Design of Shape-Adaptive Deployable Slat-Cove Filler for Airframe Noise Reduction

Mechanical instabilities and elastic nonlinearities are emerging means for designing deployable shape adaptive structures. Dynamic snap-through buckling is investigated here as a to tailor the deployment retraction of slat-cove filler (SCF), morphing component used reduce airframe noise. Upon deployment, leading-edge slats create cove between themselves main wing, producing unsteady flow features that significant source A SCF designed autonomously snap out slat deploys, providing smoother aerodynamic profile reduces unsteadiness. The nonlinear structural behavior studied, then tailored, achieve desirable snapping response. Three configurations considered: 1) constant thickness (monolithic) superelastic shape-memory alloy (SMA) SCF, 2) variable-thickness SMA 3) set stiffness-tailored fiberglass composite SCFs. Results indicate that, although monolithic SCFs provide simple solution, variations in both designs allow decrease energy required self-deployment reduction severity impact during stowage. enhanced from stiffness tailoring peak material strains comparison previous leveraged superelasticity adaptation. readily achieved through use layered composites, facilitating considerable weight savings compared dense designs. aeroelastic response different calculated using fluid/structure interaction analyses, it shown can deploy retract full conditions.