Towards Robust Nonlinear Closed-Loop Transition Control Using Local Dynamic Surface Modification

2022 ◽  
Author(s):  
Miriam Deschine ◽  
Luke Szathmary ◽  
Vladimir V. Golubev ◽  
William MacKunis ◽  
Reda R. Mankbadi ◽  
...  
2020 ◽  
Vol 142 (9) ◽  
Author(s):  
Donald P. Rizzetta ◽  
Miguel R. Visbal ◽  
Sandipan Mishra ◽  
Michael Amitay

Abstract Direct numerical simulations (DNSs) were carried out in order reproduce the generation and control of transition on a flat plate by means of local dynamic surface modification. The configurations and flow conditions duplicate those of previous numerical investigations, and are similar to an experimental arrangement, which employed piezoelectrically driven actuators to impart small amplitude local deformation of the plate surface. In those studies, one actuator was located in the upstream plate region, and oscillated at the most unstable frequency of 250 Hz in order to generate small disturbances, which amplified Tollmien–Schlichting instabilities. A second actuator placed downstream, was then oscillated at the same frequency, but with appropriate amplitudes in order to mitigate disturbance growth and delay the evolution of transition. Prior simulations employed an empirical process to determine optimal values of the control parameters. In the current effort, this process is replaced with a closed-loop control law. Numerical solutions are obtained to the two-dimensional and three-dimensional compressible Navier–Stokes equations, utilizing a high-fidelity numerical scheme and an implicit time-marching approach. Local surface modification of the plate is enforced via grid deformation. Results of the simulations are presented, and features of the flowfields are described. Comparisons are made between results obtained with the two control methods, and effectiveness of the closed-loop approach is evaluated.


2020 ◽  
Author(s):  
Donald P. Rizzetta ◽  
Miguel Visbal ◽  
Michael Amitay ◽  
Sandipan Mishra

AIAA Journal ◽  
2021 ◽  
pp. 1-11
Author(s):  
John D. B. Wylie ◽  
Sandipan Mishra ◽  
Michael Amitay

2019 ◽  
Vol 141 (12) ◽  
Author(s):  
Donald P. Rizzetta ◽  
Miguel R. Visbal

Numerical calculations were carried out to investigate control of transition on a flat plate by means of local dynamic surface deformation. The configuration and flow conditions are similar to a previous computation which simulated transition mitigation. Physically, the surface modification may be produced by piezoelectrically driven actuators located below a compliant aerodynamic surface, which have been employed experimentally. One actuator is located in the upstream plate region and oscillated at the most unstable frequency of 250 Hz to develop disturbances representing Tollmien–Schlichting instabilities. A controlling actuator is placed downstream and oscillated at the same frequency, but with an appropriate phase shift and modified amplitude to decrease disturbance growth and delay transition. While the downstream controlling actuator is two-dimensional (spanwise invariant), several forms of upstream disturbances were considered. These included disturbances which were strictly two-dimensional, those which were modulated in amplitude and those which had a spanwise variation of the temporal phase shift. Direct numerical simulations were obtained by solution of the three-dimensional compressible Navier–Stokes equations, utilizing a high-fidelity computational scheme and an implicit time-marching approach. A previously devised empirical process was applied for determining the optimal parameters of the controlling actuator. Results of the simulations are described, features of the flowfields elucidated, and comparisons made between solutions of the uncontrolled and controlled cases for the respective incoming disturbances. It is found that the disturbance growth is mitigated and the transition is delayed for all forms of the upstream perturbations, substantially reducing the skin friction.


2003 ◽  
Vol 125 (3) ◽  
pp. 320-329 ◽  
Author(s):  
Bongsob Song ◽  
J. Karl Hedrick ◽  
Adam Howell

In this paper, a new method of analyzing for the performance loss caused by faults in the systems is presented, and applied to the design of a fault tolerant longitudinal controller for a transit bus. Based on the amount of performance loss measured by a quadratic function, fault impact assessment is developed for both single and multiple faults. More specifically, ellipsoidal approximation of the tracking error bounds via dynamic surface control (DSC) is obtained via convex optimization technique for the nonlinear closed-loop system. Relying on the fault impact to the closed loop system and its isolatability on a fault detection and diagnosis system, the fault classification is proposed to provide a switching logic in the framework of a switched hierarchical structure. Finally, simulation results of the fault tolerant controller and corresponding fault classification are shown for multiple multiplicative faults.


Author(s):  
Cong Zhang ◽  
Yun-Jie Wu

This paper proposes a novel integrated guidance and control (IGC) method combining dynamic surface control (DSC) and active disturbance rejection control (ADRC) for the guidance and control system of hypersonic reentry missile (HRM) with bounded uncertainties. First, the model of HRM is established. Second, the proposed IGC method based on DSC and ADRC is designed. The stability of closed-loop system is proved strictly. It is worth mentioning that the ADRC technique is used to estimate and compensate the disturbance in the proposed IGC system. This makes the closed-loop system a better performance and reduces the chattering caused by lumped disturbances. Finally, a series of simulations and comparisons with a 6-DOF non-linear missile that includes all aerodynamic effects are demonstrated to illustrate the effectiveness and advantage of the proposed IGC method.


2011 ◽  
Vol 110-116 ◽  
pp. 3580-3586 ◽  
Author(s):  
Waseem Aslam Butt ◽  
Lin Yan ◽  
Amezquita S. Kendrick

The design of a nonlinear adaptive dynamic surface controller for the longitudinal model of a hypothetical supersonic flight vehicle is considered in this work. The uncertain nonlinear functions in the strict feedback flight vehicle model are approximated by using radial basis function neural networks. A detailed stability analysis of the designed angle-of-attack controller shows that all the signals of the closed loop system are uniformly ultimately bounded. The performance of the designed controller is verified through numerical simulations of the flight vehicle model.


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