Problem 2) open-loop transfei runction is given by · Consider the characteristic equation of a unity feedback control system whose K(s + 2) G(s) = s(s – 1) a. Determine the range of values for the gain K using Routh-Hurwitz method. b. Sketch the root-locus by applying all appropriate steps of root-locus.
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- Figure Q2 shows the block diagram of a flight control system.a) Derive the system transfer function.b) Find out the system gain, natural frequency and damping ratio for this systembased on the standard form of second order systems.c) If K1 = 2 and K2 = 10, use the standard response sheet to find out the systemsteady-state value, overshoot and 63% rise time, with a unit step input.are given a system’s transfer function as T(s) = 21 Construct a state-space model for the given system using ” Observer Canonical Form” method. | that the full state information of this system is available, design a state-feedback controller for this put the desired closed loop poles at ~2+ 2. Now, assume that the state information of the system are measurable, for this case what kind of controller do you suggest? Design this controller so that the ¢ Joop poles of the system are located at —10 + 510.BelowIn the unit feedback system given the shape, G(s),is given as. When a unit ramp is applied to the input of the system, 2% of the steady-state error and unit to the inputWhen the step is applied, it is desired that the percentage exceedance rate is 9.25% and the settling time is 0.58 s.1-In this case, which of the following is the approximate value of the constant a?
- The open loop transfer function of unity feedback system is ??(??) = ??????????(??+??)(??+????).1- Assess the stability of the system.2- If the gain ?? is connected in series with G(s) as shown in figure Q1, Determine the range of ?? for stable system.Below is given the forward transfer function of a unity-feedback system.a) Determine the position, velocity, and acceleration error constants Kp, Kv, and Ka and the steady-state error for step, ramp, and parabolic inputs;b) If possible, use a proportional controller to give a steady-state error for ramp input of e_ss(ramp) ≤ 0.01; c) Determine the controller necessary to give zero steady-state error for a ramp input;d) Determine the controller necessary to give zero steady-state error for aparabolic input.Consider a unity negative feedback system with loop transfer function shown in Figure where L(s)=GcG(s)=K(s2+6s+1)(s2+5s+1)L(s)=GcG(s)=K(s2+6s+1)(s2+5s+1) Determine the value of K for which the closed-loop system is stable.
- The forward transfer function G(s) with a H(s) feedback configuration of an uncompensated Basic Satellite Launching System is as shown in figures 1 and 2. A- Write a m-script and generate the time and frequency response of the system shown in Figure 1. (a = 4, b = 2, c=2, d = 1and e=10, and f=4). B- Compute the percent overshoot, peak time and settling time, using second order approximation through pole zero cancellation and unity feedback configuration shown in figure 2.Consider the feedback system given the open loop transfer function below G(s)H(s) = K / ( S (s+3) (s+2)) a) Using the Routh-Hurwitz criterion, for which value of K, the poles of the closed-loop system take the pure imaginary value.b) What will be the maximum value of K for the system to be stable?c) Calculate the value of K, where the real value of the complex root of the system is Re{s}=-1. Tip 1: Closed loop transfer function T(s) = G(s) / ( 1+ G(s)H(s)) .Routh HurwitzIn order to perform the criterion analysis, the denominator of the closed-loop function will be examined. Tip 2: The real value of the system complex root Re{s}=-1 is expressed by the following formula f^2(s) = p(s-1) p(s) is the payoff of the closed-loop function.The forward transfer function G(s) with a H(s) feedback configuration of an uncompensated Basic Satellite Launching System is as shown in figures 1 and 2. A- in the picture B- Compute the percent overshoot, peak time and settling time, using second order approximation through pole zero cancellation and unity feedback configuration shown in figure 2. C- Summarise the results (a) and (b) in tabular form and comment on the stability of both systems based on time response graph for (a) and computed values in (b).
- Consider PD-Control with set-point weighting by setting ki = 0 in Equation 6.4.1. Determine the closed-loop transfer function from the position reference, r, to the angular position output, θ in radians, i.e., Y(s)/R(s), in terms of K, τ, bsp, kp and kd/ then, Determine kp and kd in terms of the closed-loop natural frequency, ωn, damping ratio, ζ, motor time constant, τ, and motor gain constant, K.BelowIn the unit feedback system given the shape, G(s),is given as. When a unit ramp is applied to the input of the system, 2% of the steady-state error and unit to the inputWhen the step is applied, it is desired that the percentage exceedance rate is 9.25% and the settling time is 0.58 s.1-In this case, which of the following is the approximate value of the constant a? 2-In this case, which of the following is the approximate value of the constant b? 3-Looking at the unit step response of the systemWhat is .peak time?This mode of control is not recommended for disturbances that are erratic and noisy in nature. a. integral b. on/off c. proportional d. derivative What is calculated as the error in a negative feedback loop? difference between measured variable and load difference between load and set point difference between load and process output 4. difference beween measured variable and set point A proportional controller whose gain has a very large value approaches which mode of control? on/off proportional-derivative proportional-integral proportional-integral-derivative