The distillation process is vital in many fields of chemical industries, such as the two-coupled distillation columns that are usually highly nonlinear Multi-Input Multi-Output (MIMO) coupled processes. The control of MIMO process is usually implemented via a decentralized approach using a set of Single-Input Single-Output (SISO) loop controllers. Decoupling the MIMO process into group of single loops requires proper input-output pairing and development of decoupling compensator unit. This paper proposes a novel intelligent decoupling approach for MIMO processes based on new MIMO brain emotional learning architecture. A MIMO architecture of Brain Emotional Learning Based Intelligent Controller (BELBIC) is developed and applied as a decoupler for 4 input/4 output highly nonlinear coupled distillation columns process. Moreover, the performance of the proposed Brain Emotional Learning Based Intelligent Decoupler (BELBID) is enhanced using Particle Swarm Optimization (PSO) technique. The performance is compared with the PSO optimized steady state decoupling compensation matrix. Mathematical models of the distillation columns and the decouplers are built and tested in simulation environment by applying the same inputs. The results prove remarkable success of the BELBID in minimizing the loops interactions without degrading the output that every input has been paired with.

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The performance of antitank guided missile systems is measured through the minimum missdistance and the capability of the missile to overcome target maneuver and different sources of errors and disturbance noises. The variety of new missiles with higher performance requirements impulse new problems in structure, effectiveness of control, cost, reliability...etc. One of the most interesting and challenging problem areas for antitank missile is that of the guidance and control. Therefore this paper consider an antitank guided missile system which belongs to the second generation for the design and analysis. Transfer functions representing the missile dynamics in pitch and yaw planes are derived to be considered for investigation. This investigation includes autopilot design and evaluating the system response such that the performance requirements are achieved. The control loop for both pitch and yaw channels of the intended guided missile system with compensation network are designed and investigated for each channel such that the system is stabilized and the performance requirements are satisfied. In addition, an inner loop design is carried out using free gyroscope for the yaw channel to improve its performance against target maneuver. To stay on the robustness of these compensators and their ability to withstand against disturbances, the measurements are corrupted with noise and the system performance is investigated. This investigation leads to the necessary modification or retuning the designed compensators for achieving the required robustness margin.

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