一种近程简易制导火箭方案设计和仿真  

Research on General Guidance Module for Short-Range Terminal Trajectory Correction Rocket

作　　者：张敬敏 章浩飞 刘佳兴 ZHANG Jingmin;ZHANG Haofei;LIU Jiaxing(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;No.208 Research Institute of China Ordnance Industries,Beijing 102202,China)

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国兵器工业第二〇八研究所,北京102202

出　　处：《兵器装备工程学报》2019年第11期40-44,共5页Journal of Ordnance Equipment Engineering

摘　　要：提出了一种低成本、简易制导火箭设计方案。方案采用捷联激光导引头探测目标的位置信息,经信息处理后,通过弹上环状微脉冲推力器作用,实现对火箭弹道的修正。系统建模、仿真分析和试验表明:通过合理匹配简易制导火箭导引头开机时间、起控时刻、脉冲推力器总冲等参数,可使脱靶量小于1.2m,能够满足单兵火箭对目标命中精度的要求,且大幅降低了制导火箭成本,具有重要的工程参考价值。General guidance module was proposed,through the integration and the generalization of the guidance control module,it implemented conventional munitions guidance for implementing individual short-range trajectory correction at the end about the rocket.The laser seeker at the head about the guidance module can receive location information to the target,through the information processing system,controls the annular micro pulse thruster on the guidance module effect,thus corrected the trajectory about rocket.By trajectory characteristics simulation,it calculated the effect on the control start time and the impulse about a single pulse thruster on the correction ability,at the same time analyzed the effect about the launch velocity error and launch angle error on the accuracy.Results show that the correction ability increases with the increase about the impulse on a single pulse thruster,but not the greater total impulse,the earlier control time,the higher the accuracy,the control time and the impulse on a single pulse thruster were needed to ensure by the parameters about rocket and trajectory characteristics etc.The effectiveness on guidance module and the method about determining the key parameters were verified by simulation and experiment,and it has certain engineering reference value.

关 键 词：单兵火箭 制导模块 脉冲推力器 弹道修正 

分 类 号：TJ413[兵器科学与技术—火炮、自动武器与弹药工程]