Predictor-Corrector Guidance Based on Optimization

A new guidance algorithm based on a predictor-corrector approach is presented. The algorithm was designed for the re-entry guidance of the axisymmetric hypersonic vehicle. For this purpose, the angle-of-attack was considered to be the only input. We cast the re-entry guidance problem as a constrained optimization problem, then translated the constrained optimization problem into an unconstrained optimization problem using exterior point penalty function method and solved the unconstrained optimization problem using the steepest decent method. Altitude and range errors computed from the desired and achieved state at the terminal point were used to correct the angle-of-attack variables. Simulation results show that the algorithm developed in the paper is able to solve the re-entry guidance problem of the axisymmetric hypersonic vehicle and satisfies both terminal and path constraints.