反坦克导弹末制导稳定性及对精度影响分析  

Trajectory Stability and Precision Analysis of Proportional Navigation Law

作　　者：杨凯 张建灵 严宪军 

机构地区：[1]中国兵器工业第203研究所,西安710065

出　　处：《弹箭与制导学报》2015年第3期23-26,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中为了分析导弹末制导稳定性及其对精度的影响,首先研究了比例导引弹道稳定条件,提出了比例导引弹道稳定性设计和分析方法。其次,对直升机载反坦克导弹系统误差源进行分析建模,利用精度分析方法设计出精度分析系统。最后依靠高精度、高准确度的误差源模型及文中设计的精度分析系统进行大量数字仿真试验,得到置信度高的精度分析结果和末制导控制系统考核结果。In order to analyze stability of missile in terminal guidance and its impact on accuracy, condition of trajectory stability based on proportional navigation law was studied Firstly. The design and analysis methods on trajectory stability based on proportional navigation law were proposed. Then, error source of helicopter-borne antitank missile system was modeled and the analysis system on accuracy was de- signed by using precision analysis methods. Finally, relying on the error source model which has high precision and accuracy and the analysis system on accuracy designed in this paper, digital simulation tests were completed and the accuracy analysis result with high confidence and the assessment result of terminal guidance control system were obtained.

关 键 词：反坦克导弹 比例导引规律 弹道稳定性 精度分析 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]