Improvement of Aircraft Aerodynamic Performance Using Piezoelectric Actuators
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Improvement of Aircraft Aerodynamic Performance Using Piezoelectric Actuators LI Min 1
CHEN Wei-min 2
Li Wei1
1. School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China 2. Div. of Engineering Science Research, Institute of Mechanics, CAS, Beijing 100080, China Abstract: To flight vehicle designer, the ability to adapt air vehicle aerodynamic shape so as to increase the optimum flight envelope is highly desirable. In this work, by distributing piezoelectric actuators on the top and bottom surfaces of a rectangular wing, the improvement of aerodynamic performance of flight vehicle is studied. The approach of the Fictitious Control Surface (FCS) is evaluated at a group of dynamic pressure and wing stiffness, through examining four aspects including the improvement of rolling power, the increase of lift, the decrease of the induced drag and the decrease of the bending moment at root of wing. Then an experimental model of high-speed wind tunnel is designed in order to validate the results of theoretical analysis. The ground tests and wind tunnel tests demonstrate that the lift and rolling moment can be increased by using the favorable aeroelastic effect. And quantificationally the experimental results agree well with the analytical results. Key words : piezoelectric actuator, aerodynamic performance，fictitious control surface (FCS) CLC number: Document code:
Air vehicles are optimized for specific flight conditions. When the vehicle operates away from this design point, the performance will decline. The ability to adapt air vehicle aerodynamic shape to increase the optimum flight envelope is therefore highly desirable. This is an elusive goal that aircraft designers continually strive to achieve and keep technologists motivated to invent new and innovative adaptive structure concept. Aircraft have always been adaptive in one form or another one, and aerospace history is rich with innovative solutions to this design issue. For example, the Wright brothers used wing warping, an adaptable lifting surface, to control the Wright B flyer. As aircraft speed increased, wings became stiffer to preclude aeroelastic instabilities such as divergence and flutter. Wing warping disappeared because the power required exceeded the capability of actuators. And instead of warping wing, the more energy efficient aileron system emerged, which is just another form of shape adaptation. Other forms of shape control for aerodynamic performance are retractable landing gear, flaps, and trim tabs. These have all been successfully fielded and are predominant in modern day vehicle design from general aviation aircraft to high-performance military aircraft. More advanced forms of shape control include wing sweep, camber change, and wing twist[1]. Another highly sought after shape control concept is variable camber. In addition to ailerons to control roll performance, this is currently accomplished using articulated, trailing-edge flaps to increase the lift coefficient
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