摘要
以非线性瞬态动力学理论为基础,计算和分析了某型火箭发射过程中管内姿态情况。首先,以动力学理论为基础,建立了某型火箭炮系统发射过程中的弹管柔性相互作用模型;其次,借助数值仿真分析方法,对该模型进行了发射动力学仿真和分析,得到了火箭弹离轨时的滑离参数,通过比较可知,仿真结果与实验结果吻合较好。计算结果及结论可为今后该火箭炮系统的改进研究工作提供理论参考。
The posture of a rocket in launch tube was calculated and analyzed basel on the theory of non-linear transient dynamics. Firstly, the flexible interaction model of MLRS launching process was established bas on non-linear transient dynamics theories. Secondly, launching dynamical simulation and analysis of this model were conducted using numerical simulation methods. The rocket escape parameters were obtained, which match with experimental results very well. The content and method offer theory reference and basis for the improvement research of this type of MLRS.
出处
《弹箭与制导学报》
CSCD
北大核心
2008年第6期166-168,174,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
南京工程学院基金(KXJ08001)资助
