A closed-loop flight control experiment using active flow control actuators

Kutay, Ali Türker
Muse, Jonathan A.
Brzozowski, Daniel P.
Glezer, Ari
Calise, Anthony J.
Closed-loop pitch control on a moving 1-DOF wing model is investigated in wind tunnel experiments. The model's attitude is controlled over a broad range of angles of attack when the baseline flow is fully attached using bi-directional pitching moment that is effected by flow-controlled trapped vorticity concentrations on the pressure and suction surfaces near the trailing edge. In the present work, the model is trimmed using a position feedback loop and a servomotor actuator. Once the model is trimmed, the position feedback loop is opened and the servomotor acts like an inner loop control to alter the dynamic characteristics and to introduce disturbances. Position control of the model is achieved by the flow control actuation using an arbitrary reference model based adaptive outer loop controller. The control architecture employs a neural network based adaptive element that permits adaptation to both parametric uncertainty and unmodeled dynamics.


Experimental trapped vorticity flight control using an augmenting error minimization adaptive law
Muse, Jonathan A.; Kutay, Ali Türker; Calise, Anthony J. (2008-01-01)
Closed-loop feedback control is used in a series of wind tunnel experiments to effect commanded 2-DOF maneuvers (pitch and plunge) of a free airfoil without moving control surfaces. The objective is to achieve control bandwidths that are beyond those achievable with mechanical control surfaces. Bi-directional changes in the pitching moment over a range of angles of attack are effected by controllable, nominally-symmetric, trapped vorticity concentrations on both the suction and pressure surfaces near the tr...
A comparison of two novel direct adaptive control methods under actuator failure accommodation
Kutay, Ali Türker; Calise, Anthony J.; Johnson, Eric N. (null; 2008-12-01)
In flight control systems it is crucial to accommodate actuator failures for safe operation. Modern flight control systems are equipped with multiple power sources and actuation systems that offer redundancy in the event of actuator failures. Traditional approaches to flight control system design involve scheduling of fixed gain controllers and control allocation to take full advantage of redundant actuators. Alternative adaptive control approaches have been extensively investigated recently to provide enha...
Investigation of rotor rotor interactions for two helicopters in forward flight using free vortex wake methodology
Tonkal, Ozan Çağrı; Pehlivan, Sercan; Sezer Uzol, Nilay; İşler, Veysi (null; 2010-07-01)
This paper presents an investigation of the aerodynamic interactions between two UH-1H helicopter rotors in forward flight. The wake flow structure and performance characteristics of the rotors are investigated when the rear rotor is operating within the wake of the front rotor. A 3-D unsteady vortex-panel method potential flow solver based on a free-vortex-wake methodology is used for this purpose. The solver is validated using the experimental data from the Caradonna-Tung experiments. The interactional an...
A novel flight control algorithm for multicopters
Tekinalp, Ozan (null; 2016-09-29)
A new nonlinear control algorithm is proposed for multi-copter type vertical takeoff vehicles. The algorithm uses linear controllers for the position control in the outer loop. The inner loop attitude control is carried out using quaternion representation. The necessary thrust vector requirements of the position control are converted to inner loop as attitude control commands. The inner loop uses a Lyapunov function based attitude controller utilizing the to-go quaternion calculated from thrust vector comma...
A novel force control traverse for simulating UAV flight in a wind tunnel
Muse, Jonathan A.; Kutay, Ali Türker; Calise, Anthony J. (2008-01-01)
Wind tunnel testing methods often infer aerodynamic performance via quasi-steady predictions, driving a wind tunnel model through predetermined trajectories, or quasi- steady integration of the applied aerodynamic forces and moments. This paper focuses on a new testing approach that allows the simulation and study of the true longitudinal dynamics of a wind tunnel model. The system design allows an experimentalist to carry heavy models with all of the needed sensors for evaluating true unsteady aerodynamic ...
Citation Formats
A. T. Kutay, J. A. Muse, D. P. Brzozowski, A. Glezer, and A. J. Calise, “A closed-loop flight control experiment using active flow control actuators,” Reno, NV; United States, 2007, vol. 2, p. 1289, Accessed: 00, 2021. [Online]. Available: https://arc.aiaa.org/doi/10.2514/6.2007-114.