摘要
通过有限元法和试验模态分析技术获取某火箭炮的固有振动特性,经过建模进行响应历程模拟和实弹射击测试分析,得到火炮连发射击时的振动规律,找到炮口振动与火箭弹落点散布的定量关系。在此基础上,设计和制造了火箭炮最佳点火时机控制系统,与减振技术等相结合,使某炮连发射击的方向密集度提高20%。
A quantitative analysis between the rocket hitting distribution and launcher vibration is presented. The inherent vibration is obtained through the aid of FEM as well as techniques of test mode analysis. Analysis of the forced vibration of the launcher is carried out by simulating the response history and analysising the live firing test. Based on these results, a firing control system for optimal timing of the launcher has been designed which in combination with damping techniques, enabled the direction concentration in continued firing of the launcher to be improved by 20%.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
1993年第4期17-22,共6页
Acta Armamentarii
关键词
振动
火箭炮
射击
密集度
vibration, experimental modal analysis, rocket launcher, hitting distribution of projectiles, optimal firing
