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

摘要

This paper presents the design, synthesis, and performance of anoptimal setpoint high angle-of-attack lateral/directional controller forthe X-29A aircraft equipped with forebody vortex flow control nozzles.The closed-loop control law is full state feedback, and is synthesizedusing a linear time-invariant generic model of the X-29A. Resultsdemonstrate that by proper selection of the weighting elements, theforebody vortex nozzles together with the aerodynamic control effecterscan be modulated to improve the closed-loop response compared to acontroller design which uses only the aerodynamic controleffecters