SMA actuator design and analysis for forebody active disturbance flow control on slender body

Active disturbance flow control system depended on the ability of small square-edged rectangular flow effector (FE) generates aerodynamic forces by triggering or stabilizing the FE structures. Computational analysis is performed for supersonic flow runs through a generic slender body equipped with micro-structure on its nose cone. Computational Fluid Dynamics (CFD) studies show that a proportional side force magnitude can be obtained by indexing static micro-flow effectors with various parameters of the flow effector structure. To develop a dynamic micro square-edged rectangular flow effector assembly that would fit in the available missile model nose volume, shape memory alloy (SMA) wire is selected as an actuation material due to its force and displacement characteristics. Based on the SMA constitutive equations, the boundary conditions are partial constraints, considering the constant loading, the SMA inner stress is calculated in the process of the phase transition between austenite phase and martensite phase. A worm-gear pair and slider-crank mechanism is designed to act as a transmission between the SMA actuator and the end of the flow effector. The actuator structural parameters and the SMA wire control system component of the FE actuator were design for active disturbance flow control on slender body.