主动式气膜冷却对高超声速飞行器等离子体鞘套的影响
V411; 以钝锥模型为研究对象,采用热化学非平衡计算方法并结合可压缩 N-S方程、SST k-ω湍流模型,对钝锥模型肩部台阶喷流和头部逆向喷流流场进行了数值模拟.在考虑不同喷流压强、喷口位置和数量等因素的基础上,分析了主动式气膜冷却对等离子体鞘套的影响.结果表明:高超声速飞行器采用主动式气膜冷却技术时,喷口的数量、位置及喷流压强对等离子体密度均具有显著的影响.肩部的切向喷流可有效抑制模型壁面附近的等离子体密度,进而可能对高频电磁波的传输和目标雷达散射截面(RCS)产生影响.头部逆向喷流可显著改变等离子体的分布情况,不同的逆向喷流参数配置会导致明显的差异....
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| Published in | 中山大学学报（自然科学版）（中英文） Vol. 64; no. 1; pp. 250 - 256 |
|---|---|
| Main Authors | , |
| Format | Journal Article |
| Language | Chinese |
| Published |
中山大学航空航天学院,广东 深圳 518107
2025
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| Subjects | |
| Online Access | Get full text |
| ISSN | 2097-0137 |
| DOI | 10.13471/j.cnki.acta.snus.ZR20240173 |
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| Abstract | V411; 以钝锥模型为研究对象,采用热化学非平衡计算方法并结合可压缩 N-S方程、SST k-ω湍流模型,对钝锥模型肩部台阶喷流和头部逆向喷流流场进行了数值模拟.在考虑不同喷流压强、喷口位置和数量等因素的基础上,分析了主动式气膜冷却对等离子体鞘套的影响.结果表明:高超声速飞行器采用主动式气膜冷却技术时,喷口的数量、位置及喷流压强对等离子体密度均具有显著的影响.肩部的切向喷流可有效抑制模型壁面附近的等离子体密度,进而可能对高频电磁波的传输和目标雷达散射截面(RCS)产生影响.头部逆向喷流可显著改变等离子体的分布情况,不同的逆向喷流参数配置会导致明显的差异. |
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| AbstractList | V411; 以钝锥模型为研究对象,采用热化学非平衡计算方法并结合可压缩 N-S方程、SST k-ω湍流模型,对钝锥模型肩部台阶喷流和头部逆向喷流流场进行了数值模拟.在考虑不同喷流压强、喷口位置和数量等因素的基础上,分析了主动式气膜冷却对等离子体鞘套的影响.结果表明:高超声速飞行器采用主动式气膜冷却技术时,喷口的数量、位置及喷流压强对等离子体密度均具有显著的影响.肩部的切向喷流可有效抑制模型壁面附近的等离子体密度,进而可能对高频电磁波的传输和目标雷达散射截面(RCS)产生影响.头部逆向喷流可显著改变等离子体的分布情况,不同的逆向喷流参数配置会导致明显的差异. |
| Abstract_FL | Utilizing a thermochemical non-equilibrium computational approach and employing compressible N-S equations along with the SST k-ω turbulence model,numerical simulations were conducted for the flow fields of the shoulder step jet and the head reverse jet of the blunt cone model.Under different conditions of jet pressure,nozzle positions,and quantities,the effects of active gas film cooling on the sheath surrounding the hypersonic vehicle were meticulously analyzed.The results indicate that the number and position of the nozzles as well as the pressure of the jets in active gas film cooling for hypersonic vehicles significantly influence plasma density.Tangential jets at the shoulder effectively reduce plasma density near the model wall,potentially affecting the transmission of high-frequency electronic waves and target RCS(radar cross section).Meanwhile,reverse jets at the head can notably alter the distribution of head plasma.Different arrangements of reverse jets will lead to obvious differences in their effects. |
| Author | 徐春光 张源耕 |
| AuthorAffiliation | 中山大学航空航天学院,广东 深圳 518107 |
| AuthorAffiliation_xml | – name: 中山大学航空航天学院,广东 深圳 518107 |
| Author_FL | XU Chunguang ZHANG Yuangeng |
| Author_FL_xml | – sequence: 1 fullname: XU Chunguang – sequence: 2 fullname: ZHANG Yuangeng |
| Author_xml | – sequence: 1 fullname: 徐春光 – sequence: 2 fullname: 张源耕 |
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| DOI | 10.13471/j.cnki.acta.snus.ZR20240173 |
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| Keywords | thermochemical non-equilibrium calculation 双温模型 hypersonic vehicle 热化学非平衡 active gas film cooling 高超声速飞行器 two-temperature model 主动式气膜冷却 plasma sheath 等离子体鞘套 |
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| Title | 主动式气膜冷却对高超声速飞行器等离子体鞘套的影响 |
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