Closed Loop Control System for Wing Stability

Project goal: To design, build and test a detailed control system within a wing model to discover the wing’s aerodynamic characteristics, such as frequency and flutter. A closed-loop system was designed and implemented that would allow the wing to correct itself and remove any unnecessary flutter while optimizing flight conditions. The objective of this design is a closed-loop control system that stabilizes the wing section when the angle of attack is disturbed from its desired position. Sensors were placed on the top and bottom surfaces to measure the free stream velocity. Sensor data is sent to a proportional integral derivative controller, which generates the desired values.