1491 Words6 Pages

Design of Missile with Two-Loop and Autopilot Yaw Using Root Locus
Abstract:This paper aims at designing Automatic Landing Systems for MISSILE based on Root Locus modern control system. The control method is used to determine gains of the controllers in order to apply the Root Locus method. The block diagram of the proposed control system with required controller gains is established. The transfer functions for open loop and then the closed loop are obtained based on automatic control principles. The Root Locus for open loop is drawn and then gain (K) values are found for given damping ratios. Finally, the step responses of the closed-loop system with automatic landing system controller auto-pilot were drawn. The digital simulation results*…show more content…*

More specifically, use the tail deflection to track an acceleration maneuver with a time constant of less than 0.35s, a steady state error of less than 5%, and a maximum overshot of 20% for the step response. Controller synthesis can be done using different frequency or time-domain methods. The root locus technique is applied in this paper, the discussion of which is presented below. This technique provides graphical information in the complex plane on the trajectory of the roots of the characteristic equation for variations in one or more system parameters. Since the roots placement in the complex plane governs the type of the response that can be expected to occur, the ability to view the movement of the roots in the complex plane, as one or more system parameters are varied, turns out to be very useful. The root locus and the closed-loop step response plot of the transfer function 1defined in*…show more content…*

Lead Compensation The purpose of compensator design generally is to satisfy both transient and steady-state specifications. In the root locus design approach presented here, these two tasks are approached separately. First, the transient performance specifications are satisfied, using one or more stages of lead (usually) or lag compensation [7] The transfer function of a typical lead compensator is the following, where the zero is smaller than the pole, that is, it is closer to the imaginary axis in the complex plane. C(S)=K (S-Z)/(S-P) (3) Then by clicking the Show Analysis Plot button a window entitled LTI Viewer for SISO Design Task displaying the system's closed-loop step response will open. You can also identify some characteristics of the step response. Specifically, right-click on the figure and under Characteristics choose Settling Time. Then repeat for Rise Time[3]. Simulation Results The simulations are carried out in MATLAB environment and the results obtained areshown in Fig.5, Fig.6

More specifically, use the tail deflection to track an acceleration maneuver with a time constant of less than 0.35s, a steady state error of less than 5%, and a maximum overshot of 20% for the step response. Controller synthesis can be done using different frequency or time-domain methods. The root locus technique is applied in this paper, the discussion of which is presented below. This technique provides graphical information in the complex plane on the trajectory of the roots of the characteristic equation for variations in one or more system parameters. Since the roots placement in the complex plane governs the type of the response that can be expected to occur, the ability to view the movement of the roots in the complex plane, as one or more system parameters are varied, turns out to be very useful. The root locus and the closed-loop step response plot of the transfer function 1defined in

Lead Compensation The purpose of compensator design generally is to satisfy both transient and steady-state specifications. In the root locus design approach presented here, these two tasks are approached separately. First, the transient performance specifications are satisfied, using one or more stages of lead (usually) or lag compensation [7] The transfer function of a typical lead compensator is the following, where the zero is smaller than the pole, that is, it is closer to the imaginary axis in the complex plane. C(S)=K (S-Z)/(S-P) (3) Then by clicking the Show Analysis Plot button a window entitled LTI Viewer for SISO Design Task displaying the system's closed-loop step response will open. You can also identify some characteristics of the step response. Specifically, right-click on the figure and under Characteristics choose Settling Time. Then repeat for Rise Time[3]. Simulation Results The simulations are carried out in MATLAB environment and the results obtained areshown in Fig.5, Fig.6

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