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A specific z-plane control design technique is used to design the pitch axis controller for the Grumman F - 14 aircraft. Simulations show that the angle-of-attack (sampled-data) step response of the system satisfies the design specifications. Due to the sampling, a non-minimum phase zero is induced in the plant which makes the controller unstable. An attempt is also taken to stabilize the controller via the HÂ¿ model-matching technique.
American Control Conference, 1993
Date of Conference: 2-4 June 1993