Engineering Application Analysis of Terminal Attitude Constrained IGM Based on Parabolic Feature*

Abstract

Iterative guidance method(IGM) is a kind of optimal guidance law. It can automatically schedule the flight path according to the optimal conditions and correct the orbit deviation by changing the direction of the thrust vector to achieve the precise orbit. However, the problem is that the attitude of the rocket into orbit’s time must be determined by the thrust vector direction and cannot be predetermined. Otherwise, the deviation of the last moment of the thrust vector may make the accuracy of the iterative guidance difficult. Based on the traditional IGM, a terminal attitude constraint Iterative guidance method(TACIGM) based on parabolic feature is proposed for the problem that the traditional IGM can not carry on the attitude constraint. The results show that the TACIGM can meet the accuracy of the traditional IGM, but also can meet the high accuracy of the orbit attitude, and It can adapt to the variation of the attitude angle. The method will have a high engineering application value.