Study on Virtual Flight with PID Closed-Loop Control of Rudder Surface
Based on computational fluid dynamics,the dynamic nested mesh technique was used to solve the un-steady flow equations and dynamics equations and the PID(proportional integral-differential)closed-loop control al-gorithm.The characteristics of the flow field and the time variation of the tilting Angle and the tilting Angle of a two-dimensional wing with ailerons under the control of the rudder surface with predetermined target elevation were stud-ied.The results show that the response of feedback control is rapid,the wing can quickly deflect to the target elevation Angle,and the error between the pitch and the target elevation Angle is small after the pitch oscillation is relatively stable.The effectiveness of closed-loop control applied to virtual flight technology is verified.This method has a high reference value for studying the flow mechanism and dynamic characteristics of general-purpose aircraft in controlled flight.
万方数据
维普
