基于GPS简易制导火箭弹控制系统设计研究  

Control System Design of Simple Guided Rocket Based on GPS

作　　者：杨泗智 王全忠 尹刚 张博浪 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]西北工业集团有限公司,陕西西安710043

出　　处：《现代防御技术》2016年第2期55-60,91,共7页Modern Defence Technology

摘　　要：提出了一种基于GPS简易制导火箭弹的比例导引加重力补偿的控制方法。制导火箭弹利用GPS的实时测量的飞行状态参数,并与目标的运动状态参数进行对比,生成弹目视线角(lineof-sight,LOS)的变化率,随后按照比例导引律进行制导控制。并利用简易惯导系统进行重力补偿,可以实现纯比例导引律的功能,同时可有效增大末端落角,提高作战毁伤效能,具有一定的工程实际意义。A design princip guided rocket has been proposed e of the proportional navigation and the gravity compensation for the The guided rocket makes use of real time flight information measured by GPS, and is compared with the motion state information of the target, which generates the rate of the line of sight （LOS）. According to the proportional guidance law for guidance and contro tial navigation system for gravity compensation is used, which can realize the function of l, th a simple iner- e pure propor- tional guidance law, and at the same time can enlarge the terminal angle, and effectively improve the combat damage effectiveness. The principle has some actual engineering significance.

关 键 词：全球定位系统 制导火箭弹 比例导引律 重力补偿 惯导 末端落角 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]