Design of Optimal Flight Controller for Generic Linearised Missile Model in Hypersonic Regime

This report presents a multivariable controller design for a generic missile travelling at hypersonic speed. The controller is based on the theory of optimal control, and the solution is provided by a feedback controller known as a Linear Quadratic Regulator (LQR) for tracking the demands (lateral acceleration and roll rate) as closely as possible while keeping the actuator efforts (for deflecting aileron, elevator and rudder) small. In the computer simulation, the missile model is subject to various hypersonic flight conditions and gain scheduling is exercised as a function of dynamic pressure. The intial study assumes perfect knowledge of all the states for the controller design. Subsequently, a state observer (kalman filter) is introduced into the design to reflect a more practical synthesis where some of the states need to be estimated. RELEASE LIMITATION Approved for public release Published by Weapons Systems Division DSTO Defence Science and Technology Organisation PO Box 1500 Edinburgh South Australia 5111 Australia Telephone: (08) 7389 5555 Fax: (08) 7389 6567 © Commonwealth of Australia 2010 AR-017-787 July 2010 APPROVED FOR PUBLIC RELEASE Design of Optimal Flight Controller for Generic Linearised Missile Model in Hypersonic Regime