Hypersonic glider control using higher order sliding mode control

Hypersonic glider is a new class of missile being developed. It characterized by sub-orbital velocities and cruising altitudes in the 40-50 km altitude. They pose a very challenging control problem in that their aerodynamic model and eventual propulsion models are largely uncertain. This paper proposes a higher order sliding mode control solution to the problem, where the flight path angle rate and ground track angles are controlled using the angle-of-attack and roll angle as control parameter. Simulation results present the flight profile and the wide reach footprint of this type of vehicle. They show that the proposed control solution achieves excellent results.