Hypersonic guidance via the state-dependent Riccati equation control method

In this paper, the state-dependent Riccati equation (SDRE) control method is used to design a guidance law for the midcourse phase of flight of a hypersonic vehicle. The guidance law converts flight path angle and heading angle commands to angle of attack and bank angle commands for input to an attitude autopilot.

[1]  N. Vinh,et al.  Hypersonic and Planetary Entry Flight Mechanics , 1980 .

[2]  J. Cloutier State-dependent Riccati equation techniques: an overview , 1997, Proceedings of the 1997 American Control Conference (Cat. No.97CH36041).

[3]  Michael J. Wozny,et al.  Computer Aided Multivariable Control System Design Package , 1982, 1982 American Control Conference.