| 冲压增程弹进气道型面气动优化研究 |
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| 引用本文： | 王筱蓉,姜根柱,周长省.冲压增程弹进气道型面气动优化研究[J].固体火箭技术,2009,32(1). |
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| 作者姓名： | 王筱蓉 姜根柱 周长省 |
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| 作者单位： | 南京理工大学,机械工程学院,南京,210094 |
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| 摘 要： | 以某型冲压增程弹为研究对象,为了使进气道总压恢复系数最大,利用自动优化平台,集成了参数化建模和进气道流场数值模拟,以总压恢复系数最大为优化目标,运用组合优化策略对双锥进气道的锥角进行气动优化,优化后的进气道总压恢复系数提高了11.96%.数值模拟结果与试验数据吻合较好,证明优化结果可信.结果表明,通过对进气道锥角的优化可快速找出最佳锥角组合.
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| 关 键 词： | 冲压发动机 进气道 气动优化 模拟退火算法 序列二次规划 数值模拟 |
Aerodynamic optimization research for contour of ramjet assisted projectile inlet |
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| WANG Xiao-rong,JIANG Gen-zhu,ZHOU Chang-sheng.Aerodynamic optimization research for contour of ramjet assisted projectile inlet[J].Journal of Solid Rocket Technology,2009,32(1). |
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| Authors: | WANG Xiao-rong JIANG Gen-zhu ZHOU Chang-sheng |
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| Institution: | College of Mechanical Engineering;NUST;Nanjing 210094;China |
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| Abstract: | Taking the ramjet assisted projectile as the research subject,in order to make the total pressure recovery coefficient maximal,the model of parameters and the numerical simulation to the flow field of the inlet was integrated by using the auto-optimizing platform.The strategy composed by SA and SQP was used to optimize the double cone angle based on the highest total pressure recovery coefficient.After the optimization,the total pressure recovery coefficient of the inlet is increased by 11.96%.The numerical... |
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| Keywords: | ramjet engine inlet aerodynamic optimization simulated annealing sequential quadratic programming numerical simulation |
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