摘要
为了能利用自翻转技术实现导弹越肩发射,文中采用CFD技术研究细长体和舵身组合体的超大攻角气动力特性,采用动网格方法模拟导弹自动翻转掉头过程,分析了导弹自翻转的翻转条件和受力情况,揭示了细长体翻转自稳定现象,得到了舵控对翻转过程的影响,验证了自翻转越肩发射的性能技术指标,仿真结果为采用自翻转技术来实现越肩发射的导弹总体设计和控制设计提供了参考。
In order to realize self-turning technology of missile,in this paper,aerodynamic characteristics of slender body and rudder-fuselage body at extra-wide angle of attack were investigated by CFD technology,the process of missile turning was simulated by dynamic grid method,the range of aerodynamic force and the conditions of self-turning were evaluated,the phenomena of self-stabilization was revealed,the relationship between rudder control and turning process was found out,and the performance index of self-turning of missile was validated. The numerical result provides a reference for system design and control design of missile which employs self-turning method to realize over-shoulder launch.
出处
《弹箭与制导学报》
CSCD
北大核心
2015年第5期112-118,共7页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
上海市科学技术委员会项目(13QB1401500)资助
关键词
自翻转
超大攻角
气动特性
动网格
self-turning
extra-wide angle-of-attack
aerodynamic characteristics
dynamic grid
