一种短航程再入解析预测校正制导方法

针对载人探月飞船高速再入返回问题，提出了一种短航程低过载的再入解析预测校正制导方法。引入大升阻比航天器滑翔式再入的概念，通过设定再入过程中滑翔段轨迹形式，利用轨迹参数描述滑翔段轨迹，推导出预测航程的解析公式。为使终端误差满足要求，通过试位法校正轨迹参数，并换算得到倾侧角制导指令。在偏差条件下进行仿真，实现了飞船2100km任务航程下400~450s内以低于6.5g₀的过载再入，结果表明，所提制导方法具有较高的精度和较强的鲁棒性，为载人探月飞船应急快速返回提供了参考思路。 

An analytical predictor-corrector guidance method designed for spacecraft reentry with short range

For the manned lunar return spacecraft reentry problem, an analytical predictor-corrector guidance method for short range reentry is proposed. Firstly, the concept of glide reentryis introduced, which has been studied in the trajectory design of high lift-to-drag ratio vehicle.In order to pre-design the reentry trajectory, a trajectory parameter is chosen to describe the analytic trajectory form, and then the analytical formula to predict the range-to-go is derived. The false position method is used to modify the trajectory parameter and finally converts to the command bank angle, eventually satisfying the terminal precision requirements. The proposed analytical method succeeds in achieving spacecraft reentry with a mission range of 2 100km in 400-450 seconds. During the entire reentry phase, the loads are under a level of 6.5 g₀, which is beneficial to manned spacecraft emergency return situation. Simulation has proved that this method has relatively high accuracy and robustness.