论文部分内容阅读
本文以某机载武器为研究对象,建立了导弹与载机的三维数学模型,采用基于kw-SST湍流模型的雷诺平均N-S方程求解,数值模拟了机弹分离过程。通过流场气动参数分析,研究了导弹下滑过程的动态特性,获取了导弹安全分离边界,以及适合折叠弹翼、折叠尾翼展开的条件,研究结果对其它型号导弹的研制工作具有一定参考价值。
In this paper, we take a certain airborne weapon as the research object, established a three-dimensional mathematical model of the missile and the carrier aircraft, and solved the Reynolds-averaged Navier-Stokes equations based on the kw-SST turbulence model. Through the analysis of the aerodynamic parameters of the flow field, the dynamic characteristics of the missile sliding process are studied, the missile separation safety boundary is obtained, and the conditions for the folded wing and the folded tail are obtained. The research results have certain reference value for the research and development of other missile types.