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Application of H/sup /spl infin// control to pitch autopilot of missiles

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2 Author(s)
Yang, S.M. ; Inst. of Aeronaut. & Astronaut., Nat. Cheng Kung Univ., Tainan, Taiwan ; Huang, N.H.

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.

Published in:

Aerospace and Electronic Systems, IEEE Transactions on  (Volume:32 ,  Issue: 1 )