第三章研究了基于先验弹道模板的主动段战术参数估计与落点预报问题。
Chapter III studies tactical parameters estimation of boost phase and impact position prediction problems based on prior trajectory profile.
如果能在火箭主动段加一套简易的控制系统来控制火箭的姿态，则将大大提高火箭的命中精度。
The precision of hitting will be improved obviously if we can offer a set of simple guidance control systems in powered phase of the rocket projectile.
为使飞行器能在主动段很快地进入到理想弹道上，系统采用了非线性的推力向量控制及预测制导方法。
In order to enter into the ideal trajectory with minimal energy, the nonlinear thrust vector control and the prediction guidance are adopted in the missile guidance control system.
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