Closed-Loop Flow Separation Control Using the Deep Q Network over Airfoil

AIAA Journal ◽  
2020 ◽  
Vol 58 (10) ◽  
pp. 4260-4270
Author(s):  
Satoshi Shimomura ◽  
Satoshi Sekimoto ◽  
Akira Oyama ◽  
Kozo Fujii ◽  
Hiroyuki Nishida
Keyword(s):  
Flow Separation ◽  
Closed Loop ◽  
Separation Control ◽  
Flow Separation Control

Experimental Study on Closed-loop Flow Separation Control Utilizing Deep Q-Network over Fixed Angle-of-Attack Airfoil

2018 ◽  
Vol 2018 (0) ◽  
pp. S0520306
Author(s):  
Satoshi SHIMOMURA ◽  
Satoshi SEKIMOTO ◽  
Hiroaki HUKUMOTO ◽  
Akira OYAMA ◽  
Kozo FUJII ◽  
...  
Keyword(s):  
Experimental Study ◽  
Flow Separation ◽  
Closed Loop ◽  
Angle Of Attack ◽  
Separation Control ◽  
Flow Separation Control ◽  
Fixed Angle

Flow-separation-control system operating in feedback closed loop

2019 ◽  
Vol 91 (3) ◽  
pp. 498-508
Author(s):  
Wienczyslaw Stalewski ◽  
Andrzej Krzysiak
Keyword(s):  
Flow Separation ◽  
Closed Loop ◽  
Pressure Sensors ◽  
The Self ◽  
Experimental Investigations ◽  
Separation Control ◽  
Trailing Edge ◽  
High Lift ◽  
Content Type ◽  
Flow Separation Control

Purpose The purpose of this study is to develop the concept of self-adapting system which would be able to control a flow on the wing-high-lift system and protect the flow against strong separation. Design/methodology/approach The self-adapting system has been developed based on computational approach. The computational studies have been conducted using the URANS solver. The experimental investigations have been conducted to verify the computational results. Findings The developed solution is controlled by closed-loop-control (CLC) system. As flow actuators, the main-wing trailing-edge nozzles are proposed. Based on signals received from the pressure sensors located at the flap trailing edge, the CLC algorithm changes the amount of air blown from the nozzles. The results of computational simulations confirmed good effectiveness and reliability of the developed system. These results have been partially confirmed by experimental investigations. Research limitations/implications The presented research on an improvement of the effectiveness of high-lift systems of modern aircraft was conducted on the relatively lower level of the technology readiness. However, despite this limitation, the results of presented studies can provide a basis for developing innovative self-adaptive aerodynamic systems that potentially may be implemented in future aircrafts. Practical implications The studies on autonomous flow-separation control systems, operating in a closed feedback loop, are a great hope for significant advances in modern aeronautical engineering, also in the UAV area. The results of the presented studies can provide a basis for developing innovative self-adaptive aerodynamic systems at a higher level of technological readiness. Originality/value The presented approach is especially original and valuable in relation to the innovative concept of high-lift system supported by air-jets blown form the main-wing-trailing-edge nozzles; the effective and reliable flow sensors are the pressure sensors located at the flap trailing edge, and the effective and robust algorithm controlling the self-adapting aerodynamic system – original especially in respect to a strategy of deactivation of flow actuators.

scholarly journals Active flow separation control at the outer wing

2019 ◽  
Vol 11 (4) ◽  
pp. 823-836 ◽  
Author(s):  
J. P. Rosenblum ◽  
P. Vrchota ◽  
A. Prachar ◽  
S. H. Peng ◽  
S. Wallin ◽  
...  
Keyword(s):  
Flow Separation ◽  
Separation Control ◽  
Flow Separation Control ◽  
Active Flow
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