An ascent iterative guidance algorithm for solid rocket concerned with multiconstraints

This paper is concerned with ascent guidance for solid rocket, whose kinetic parameter with large deviation at each stage is a challenging problem for terminal multiconstraints. A guidance algorithm based on least square method and Newton iteration is developed at each stage to solve this problem. The angle of attack (AOA) and yaw angle of current stage are main variables and these angles of the latter stages are instrumental variables. Closed-loop iterative guidance is applied in last phase of the third stage. In the simulation part, two integrated guidance methods (IGM) containing perturbation and iterative guidance applied for different stages and one method of iterative guidance for three stages (IGTS) are analyzed to compare the performance of these guidance algorithms. The results show that the second IGM can effectively revise the influence of the thrust deviation produced by the first and second stage, whose robustness is better than the first IGM. In addition, the robustness of the IGTS is best compared with the first and the second IGM, and the range of propulsion error that the IGTS can fix is the largest among these methods.