Study of cascade PID controller parameter optimization based on IMEA for thermal system

Author(s):  
Liu QingSong ◽  
Qian SuXiang
2014 ◽  
Vol 1082 ◽  
pp. 525-528
Author(s):  
Yuan Qi Zhang ◽  
Wei Ping Zhao ◽  
Song Xiang

Proportion, integration and differential gain of nonlinear PID Controller is nonlinear function of controlling error. This paper performed the non-linear PID controller parameter optimization of vertical take-off and landing stage for tilt rotor aircraft using the genetic algorithm. Dual loop control is used. Inner loop is angular velocity loop. Outer loop is angular position loop. According to the features of stability control of vertical take-off and landing stage of tilt rotor aircraft, system ascend time, steady error, and weighted overshoot are chosen as objective function of optimization. Simulation results show that controller designed by the present method can meet the requirement of control.


2015 ◽  
Vol 738-739 ◽  
pp. 1077-1081
Author(s):  
Juan Wei

For the difficulties of PID controller parameter optimization, we have put forward a novel depiction method PPOGS (PID Parameters Optimization based on Glowworm Swarm). By combining the minimum error absolute time integral definition proportion, the objective optimal functions of integral and differential functions, this method can produce the optimal allocation with the help of the glowworm swarm algorithm which seeks solution to the objective function. At last, we use MATLAB to make a simulation experiment, conducting an in-depth investigation of the key factors influencing the method. The results have showed PPOGS has better adaptability compared with other methods Key words: PID controller; parameter optimization; glowworm swarm; simulation


2014 ◽  
Vol 709 ◽  
pp. 252-255 ◽  
Author(s):  
Xin Zhao ◽  
Wei Ping Zhao ◽  
Song Xiang

This paper performed the longitudinal nonlinear PID Controller parameter optimization of general aircraft autopilot based on the longitudinal channel model and genetic algorithm. Proportion, integration and differential gain of nonlinear PID Controller is nonlinear function of controlling error. The objection function involves time integration of error’s absolute value, output of controller and system overshoot. The longitudinal controlling rate optimization of general aircraft autopilot is realized by minimizing the objection function value. Simulation results show that controller designed by the present method is better than traditional PID controller.


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