Optimal Setpoint Controller for a Generic X-29a Aircraft with Forebody Vortex Nozzles
نویسنده
چکیده
This paper presents the design, synthesis, and performance of an optimal setpoint high angle-of-attack lateralldirectional controller for the X-29A aircraft equipped with forebody vortex flow control nozzles. The closed-loop control law is full state feedback, and is synthesized using a linear time-invariant generic model of the X-29A. Results demonstrate that by proper selection of the weighting elements, the forebody vortex nozzles together with the aerodynamic control effectors can be modulated to improve the closed-loop response compared to a controller design which uses only the aerodynamic control effectors.
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