Loading...

Design and Development of a Load Alleviation Control System for an Aeroelastic Wing Using Smart Materials

Mohammadizadeh Zanianpour, Khalil | 2020

755 Viewed
  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 53440 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Pourtakdoust, Hossein
  7. Abstract:
  8. As the aeronautical design evolves, the optimal solutions tend to employ slenderer and aeroelastic wings. These slender wings could help to increase the flight endurance, by decreasing the fuel consumption. However, as a wing becomes slenderer its structural stiffness decreases. The decrease in the stiffness highlights the structural vibrations and aeroelastic behavior in these wings. Atmospheric turbulences induce vibrations that can cause fatigue and structural failures. A possible solution to decrease these oscillations is to use active vibration control and flutter suppression. Conventional control surfaces on a wing can be used to implement the active vibration control. However, given the recent advancements in material science, smart materials can provide a novel solution. Smart material used as actuators can be integrated into the structure and provide a nonintrusive actuation. Thus, using the mart materials for the active vibration control attracted many researchers in recent decades. In this Thesis, first, we start by modeling the wing as clamped-free beam and deriving the linear governing equation. Then, considering references with experimental results, we choose the mechanical and the geometrical properties of the wing that is considered in this study. We later use these properties to simulate an aeroelastic wing. Then, the natural frequencies and the flutter speed are calculated numerically via finite-element analysis. The fourth chapter is dedicated to the load alleviation system implementation. The preparation of the required software and hardware in the loop testbed is presented. Then we move forward and represent design of a Linear Quadratic Gaussian controller. In the LQG controller design three weighting matrices are considered. We then simulate and analyze the performance of each controller. Next, we compare the performance of the controllers with the results obtained from the hardware in the loop testbed. At the end, the results of wind tunnel tests are presented. As anticipated, the performance of the designed controller is proven to be satisfactory. It can be seen that controller suppresses the wing vibration effectively and the amplitude of oscillation is decreased
  9. Keywords:
  10. Smart Materials ; Linear Quadratic Gaussian (LQG)Controller ; Active Vibration Suppression ; Wind Tunnel Test ; Flutter Suppression ; Aeroelastic Behavior ; Aircraft Wing

 Digital Object List

 Bookmark

No TOC