弹翼部件巡航状态受力分析

Stress Analysis of Missile Wing under the Condition of Cruise

研究了某类型弹翼部件在巡航状态下的应力、应变状况。先建立弹翼三维实体模型,并利用计算机仿真技术,加载了弹翼在巡航过程中所受到的各种载荷。然后采用有限元分析的方法,得到弹翼在巡航状态下的应力、应变数据,验证了弹翼结构设计的合理性,进而为弹翼翼型参数的研究提供依据。

The stress strain condition of certain kinds of missile wings under the condition of cruise was studied. The data of stress strain was obtained by simulating all kinds of loads on the three-dimensional model structure of missile wings under the cruising condition. Then, the finite element analysis was employed. The purpose of the paper is to analyze whether the structure of missile wings meets the requirements of design and provide the basis for parameter study of missile wings.