Abstract
Abstract : This paper examines the use of piezoelectric actuators to control supersonic flutter of wing boxes. Aluminum built-up wing boxes are used as examples to analyze the free vibration, aeroelastic, and control concepts associated with flutter control. Finite elements are used to calculate deflections due to input forces, the member stresses and strains, natural frequencies, and mode shapes. Linear strip theory with steady aerodynamics are applied to find the frequency coalescence of modes indicating flutter. The variables of interest are the skin, web, and rib thicknesses associated with torsional rigidity, and the spar cap and vertical post areas associated with bending rigidity. Piezoelectric actuators are implemented in a configuration which generates torsional control of the wing box. Pole assignment concepts are applied to change the free vibration frequencies. A parametric study changing the free vibration frequencies using piezoelectric actuators is conducted to determine which thicknesses of skins, webs, and ribs will meet a specified flutter requirement. The addition of piezoelectric actuators will allow the flutter requirements to be met at smaller thicknesses of skins, webs, and ribs so that the overall weight of the wing box, including actuators, is decreased.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
