Numerical Predictor-Corrector Re-entry Guidance Algorithm for Aerospace Vehicles

Abstract

The numerical predictor-corrector re-entry guidance algorithm is proposed for aerospace vehicles(ASV). Firstly, over the spherical rotating Earth, the three degree of freedom dynamical model of ASV is established in the launch coordinate system and the trajectory constraints are analyzed for the re-entry phase. Then, the predictor-corrector entry guidance algorithm numerically computes a complete entry trajectory onboard repeatedly based on the current state and required targeting condition, and the required bank angle command can be computed by the selected iterative algorithm to achieve the guidance accuracy. Simultaneously, a bank reversal logic is given by online prediction of the cross-range for the lateral guidance. Moreover, in order to avoid the numerical divergency problem at the end of re-entry phase due to the range-to-go tends to zero, the total re-entry range is used to replace the range-to-go in the corrector algorithm, particularly the adaptive iterative algorithm is employed to guarantee the convergence and accuracy of the predictor-corrector guidance algorithm. Finally, numerical simulations have been carried out to test the validity of the proposed entry guidance algorithm. The simulation results demonstrate that the re-entry guidance works well and has a good performance.