To solve the problems of multi-restriction and uncertainty in reentry guidance of hypersonic vehicles,a predictor-corrector guidance method based on waypoint programming was established,integrating the advantages of the standard trajectory guidance and predictive-corrector guidance,and the accurate guidance model and guidance theory were derived .To eliminate the effect of model dynamic parameters,the numerical predictive arithmetic was improved,then a predictor-corrector guidance law based on optimal quadratic index was designed,and a numerical analytic solution was derived .With the attitude control loop considered as a second order system,a trajectory simulation was made between two waypoints .The result shows that this method has high precision and robustness,and is insensitive to the initial errors .%针对高超声速飞行器再入制导多约束、不确定性问题，结合预测-校正制导和标准航迹制导的优点，提出基于航路点规划的预测-校正制导方式，推导出精确的制导模型和制导原理。针对制导模型参数的动态性能，改进了数值预测算法，并基于二次型最优性能指标设计了预测-校正制导律，给出了制导指令数值方法的解析解，符合高超声速制导的实时性要求。将姿态控制回路近似描述成二阶系统，基于已规划航路进行了仿真验证，仿真结果表明，该方法对初始误差不敏感，具有较高的精度和较强的鲁棒性。
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