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Preliminary Investigation of Active Control of a Flared Folding Wingtip using Model Predictive Control

Narimani, Mohammad Hossein | 2024

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 57075 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Pourtakdoust, Hossein
  7. Abstract:
  8. One of the ways to optimize fuel consumption and improve aircraft performance can be realized by reducing drag, and a major part of this force is the lift-induced drag, which is reduced by increasing the wing span. On the other hand, increasing the wingspan has physical limitations on the allowed dimensions of the aircraft, increasing the weight and reducing the maneuverability of the aircraft, especially in the roll maneuver. Therefore, in order to benefit from the advantages of increasing the wing span and not facing the mentioned limitations, the idea of using a Folding Wing-Tip (FWT) has been proposed by aircraft manufacturing companies and experts. In this way, in normal flight such as cruise, by locking the wing tip hinge, the aircraft uses the maximum length of its wing, which improves the aerodynamic efficiency, and by folding it on the ground, the dimensional limit for the runway or hangar is removed. In this research, the effect of active wing angle control as a control input in reducing wing load and vibrations was investigated. In this regard, first, the aeroelastic model of an elastic wing with a rigid hinged wing tip utilized with a trailing edge tab has been modeled and verified. Then, through the design of an active control system to adjust the tab angle of the wing tip, the idea of active vibration control and load alleviation has been investigated. In particular, the controller is designed to decrease maximum Wing-Root Bending Boment (WRBM) of the elastic wing, as well as eliminating the Limit Cycle Oscillations (LCO) of the wing-tip and increasing the stability margin of the system, which has not been done in the literature. Among the innovations of the research, the development of an existing aerodynamic model through consideration of unsteady effects with Theodorsen's theory can be mentioned. Moreover, the idea of active control of the wing tip has not been investigated in previous studies, which have been limited to investigating the passive effect of hinged wing tips and analyzing their stability
  9. Keywords:
  10. Aeroservoelasticity ; Limit Cycle Oscillation ; Folding Wing-Tip ; Gust Load Alleviation ; Active Vibration Suppression

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