Aeroelastic Analysis And Control Of A Flexible Chordwise Wing

Adaptive wing is a kind of flexible structure based on active control technology to get the bestflight performance in different flight conditions. It is obtained in part by a reduction of stiffness in thewing primary structures. This may also has an undesirable impact on the aeroelastic stabilitycharacteristics. Now researchers are focuse on the implementation of adaptive wing structures. Butlittle has been done in the aeroelastic of the adaptive wing. This paper deals with the aeroelasticity andcontrol of an adaptive wing with a flexible chordwise. The main progresses of the thesis are asfollows.Based on Murua’s model of three degrees of freedom which considering the flexible chordewise,the suboptimal control is used to increase the flutter speed of the system. V-g method has beenimplemented in order to compute flutter speed. The influence of the variation camber on the stabilityboundaries is investigated. The deflection of the bending deformation is selected as the controlvariable. It is shown that the camber deformation has significant effects on the aeroelasticity of thesystem, and the flutter critical speed improved26%.A piezoelectric beam finite element model is developed for a flexible chordwise wing section. Theunsteady vortex lattice method is used to calculate the aerodynamics. PID controller is used toincrease the flutter speed with the displacement as the feedback signal. It is shown11%flutter criticalspeed increased in the given range of control voltage.Finally, the neural network predictive controller is implemented to suppress flutter of the system.The state output feedback and the displacement output feedback methods are respectively applied tothe control system. The limit cycle of the vibration system tends to convergence within the limitedvoltage.