The Airborne CCD image racemic control technology research
|School||Graduate Schoo,Chinese Academy of Sciences|
|Course||Mechanical Manufacturing and Automation|
|Keywords||Image rotation compensation The racemic Control system Improved Internal Model Control|
Airborne photoelectric platform stability and tracking technology has become more and more mature , stable tracking performance of the onboard television equipment to continuously improve . Additional rotation is superimposed due to the movement of the optical platform framework in the trace , so that the stable image to the pilot observation inconvenience , so the CCD image rotation compensation control technique (in this control technology referred to as a CCD image rac ) Be a necessary research content . This paper describes the airborne camera system image rotation mechanism , and to understand calculation of racemic angle ; illustrates the need for image compensation ; analysis three different racemic program are to select for airborne CCD image racemic physical methods. Based on system performance , system friction torque and wire beam interference torque measurement and analysis to determine the effects of to overcome frictional torque and wiring harness torque interference is the racemic improvement in the the racemic performance to solve the primary problem . And solve this problem to the classical theory of frequency domain based guarantee the system stability and speed of response can be achieved under the premise in the speed loop with second-order correction , the speed loop open-loop gain to reach a higher level ; in the position of the ring using the a nonlinear piecewise fuzzy control and classical lag - advance control combined the multimode control method , while taking advantage of the input information , speed feedforward control method , the system reaches a certain racemic accuracy . Classical control theory design racemic unstable control system performance , racemic accuracy is not high enough to analyze cause problems due to the friction torque system , especially larger wire beam interference torque , classical control methods to exist in the system friction torque and the disturbance torque of the wire bundles to be fully suppressed while for the system operation due to friction, etc. caused by uncertain factors such as the temperature change of the fuselage to bring the model uncertainty is not sufficient robustness . To resolve this problem , improved internal model control method , and the simulation study , the simulation results show that the improved internal model control method is simple and effective solution to the above problem is very suitable for engineering applications .