推力偏心影响下火箭弹离轨姿态研究  

Off Orbit Attitude of Rocket Under Influence of Thrust Eccentricity

作　　者：何自力 马新谋[1,2] 于欢 岳光[1,2] 潘玉田 HE Zili;MA Xinmou;YU Huan;YUE Guang;PAN Yutian(College of Mechatronic Engineering,North University of China,Taiyuan 030051,China;Research Institute of Collaborative Innovation of Military Civilian Integration,North University of China,Taiyuan 030051,China)

机构地区：[1]中北大学机电工程学院,太原030051 [2]中北大学军民融合协同创新研究院,太原030051

出　　处：《兵器装备工程学报》2020年第2期25-29,66,共6页Journal of Ordnance Equipment Engineering

摘　　要：建立了火箭弹离轨发射过程的起始扰动时的推力偏心数学模型,给出了火箭弹下沉量计算公式。采用虚拟样机方法,利用ADAMS动力学软件建立同时离轨火箭弹发射动力学模型,对不同推力偏心下火箭弹离轨过程进行了仿真分析,结果表明:发动机推力偏心对质量大、初速低的火箭弹离轨姿态扰动明显,离轨过程姿态角逐渐增大,增大火箭弹发射的起始扰动;火箭弹离轨安全性随推力偏心角的增大而降低,在发射箱的结构设计中应充分考虑推力偏心影响带来的离轨安全性问题,尽量选择较大射角进行发射。The mathematical model of the thrust eccentricity of the initial disturbance in the rocket launching process was established,and the calculation formula of the rocket’s subsidence was given.Using virtual prototyping method and Adams dynamics software,the launch dynamics model of the rocket was established,and the simulation analysis was carried out on the process of the rocket’s derailment under different thrust eccentricity.The results show that the engine thrust eccentricity has obvious disturbance on the attitude of the rocket with large mass and low initial velocity,and the attitude angle gradually increases during the derailment process,increasing the initial disturbance of the rocket’s launch.The derailment safety of rocket decreases with the increase of thrust eccentricity.In the structural design of launching box,the derailment safety caused by thrust eccentricity should be fully considered,and the larger launching angle should be selected as far as possible.

关 键 词：推力偏心 同时离轨 虚拟样机方法 ADAMS 仿真 

分 类 号：TJ415[兵器科学与技术—火炮、自动武器与弹药工程]