火箭弹折叠尾翼的质量优化设计  

Optimization Design of Folded Wing for Rocket Projectile

作　　者：李双江[1] 邓克文[1] 陈小伟[1] 甄文强 陈强洪[1] 

机构地区：[1]中国工程物理研究院总体工程研究所,四川绵阳621999

出　　处：《兵工自动化》2016年第3期77-81,共5页Ordnance Industry Automation

基　　金：中物院总体工程研究所创新与发展基金(15CXJ13)

摘　　要：火箭弹作为一种飞行武器,弹体应具有良好的气动性能。弹翼作为火箭弹结构的重要部分,可以产生飞行升力和对弹体的操纵力,并能加强弹体飞行的稳定性。火箭弹尾翼的质量与其飞行性能相关,此以火箭弹尾翼的质量为优化目标,进行尾翼的轻量化设计。根据火箭弹飞行的空气动力学要求,在尾翼面积不变的条件下以尾翼翼根厚度和展向厚度变化量作为设计变量,以翼面受气动载荷时的最大挠度和翼面展开时间为约束变量。通过理论分析和数值计算,给出了设计变量的设计可行域,得到了尾翼质量的优化设计结果,其优化后质量比优化前减少41%。The rocket projectile should have well-designed aerodynamic performance, and the wings play an important role in the aerodynamics, such as providing the flight lift, operating force and flight stability of rocket. A lighter weight of the rocket folded wing may improve the flight performance of a rocket. Aiming to reduce the weight of a rocket, this paper conducts the optimization design of the folded wing. According to the requirements of the rocket flight aerodynamics, the surface area of the folded wing can＇t be changed. Under the weight optimization design of the folded wing, the root thickness and the thickness variation of the wing are the design variables, respectively. Meanwhile, the maximum deflection of the wing under aerodynamic load and the spreading time of the folded wing are constraint variables. The feasible area of the design variables are obtained after the theoretical analysis, and finally the weight optimization design of the folded wing are achieved. As the result shows, the mass of the folding wing is reduced 41 % after optimization.

关 键 词：火箭弹 折叠尾翼 质量 优化设计 设计可行域 

分 类 号：TJ415[兵器科学与技术—火炮、自动武器与弹药工程]