Aerodynamic characteristic of a canard guided rocket
Aerodynamic characteristic of a canard guided rocket
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DOI：
10.1142/s1793962317500015
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发表时间：
2017-03-01
影响因子：
1.2
通讯作者：
Lv, Hui-Miao
中科院分区：
文献类型：
--
作者：
Chen, Yong-Chao;Gao, Xin-Bao;Lv, Hui-Miao
采用计算流体力学（CFD）数值模拟方法研究了基于高质量点对点多块结构网格技术的鸭式制导火箭的气动特性。数值模拟和实验结果表明，该方法具有较高的可信度，可以应用于具有可装配构型的火箭。鸭式制导火箭采用不同的机鼻、鸭翼和尾翼设计。采用有限体积法对N-S方程进行数值求解，并采用多网格法加快收敛速度。利用这些策略对火箭、机头、鸭翼和翼的气动特性进行了推导，并总结了变化规律。研究结果将为制导火箭在工程设计中的优化提供支持。
The computational fluid dynamics (CFD) numerical simulation was used to investigate the aerodynamic characteristic of a canard guided rocket based on the technology of high quality point-to-point multi-block structured grid. The results of numerical simulation and experiments showed that the method is highly credible, and the method could be used to the rockets with semblable configurations. The canard guided rocket was designed with different noses, canards and fins. The N-S equations were solved numerically by the finite volume method, and the multi-grid method was adopted to accelerate the convergence. With these strategies the aerodynamic characteristics of rocket, nose, canard and fin were educed, and the change law was summarized. The results will provide the support for the optimization of anard guided rocket in engineering design.