Title :
Application of H/sup /spl infin// control to pitch autopilot of missiles
Author :
Yang, S.M. ; Huang, N.H.
Author_Institution :
Inst. of Aeronaut. & Astronaut., Nat. Cheng Kung Univ., Tainan, Taiwan
Abstract :
The pitch rate control of a missile is analyzed by an H ∞ controller. The system dynamics governing the aerodynamic stability derivatives and airframe structure vibration is formulated in a generalized state space realization form. This formulation facilitates the γ-iteration method in solving the associated Ricatti equation of the 4-block H ∞ control problem. It is shown that the H ∞ controller, because of its loop shaping capabilities, can provide improved tracking performance and stability robustness compared with H 2 (linear-quadratic-Gaussian (LQG)) and classical proportional-integral-derivative (PID) controller in the rigid airframe model. When airframe flexibility effect is considered, the H ∞ controller is also shown to be robust under structure natural frequency variations.
Keywords :
H/sup /spl infin// control; Riccati equations; attitude control; boundary-value problems; closed loop systems; control system synthesis; flexible structures; missile control; multivariable control systems; robust control; state feedback; state-space methods; /spl gamma/-iteration method; 4-block control problem; H/sup /spl infin// control; Ricatti equation; aerodynamic stability derivatives; airframe flexibility effect; airframe structure vibration; closed-loop system; flexible airframe model application; generalized state space realization; improved tracking performance; loop shaping; missiles; multivariable system; natural frequency variations; pitch autopilot; pitch rate control; rigid airframe model; stability robustness; suboptimal controller; system dynamics; Aerodynamics; Equations; Missiles; Pi control; Proportional control; Robust control; Robust stability; Shape control; State-space methods; Tracking loops;
Journal_Title :
Aerospace and Electronic Systems, IEEE Transactions on
