NASA蘭利研究中心的計(jì)算結(jié)果作了比較，二者吻合很好。研究結(jié)果可用于飛行器熱防護(hù)設(shè)計(jì)。

     

    Abstract: The hypersonic aero-thermodynamics is important for me night control and me vehicle themal protection system (TPS) design. This paper firstly studies the thernlodynamic environment in the thermochemical nonequilibrium now unstmcnlrized girds are used to simulate the towed Ballute night in the Earth atmosphere and the Maniall atmosphere by DSMC. Important parameters of the hypersonic Vehicle, including the themochemical nonequilibrium chamcteristics and the wall heat nux, are obtained by me numerical simulation. The obtained results are compared wim the computatiOn results published by NASA Langley research center, and a good agreement is found. These results are useful for designing related vehicles'TPS.

     

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