Receding Horizon Optimal controller for reference trajectory tracking in Mars entry guidance

Abstract

In the process of the high-speed vehicle sentering a rarefied atmosphere with highly uncertainties as the Mars atmosphere, the trajectory deviation caused by entry guidance can be the major part of the total landing errors. To reduce the impact of model errors on guidance performance, a guidance law based on receding horizon control is developed for… (More)

10 Figures and Tables

Topics

  • Presentations referencing similar topics