Mars Entry Guidance Based on Predicted Corrector Algorithm

Abstract

This paper describes the development and evaluation of the common numerical predicted corrector algorithm and gives an improved algorithm for the Mars entry guidance. First, it introduces two guidance strategies:tracking the reference trajectory and predicted corrector algorithm, finding that the common predicted corrector algorithm can be less sensitive to initial dispersions, but needs fast on-board computation. Second, the downrange algorithm, lateral control logic and heading alignment are described in details, which are provided to improve the horizontal accuracy of the vehicles. Furthermore, the segmented guidance predicted corrector algorithm is used to shorten the on-board computational time. Simulation results show that this entry guidance algorithm demonstrates reliable and robust performance in situations with high uncertainties.

Keywords

entry guidance method / predictor-corrector / lateral control / heading alignment