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 H2 (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.
|Number of pages||8|
|Journal||IEEE Transactions on Aerospace and Electronic Systems|
|Publication status||Published - 1996|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Electrical and Electronic Engineering