末修姿控段战略导弹弹道仿真模型及散布分析

THE TRAJECTORY SIMULATION MODEL AND DISPERSION ANALYSIS FOR A STRATEGY MISSILE IN THE FINAL POWERED PHASE OF VELOCITY REVISION AND ATTITUDE CONTROL

导出了适用于末修姿控段弹道仿真的数学模型，用求差法算出了由于后效冲量及其偏差引起的主动段终点参数散布，找出了引起散布的主要因素，为现有及未来战略导弹的精度分析提供了直接依据．

In this paper, a group of trajectory simulation equations for velocity revision and attitude control in the final powered phase have been established, the motion paramenters dispersion at the terminal point of powered phase caused by delayed impulse and its deviations have been calculated with the methed of seeking difference, found out the primary factors of dispersion, provided the direct basis for accuracy analysis of strategy missile at the present and the future.