Attitude Control Law Designed For The Small Fixed-wing Unmanned Aerial Vehicle

In recent years,Since UAV(Unmanned Aerial Vehicle)has a great benefits of low-cost and high reliability,the application of UAVs in military and civilian has been expanding greatly.A flight system is to ensure that the UAVs can adjust its own posture and motion parameters during the flight,which is crucial to accomplish the task safe and reliable.So the flight control algorithms has a great importance in current life.At present,the flight control system mainly uses classic control theory as theoretical basis of the algorithm,but actually the classic control theory can’t meets the need of multitasking.Indeed,intelligent and diversification is the inevitable developing trend of UAVs.So this paper uses the intelligent PID to design the pitch angle controller and roll angle controller,and the results are quite good.Aimed at designing the pitch and roll controller,this paper Firstly introduces coordinate system and the flying attitude Angle used in UAV,and by using the referred hypothesis,it builds the mathematic mode of UAV and gets the dynamics and kinematics equation.Second,this paper mainly introduces the traditional PID control,which leads to the intelligent PID and do the programmed simulation according to the designed rules.And the results between the intelligent PID and traditional PID also verify effectiveness of intelligent PID.The third part studies the flight longitudinal and lateral control law,and using intelligent PID to design the pitch Angle controller in longitudinal channel and the roll Angle controller in the horizontal channel.Then compare the actual data with the instruction data recorded during the flight,to prove the design of pitch Angle and roll Angle controller is effective,and can accomplish the flight stably.