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. DESIGN OF A RIGID CONTROL LAW
A static output feedback K assigns the closed loop eigenstructure, and a static feedforward H introduces the pilot demands in the closed loop, which is summarized in Figure 2.1.
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The gain matrix K is synthesized with a classical modal approach with decoupling objectives. The poles of the open loop aerodynamic model (i. e. the rigid model without actuators) are:
3.4ІЄ-03 – l. OOe+OO -5.Ole-02 + 6.74e-01i 7.4ІЄ-02 -5.0ІЄ-02 – 6.74e-01i 7.4ІЄ-02 -8.59Є-01 l. OOe+OO
The corresponding closed loop poles are chosen as:
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Damping Freq. (rad/s)
