提出了一种基于阻力加速度的预测-校正制导方法,首先通过对阻力加速度走廊插值获取阻力加速度剖面模型,并基于该模型进行数值轨迹预测。然后根据两次预测结果近似求出阻力加速度与航程的关系,实时校正阻力加速度,消除航程偏差。同时对攻角进行调整,消除高度误差。横向制导通过校正倾侧角翻转时机实现。与传统的迭代预测校正制导算法相比,论文的制导算法同时校正纵向运动和横向运动,提升了飞行器的再入制导能力。每一次校正只需两次弹道预测,减少了制导的计算量。另外,采用插值的阻力加速度剖面对过程约束具有更强的处理能力。通过打靶仿真验证,论文的制导算法具有较高的制导精度和鲁棒性。 A prediction-correction guidance method based on drag acceleration is proposed. Firstly, a drag acceleration profile model is obtained by interpolation of drag acceleration corridor, and numerical trajectory prediction is performed based on the model. Then based on the results of the two predictions, the relationship between the drag acceleration and the range is obtained approximately, and the drag acceleration is corrected in real time to eliminate the range deviation. At the same time adjust the angle of attack to eliminate a high degree of error. Lateral guidance is achieved by correcting the timing of tilting angle reversal. Compared with the traditional Iterative Predictive Correction Guidance Algorithm, the paper guidance algorithm corrects both longitudinal and lateral motion and enhances the reentry guidance ability of the aircraft. Only two ballistic predictions are needed for each calibration, reducing the amount of guidance required. In addition, the interpolated drag acceleration profile has more processing power than the process constraints. Through the simulation of targeting simulation, the paper’s guidance algorithm has high guidance accuracy and robustness.