导弹与航天运载技术
導彈與航天運載技術
도탄여항천운재기술
Missiles and Space Vehicles
2015年
5期
30-34
,共5页
乔野%聂万胜%吴高杨%冯伟%丰松江
喬野%聶萬勝%吳高楊%馮偉%豐鬆江
교야%섭만성%오고양%풍위%봉송강
液体火箭发动机%双机并联%尾焰%数值仿真%激波
液體火箭髮動機%雙機併聯%尾燄%數值倣真%激波
액체화전발동궤%쌍궤병련%미염%수치방진%격파
Liquidrocket engine%Parallel-running%Plume%Numerical simulation%Shock wave
以氢氧火箭发动机为模型,采用耦合可实现k-ε湍流模型的N-S方程,对发动机在地面发射阶段双机并联工作状态下的尾焰流场进行数值仿真研究,得到尾焰流场的各项参数分布及其变化规律,与理论分析结果对比,证明了算法的有效性和正确性,为开展多台发动机并联工作下尾焰的撞击和辐射特性等研究奠定了基础.
以氫氧火箭髮動機為模型,採用耦閤可實現k-ε湍流模型的N-S方程,對髮動機在地麵髮射階段雙機併聯工作狀態下的尾燄流場進行數值倣真研究,得到尾燄流場的各項參數分佈及其變化規律,與理論分析結果對比,證明瞭算法的有效性和正確性,為開展多檯髮動機併聯工作下尾燄的撞擊和輻射特性等研究奠定瞭基礎.
이경양화전발동궤위모형,채용우합가실현k-ε단류모형적N-S방정,대발동궤재지면발사계단쌍궤병련공작상태하적미염류장진행수치방진연구,득도미염류장적각항삼수분포급기변화규률,여이론분석결과대비,증명료산법적유효성화정학성,위개전다태발동궤병련공작하미염적당격화복사특성등연구전정료기출.
This passage is modeled with LOX/LH2 rocket engine, and uses the N-S equation coupled with realizablek-ε model to conduct numerical simulation research on the rocket plume flow field in the two-generator parallel-running station during the launch. The distribution and change rules of different parameters in the plume field have been gained. With the compare between the simulation data and the theoretical result, the algorithm is proved to be effective and correct. With that, a great foundation will be laid for the study of the plume impact and radiation in multi-generator parallel-running.
