Optimal setpoint controller for a generic X-29A aircraft with forebody vortex nozzles

This paper presents the design, synthesis, and performance of an optimal setpoint high angle-of-attack lateral/directional 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 effecters can be modulated to improve the closed-loop response compared to a controller design which uses only the aerodynamic control effecters