Angle of attack control of a blended wing body aircraft using state feedback L1 adaptive controller

This paper explores the application of L₁ adaptive controller to a blended wing body aircraft configuration that divergence of angle-of-attack when landing at a low velocity without considering ground effect. The high angle of attack conditions make the blended wing body aircraft dangerously susceptible to gust loads which push the local angle of attack to near stall conditions, this will continuous prone leads to longitudinal and lateral instabilities. L₁ adaptive controller was designed at low speed. The results of simulation show that: L₁ adaptive controller can stabilize and meet the performance of the angle-of-attack of this blended wing body aircraft.