Oriented Micro-actuator Arrays And Simulation Analysis, Active Flow Control

In recent years, as the great progresses of researches on the material science, electronics and miniature device and the advance of studies in the physical turbulent phenomena and principle of three dimensional unsteady flow, MEMS-based advanced active flow control (AFC) technology was brought forward, which integrated aerodynamics, material and control disciplines. AFC technology has great potential in the domain of reducing drag, increasing lift, enhancing maneuverability, decreasing noise radiation, control separated flow and maneuvering aircraft. Consequently it has become key field of flow control. At the present time, there is few research findings. However, MEMS technology has opened a new territory for active flow control. Development of MEMS-based actuators is a kernel of this paper.In this paper, a MEMS-based micro balloon actuator array for realizing rolling moment of delta wing had been researched. The principle of the macro aerodynamic maneuver is discussed. Based on finite element method, a model of microactuator array and delta wing was accomplished, and Computational Fluid Dynamics (CFD) flow simulation was performed. As a result, the geometrical parameter of the microactuators and the optimization of the actuator arrays structure configuration were realized. According to the wind tunnel experiments, the validity of the design and simulation technique was proved.Firstly, according to the theory of wall boundary layer control and aerodynamics character of delta wing at medium attack angle, the generation principle of rolling, which was produced by coupling between the microactuators array and boundary layer near the leading edge of the delta wing, was discussed. Then the physical dimensions and arrangement of the microactuator arrays were designed preliminarily, and the initial model was built.Secondly, according to the shaped size information of microactuators at theworking state, a delta wing flow model was built by GAMBIT. On the basis of the k-epsilon turbulent model, the flow field of the delta wing coupled with microactuators in different arrangement was calculated by FLUENT. The rolling moment of the delta wing was obtained at some flow states. Based on the CFD results, the optimum arrangement of the microactuator arrays was gained.Finally, the experiment of the delta wing model with microactuator arrays mounted on the leading edge was carried on in a wind tunnel of low turbulivity to prove the control ability of micro actuator arrays and the feasibility of the arrangement scheme.