按弹体响应辨识干扰并预测偏差的原理研究  

PRINCIPLES FOR THE IDENTIFICATION OF DISTURBANCE FACTORS AND PREDICTION OF FLIGHT DEVIATION IN A SPINNING MISSILE

作　　者：万春熙[1] 冀四梅[1] 王光 俞仁顺[1] 

机构地区：[1]北京理工大学

出　　处：《兵工学报》1995年第2期38-43,共6页Acta Armamentarii

摘　　要：提出了一种利用低成本捷联惯性系统的测量数据，对滚转的火箭或导弹弹体在弹道上受到的干扰因素进行辨识和根据这一辨识结果对飞行偏差进行预测的原理。在这原理基础上发展的技术，可用于对飞行过程的监测，也可用于火箭的制导。Fundamental principles for the identification of disturbance factors acting on a spinning flight vehicle are proposed.The identification is based on data measured by a low-cost,strap-down inerital system.Further,the fundamentals of predicting the deviation of the disturbed trajectory according to the results of identification is provided.On the basis of these principles,techniques can be developed for the observation and measurement of test missiles in flight and/or for the guidance of a rocket in the mid-course of its trajectory.

关 键 词：火箭 导弹 弹道干扰 飞行偏差 捷联惯性系统 

分 类 号：TJ760.12[兵器科学与技术—武器系统与运用工程]