自适应预测补偿的迭代制导方法及其应用研究

针对迭代制导完成后入轨参数或终端程序角修正问题，研究一种基于模型参考的自适应预测补偿迭代制导算法在运载火箭上的应用。该算法在经典迭代制导算法的基础上，根据预测的迭代终端程序角和飞行视加速度的参考模型，对关机点参数进行补偿，依据补偿后的终端指标重新规划飞行轨迹，进而得出满足入轨参数或终端程序角偏差修正的制导指令，提升迭代制导对入轨参数偏差或终端程序角的修正能力。此外，阐述了经典迭代制导的基本算法，概括了自适应预测补偿迭代制导算法的基本原理，并以大推力直接入轨、终端程序角大偏差以及满足终端程序角约束为例，给出相应工况的自适应预测补偿的迭代制导算法。仿真结果表明：该算法对入轨参数和终端程序角偏差具有一定的修正能力。

Study and Application of Iterative Guidance Algorithm with Adaptive Prediction and Compensation

Aiming at solving the problem of correcting injection parameters or terminal program angular correction after using classic iterative guidance method, an adaptive prediction compensation iterative guidance algorithm based on model reference is studied for the application of launch vehicle. Base on the classical iterative guidance algorithm, this algorithm compensates the parameters of shutdown points in time according to the reference model of the predicted iterative terminal program angle and flight acceleration. The flight trajectory is reconstructed according to the compensated terminal parameters, and then the guidance command satisfying the correction of the orbital parameters or terminal program angular deviation is obtained, so as to improve the correction ability of the adaptive prediction iterative guidance algorithm. In addition, the basic algorithm of classical iterative guidance is expounded, and the basic principle of adaptive predictive compensation iterative guidance algorithm is summarized. Taking the direct orbital injection scenario with large thrust, large deviation of terminal program angle and meeting the constraint of terminal program angle as examples, the iterative guidance algorithm of adaptive predictive compensation under corresponding working conditions is given. The simulation results show that the algorithm has a certain correction ability for the orbital parameters and terminal program angle deviation.