远程火箭弹捷联射程修正研究  

The Study of Range Correction of Long-Range Rocket with Strapdown Inertial Navigation System

作　　者：张成[1] 杨树兴[1] 王晟[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《北京理工大学学报》2005年第7期565-569,共5页Transactions of Beijing Institute of Technology

基　　金：教育部跨世纪人才培养计划基金资助项目 (10 0 762 0 2 1)

摘　　要：实现了姿态稳定后,抑制远程火箭的纵向散布上升为提高其射击效能的主要问题.通过数值仿真的方法,研究了采用捷联惯导技术后远程火箭射程修正效果.计算结果表明,捷联惯导的引入使射程修正效果大幅度改善,且采用二次修正模型比线性模型具有更高的方法精度.通过捷联惯导仪器误差的分析,发现二次模型对捷联惯导导航参数误差更为敏感,考虑惯导仪器误差后,线性模型的修正效果要优于二次模型.射程修正系统的方法误差随着导航时间的增加而减小,但由于导航参数误差有随着导航时间增加的趋势,惯导系统工作时间要综合考虑以上两方面因素后确定.After the attitude being stabilized, restraining the range dispersion of long-range rocket becomes the more important problem. The effect of range correction system of long-range rocket adopting SINS is analyzed through numerical simulation. The range correction efficiency can be enhanced obviously with strap-down SINS adopted, and the precision of the method for the quadratic model is higher than that for the linear model. After the instrument error of SINS is analyzed, it can be concluded that the quadratic model is more sensible to navigation error, and with instrument error taken into account, the linear model is better than the quadratic model.The range correction method error decreases with the navigation time but the instrument error increases, so the best navigation time should be chosen with both sides considered.

关 键 词：远程火箭 射程修正 捷联惯导 导航时间 导航参数误差 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]