| Some aircrafts are the side of the fuselage inlet form.When the plane flying in maneuver,the vortices formed by the front fuselage are different from that in static flight.This situation is likely to lead to a large difference between the internal flow field and the external flow field of the inlet during post stall maneuver.So the airflow separation at the inlet lip and the sidewall of the inlet leads to the distortion of the inlet flow field,and the aerodynamic force exhibits a strong hysteresis.Therefore,it is necessary to carry out the relevant research by means of tests.Under this backdrop,the control system of the inlet installation development for fighter maneuver in ?3.2m low speed wind tunnel has been designed.The system consists of upper monitor,motion controller,torque motor,etc.The upper monitor carries out trajectory planning according to the motion control program and generates the target position signal by timing interpolation.Then,the feedback signals from motion controllers and the displacement and speed measuring sensors,are fed into the deviation counter for comparison.After the PID parameters are positive definite,they are converted into the speed signals recognized by the motor driver by the digital to analog.Last,the motor driver drives the torque motor by a control signal obtained from the motion controller.Finally,the mechanical structure of the test device connected with the torque motor can realize the movements of pitch,yaw,oscillation and rapid pulling of the model,thereby simulating the flight state of the aircraft.After the development of the control system,the equipment debugging and checking test have been carried out.The result shows: the system scheme is reasonable and the equipment is reliable;the motor direct drive device is adopted to ensure the control accuracy of the attitude angle of the model while simulating the flight state of the aircraft effectively. |
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