基于数值仿真与飞行试验的弹道修正火箭弹阻力系数简易辨识  

Drag coefficient identification of trajectory corrected rockets based on numerical simulation and flight test

作　　者：郭庆伟[1] 宋卫东[1] 王毅[1] 卢志才[1] 

机构地区：[1]军械工程学院火炮工程系,河北石家庄050003

出　　处：《中国测试》2016年第6期127-133,共7页China Measurement & Test

基　　金：中国博士后科学基金(2013M542454);十二五装备预先研究项目(9140A05040114JB34015)

摘　　要：作为单通道鸭舵控制弹道修正火箭弹研究的关键技术之一,气动系数的辨识是实现弹体飞行控制的前提与基础。该文以阻力系数简易辨识为主要研究内容,主要探讨数值仿真与飞行试验相结合对阻力系数进行辨识的方法。利用Grigen网格划分技术和Fluent流体力学仿真(CFD)相结合,获得弹道修正火箭弹的仿真气动数据;通过弹体的受力和力矩分析,建立六自由度弹道模型;根据飞行试验数据,对比分析弹道模型与仿真气动数据,对阻力系数进行修正优化。通过试验验证,经过修正的阻力系数精度得到很大提高,对于研究弹道修正弹的弹道特性规律和制导控制设计具有参考价值。As the critical technology of the canard-corrected rocket in single channel control,aerodynamic parameters identification is the foundation and precondition for projectile guidance.This paper focuses on drag coefficient identification and mainly involves the method of the incorporation between numerical simulation and flight test. With the contribution of Grigen gridding division technology and Fluent fluid dynamic simulation, the emulation aerodynamic parameters has been conducted. From analysis of forces and moments acting on the projectile,the six degrees of freedom dynamic model was given. The flight test data has be used to make a comparison of fight data and the simulation data and provides the optimization proposal for the drag coefficient. In the end, the demonstration tests indicate that the optimized drag coefficient has a better precision that could be provide significant reference for the projectile trajectory characteristics and the guidance law design.

关 键 词：弹道修正火箭弹 数值仿真 飞行试验 系数辨识 

分 类 号：V448.23[航空宇航科学与技术—飞行器设计]