带控制舵弹体气动特性分析  

Numerical analysis of aerodynamics for missile with control-flaps

作　　者：杨永健[1] 张来平[1] 高树椿[1] 张涵信[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2003年第4期482-488,共7页Acta Aerodynamica Sinica

摘　　要：本文用数值模拟方法研究了带控制舵弹体的气动特性。该问题外形复杂,在控制舵和弹身之间会出现明显的缝隙。为了解决此类外形的气动力计算问题,我们发展了结构网格和非结构网格的混合网格技术。这样一方面充分发挥了贴体结构网格质量好、效率高的优点,另一方面充分发挥了非结构网格几何灵活性好、易于模拟复杂外形的优点。数值计算与风洞实验相当吻合,说明本方法具有良好的精度。最后对两种外形进行大量计算并进行气动特性分析,给出了静稳定特性和配平特性的研究结果。The simulation of the non-viscous problems of missile with control-flaps is presented in this paper. It is very difficult to simulate this configuration that have a very narrow gap between missile body and control-flap. To solve Euler equations for the complex body in better quality grid and high efficiency, hybrid grid technique that combine the structure grid with unstructured grid is presented. This grid is easier to fit for the configuration. The results show the agreement of present with wind tunnel test. Finally, a great amount of results of two different configurations are given. Via sufficient validation of the reliability of the calculation results, the aerodynamic performance of missile with flaps are analyzed, especially the static stability and trimming characteristics are discussed.

关 键 词：控制舵 气动特性 数值模拟 机动飞行 弹体 

分 类 号：TJ760.11[兵器科学与技术—武器系统与运用工程]