Design and experiment of attitude stability control for bionic flapping wing aircraft
A fast response automatic attitude stabilization control method is proposed to address the current situation where attitude control for flapping wing aircraft is mostly manual during flight.Establish a mathematical model of flapping wing aircraft using Newton's law and moment of momentum theorem,and study the attitude adjustment control strategy during flight based on the working principle of flapping wing aircraft attitude change.The cascade PID control algorithm is used to design the inner and outer loop controllers for attitude adjustment.With the Euler angles of the flapping wing aircraft as the output,the attitude adjustment process of the flapping wing aircraft is simulated and tested in the outfield.The accuracy of the flapping wing aircraft mathematical model and the effectiveness of the attitude controller were verified through simulation analysis of the attitude angle response of the flapping wing aircraft and analysis of field flight experimental data.The results show that under step signal input,the attitude angle can quickly respond and approach steady state.In outfield flight,the flapping wing aircraft maintains a pitch angle of 15 degrees and a flight acceleration of 1 m/s2,which can effectively maintain attitude stability automatically.
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