Abstract: 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.

Key words: Launch vehicle, Adaptive prediction compensation, Iterative guidance, Deviation correction of orbit parameters, Correction of terminal program angle