摘要
该文以螺旋导轨式火箭弹及其发射系统为研究对象，采用拉格朗日方法建立了多管火箭发射系统在其发射过程中２ 个主要阶段，即约束期和半约束期时系统的动力学方程。考虑各个扰动因素，如推力偏心、动不平衡、质量偏心等对整个系统的作用。通过计算机模拟仿真，得到火箭弹各个起始扰动量，与试验结果十分吻合。因此拉格朗日方法在发射动力学中的应用为火箭弹起始扰动的计算提供了一个有效而且简便的方法。也为采用某些数学方法（如协方差描述函数法）进一步研究火箭发射系统的统计性能作了必备的前提工作。
In this paper Multiple Launchers Rocket System [MLRS] with helical rails is studied. The dynamic equations of system are established in Lagrange method in two stages,namely,control stage and half control stage. All kinds of disturbance such as thrust deflection,free unbalance,mass deflection are considered. Initial disturbance is gained by computer simulating. Its result is similar to that of experiment, which proves the method is right.So the study makes an easy way for launching research of MLRS and prepares for applying some mathematics methods (such as CADET)in the statistic field of MLRS.
出处
《南京理工大学学报》
EI
CAS
CSCD
1999年第4期336-339,共4页
Journal of Nanjing University of Science and Technology
关键词
拉格朗日方法
起始扰动
火箭弹
建模
Lagrange methods, initial disturbance, rocket projectiles
