地-地战术导弹全程惯性制导弹道技术  

Full-distance inertial guidance trajectory technique for ground to ground missile

作　　者：程养民[1] 

机构地区：[1]中国航天科技集团公司四院设计部,西安710025

出　　处：《固体火箭技术》2007年第5期369-371,380,共4页Journal of Solid Rocket Technology

摘　　要：利用比例导引弹道原理及弹道仿真，分析了150～250km射程范围地-地战术导弹全程惯性制导弹道的设计原理。其弹道特征一般由熄火点、转弯点、俯冲点和目标点4个特征点组成，射程的改变通过改变转弯点、俯冲点和目标点3点的参数实现。通过弹道仿真研究，给出了各特征点的功能和选取原则，分析了全程制定控制弹道方案的优缺点。Design principle of full-distance inertial guidance trajectory for ground to ground missile in range of 150 -250 km was analyzed by means of proportional guide trajectory theory and simulation calculation. The trajectory features consist of four characteristic points, such as flameout point, turning point, dive point and target point. The range of missile can be changed by adjustment of three parameters （turning point, dive point and target point）. Function and selection principle of four characteristic points were given through trajectory simulation investigation. Advantages and disadvantages of full-distance trajectory control scheme were analyzed.

关 键 词：地-地导弹 全程制导 弹道原理 设计原则 弹道仿真 

分 类 号：V448.23[航空宇航科学与技术—飞行器设计]