The pitch rate control of a missile is analyzed by an Hinfinity 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 gamma -iteration method in solving the associated Ricatti equation of the 4-block Hinfinity control problem. It is shown that the Hinfinity controller, because of its loop shaping capabilities, can provide improved tracking performance and stability robustness compared with H2 (linear-quadratic-Gaussian (LQG)) and classical proportional-integral-derivative (PID) controller in the rigid airframe model. When airframe flexibility effect is considered, the Hinfinity controller is also shown to be robust under structure natural frequency variations.
Application of Hinfinity control to pitch autopilot of missiles
Die Anwendung eines H<sup>unendlich</sup>-Reglers beim Autopiloten von Raketen
IEEE Transactions on Aerospace and Electronic Systems ; 32 , 1 ; 426-433
1996
8 Seiten, 15 Quellen
Article (Journal)
English
Application of H(infinity) Control to Pitch Autopilot of Missiles
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