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Modern Control Systems

Dorf

Chapter 7

The Root Locus Method - all with Video Answers

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Chapter Questions

Problem 1

Sketch the root locus for the following loop transfer functions of the system shown in Figure P7.1 when $0<K<\infty$ :
(a) $G_c(s) G(s)=\frac{K}{s(s+10)(s+8)}$
(b) $G_c(s) G(s)=\frac{K}{\left(s^2+2 s+2\right)(s+1)}$
(c) $G_c(s) G(s)=\frac{K(s+5)}{s(s+2)(s+7)}$
(d) $G_c(s) G(s)=\frac{K\left(s^2+4 s+8\right)}{s^2(s+7)}$

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Problem 2

The linear model of a phase detector was presented in Problem 6.7. Sketch the root locus as a function of the gain $K_v=K_a K$. Determine the value of $K_v$ attained if the complex roots have a damping ratio equal to 0.60 [13].

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Problem 3

P7.3 Consider a unity feedback system with open-loop transfer function $\frac{K}{(s+a)(s+b)}$.
When the closed-loop system is subjected to a step input, the output has an overshoot of $16.3 \%$ but ultimately attains the final value of 1 . The response to a ramp input has a steady-state error of 0.0625 .
(a) Find the value of $K, a$ and $b$.
(b) Mark the closed-loop poles.
(c) If the gain is doubled, find the closed-loop poles and mark it on the s-plane.
(d) Find percentage overshoot corresponding to the gain obtained in (c).

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03:41

Problem 4

The analysis of a large antenna was presented in Problem 4.5. Sketch the root locus of the system as $0<k_a<\infty$. Determine the maximum allowable gain of the amplifier for a stable system.

Khoobchandra Agrawal
Khoobchandra Agrawal
Numerade Educator

Problem 5

Automatic control of helicopters is necessary because, unlike fixed-wing aircraft which possess a fair degree of inherent stability, the helicopter is quite unstable. A helicopter control system that utilizes an automatic control loop plus a pilot stick control is shown in Figure P7.5. When the pilot is not using the control stick, the switch may be considered to be open. The dynamics of the helicopter are represented by the transfer function
$$
G(s)=\frac{25(s+0.03)}{(s+0.4)\left(s^2-0.36 s+0.16\right)} .
$$
(a) With the pilot control loop open (hands-off control), sketch the root locus for the automatic stabilization loop. Determine the gain $K_2$ that results in a damping for the complex roots equal to $\zeta=0.707$. (b) For the gain $K_2$ obtained in part (a), determine the steady-state error due to a wind gust $T_d(s)=1 / s$. (c) With the pilot loop added, draw the root locus as $K_1$ varies from zero to $\infty$ when $K_2$ is set at the value calculated in part (a). (d) Recalculate the steady-state error of part (b) when $K_1$ is equal to a suitable value based on the root locus.

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Problem 6

An attitude control system for a satellite vehicle within the earth's atmosphere is shown in Figure P7.6. The transfer functions of the system are
$$
G(s)=\frac{K(s+0.20)}{(s+0.90)(s-0.60)(s-0.10)}
$$
and
$$
G_c(s)=\frac{(s+2+j 1.5)(s+2-j 1.5)}{s+4.0} .
$$
(a) Draw the root locus of the system as $K$ varies from 0 to $\infty$. (b) Determine the gain $K$ that results in a system with a settling time (with a $2 \%$ criterion) less than 12 seconds and a damping ratio for the complex roots greater than 0.50 .

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04:03

Problem 7

The speed control system for an isolated power system is shown in Figure P7.7. The valve controls the steam flow input to the turbine in order to account for load changes $\Delta L(s)$ within the power distribution network. The equilibrium speed desired results in a generator frequency equal to $60 \mathrm{cps}$. The effective rotary inertia $J$ is equal to 4000 and the friction constant $b$ is equal to 0.75 . The steady-state speed regulation factor $R$ is represented by the equation $R \approx\left(\omega_0-\omega_r\right) / \Delta L$, where $\omega_r$ equals the speed at rated load and $\omega_0$ equals the speed at no load. We want to obtain a very small $R$, usually less than 0.10 . (a) Using root locus techniques, determine the regulation $R$ attainable when the damping ratio of the roots of the system must be greater than 0.60 . (b) Verify that the steady-state speed deviation for a load torque change $\Delta L(s)=\Delta L / s$ is, in fact, approximately equal to $R \Delta L$ when $R \leq 0.1$.

Narayan Hari
Narayan Hari
Numerade Educator
01:29

Problem 8

Consider again the power control system of Problem P7.7 when the steam turbine is replaced by a hydroturbine. For hydroturbines, the large inertia of the water used as a source of energy causes a considerably larger time constant. The transfer function of a hydroturbine may be approximated by
$$
G_t(s)=\frac{-\tau s+1}{(\tau / 2) s+1},
$$
where $\tau=1$ second. With the rest of the system remaining as given in Problem P7.7, repeat parts (a) and (b) of Problem P7.7.

Manik Pulyani
Manik Pulyani
Numerade Educator

Problem 9

The achievement of safe, efficient control of the spacing of automatically controlled guided vehicles is an important part of the future use of the vehicles in a manufacturing plant $[14,15]$. It is important that the system eliminate the effects of disturbances (such as oil on the floor) as well as maintain accurate spacing between vehicles on a guideway. The system can be represented by the block diagram of Figure P7.9. The vehicle dynamics can be represented by
$$
G(s)=\frac{(s+0.1)\left(s^2+2 s+289\right)}{s(s-0.4)(s+0.8)\left(s^2+1.45 s+361\right)} .
$$
(a) Sketch the root locus of the system. (b) Determine all the roots when the loop gain $K=K_1 K_2$ is equal to 4000.

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05:30

Problem 10

New concepts in passenger airliner design will have the range to cross the Pacific in a single flight and the efficiency to make it economical $[16,31]$. These new designs will require the use of temperature-resistant, lightweight materials and advanced control systems. Noise control is an important issue in modern aircraft designs since most airports have strict noise level requirements. One interesting concept is the Boeing Sonic Cruiser depicted in Figure P7.10(a). It would seat 200 to 250 passengers and cruise at just below the speed of sound.
The flight control system must provide good handling characteristics and comfortable flying conditions. An automatic control system can be designed for the next generation passenger aircraft.
The desired characteristics of the dominant roots of the control system shown in Figure P7.10(b) have a $\zeta=0.707$. The characteristics of the aircraft are $\omega_n=2.5, \zeta=0.30$, and $\tau=0.1$. The gain factor $K_1$, however, will vary over the range 0.02 at mediumweight cruise conditions to 0.20 at lightweight descent conditions. (a) Sketch the root locus as a function of the loop gain $K_1 K_2$. (b) Determine the gain $K_2$ necessary to yield roots with $\zeta=0.707$ when the aircraft is in the medium-cruise condition. (c) With the gain $K_2$ as found in part (b), determine the $\zeta$ of the roots when the gain $K_1$ results from the condition of light descent.

Sheh Lit Chang
Sheh Lit Chang
University of Washington
08:12

Problem 11

A computer system requires a high-performance magnetic tape transport system [17]. The environmental conditions imposed on the system result in a severe test of control engineering design. A direct-drive DC motor system for the magnetic tape reel system is shown in Figure P7.11, where $r$ equals the reel radius, and $J$ equals the reel and rotor inertia. A complete reversal of the tape reel direction is required in $6 \mathrm{~ms}$, and the tape reel must follow a step command in $3 \mathrm{~ms}$ or less. The tape is normally operating at a speed of $100 \mathrm{in} / \mathrm{s}$. The motor and components selected for this system possess the following characteristics:
$$
\begin{array}{rrr}
K_b & =0.40 & r=0.2 \\
K_p & =1 & K_1=2.0 \\
\tau_1 & =\tau_a=1 \mathrm{~ms} & K_2 \text { is adjustable. } \\
K_T /(L J) & =2.0 &
\end{array}
$$
$K_2$ is adjustable.

The inertia of the reel and motor rotor is $2.5 \times 10^{-3}$ when the reel is empty, and $5.0 \times 10^{-3}$ when the reel is full. A series of photocells is used as an errorsensing device. The time constant of the motor is $L / R=0.5 \mathrm{~ms}$. (a) Sketch the root locus for the system when $K_2=10$ and $J=5.0 \times 10^{-3}, 0<K_a<\infty$. (b) Determine the gain $K_a$ that results in a well-damped system so that the $\zeta$ of all the roots is greater than or equal to 0.60 . (c) With the $K_a$ determined from part (b), sketch a root locus for $0<K_2<\infty$.

Keshav Singh
Keshav Singh
Numerade Educator
02:11

Problem 12

A precision speed control system (Figure P7.12) is required for a platform used in gyroscope and inertial system testing where a variety of closely controlled speeds is necessary. A direct-drive DC torque motor system was utilized to provide (1) a speed range of $0.01 \%$ to $600^{\circ} / \mathrm{s}$, and (2) $0.1 \%$ steady-state error maximum for a step input. The direct-drive DC torque motor avoids the use of a gear train with its attendant backlash and friction. Also, the direct-drive motor has a high-torque capability, high efficiency, and low motor time constants. The motor gain constant is nominally $K_m=1.8$, but is subject to variations up to $50 \%$. The amplifier gain $K_a$ is normally greater than 10 and subject to a variation of $10 \%$. (a) Determine the minimum loop gain necessary to satisfy the steady-state error requirement. (b) Determine the limiting value of gain for stability. (c) Sketch the root locus as $K_a$ varies from 0 to $\infty$. (d) Determine the roots when $K_a=40$, and estimate the response to a step input.

Narayan Hari
Narayan Hari
Numerade Educator

Problem 13

A unity feedback system has the loop transfer function
$$
G_c(s) G(s)=\frac{K}{s(s+3)\left(s^2+4 s+7.84\right)} .
$$
(a) Find the breakaway point on the real axis and the gain for this point. (b) Find the gain to provide two complex roots nearest the $j \omega$-axis with a damping ratio of 0.707 . (c) Are the two roots of part (b) dominant? (d) Determine the settling time (with a $2 \%$ criterion) of the system when the gain of part (b) is used.

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Problem 14

The loop transfer function of a single-loop negative feedback system is
$$
G_c(s) G(s)=\frac{K(s+2)(s+3)}{s^2(s+1)(s+10)(s+50)} .
$$

This system is called conditionally stable because it is stable only for a range of the gain $K$ such that $k_1<K<k_2$. Using the Routh-Hurwitz criteria and the root locus method, determine the range of the gain for which the system is stable. Sketch the root locus for $0<K<\infty$.

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Problem 15

Let us again consider the stability and ride of a rider and high performance motorcycle as outlined in Problem 6.13. The dynamics of the motorcycle and rider can be represented by the loop transfer function
$$
G_c(s) G(s)=\frac{K\left(s^2+30 s+625\right)}{s(s+20)\left(s^2+20 s+200\right)\left(s^2+60 s+3400\right)}
$$

Sketch the root locus for the system. Determine the $\zeta$ of the dominant roots when $K=3 \times 10^4$.

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Problem 16

Control systems for maintaining constant tension on strip steel in a hot strip finishing mill are called "loopers." A typical system is shown in Figure P7.16.The looper is an arm 2 to 3 feet long with a roller on the end; it is raised and pressed against the strip by a motor [18]. The typical speed of the strip passing the looper is $2000 \mathrm{ft} / \mathrm{min}$. A voltage proportional to the looper position is compared with a reference voltage and integrated where it is assumed that a change in looper position is proportional to a change in the steel strip tension. The time constant $\tau$ of the filter is negligible relative to the other time constants in the system. (a) Sketch the root locus of the control system for $0<K_a<\infty$. (b) Determine the gain $K_a$ that results in a system whose roots have a damping ratio of $\zeta=0.707$ or greater. (c) Determine the effect of $\tau$ as $\tau$ increases from a negligible quantity.

Victor Salazar
Victor Salazar
Numerade Educator
03:27

Problem 17

Consider again the vibration absorber discussed in Problems 2.2 and 2.10 as a design problem. Using the root locus method, determine the effect of the parameters $M_2$ and $k_{12}$. Determine the specific values of the parameters $M_2$ and $k_{12}$ so that the mass $M_1$ does not vibrate when $F(t)=a \sin \left(\omega_0 t\right)$. Assume that $M_1=1, k_1=1$, and $b=1$. Also assume that $k_{12}<1$ and that the term $k_{12}^2$ may be neglected.

James Kiss
James Kiss
Numerade Educator

Problem 18

A feedback control system is shown in Figure P7.18. The filter $G_c(s)$ is often called a compensator, and the design problem involves selecting the parameters $\alpha$ and $\beta$. Using the root locus method, determine the effect of varying the parameters. Select a suitable filter so that the time to settle (to within $2 \%$ of the final value) is less than 4 seconds and the damping ratio of the dominant roots is greater than 0.60 .

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Problem 19

In recent years, many automatic control systems for guided vehicles in factories have been installed. One system uses a guidance cable embedded in the floor to guide the vehicle along the desired lane $[10$, $15]$. An error detector, composed of two coils mounted on the front of the cart, senses a magnetic field produced by the current in the guidance cable. An example of a guided vehicle in a factory is shown in Figure P7.19(a). We have
$$
G(s)=\frac{s^2+3.6 s+81}{s(s+1)(s+5)}
$$
and $K_a$ is the amplifier gain. (a) Sketch a root locus and determine a suitable gain $K_a$ so that the damping ratio of the complex roots is 0.707 . (b) Determine the root sensitivity of the system for the complex root $r_1$ as a function of (1) $K_a$ and (2) the pole of $G(s)$ at $s=-1$.

Lainey Roebuck
Lainey Roebuck
Numerade Educator
04:01

Problem 20

Determine the root sensitivity for the dominant roots of the design for Problem 7.18 for the gain $K=4 \alpha / \beta$ and the pole $s=-2$.

Anas Venkitta
Anas Venkitta
Numerade Educator
03:17

Problem 21

Determine the root sensitivity of the dominant roots of the power system of Problem P7.7. Evaluate the sensitivity for variations of (a) the poles at $s=-4$, and (b) the feedback gain, $1 / R$.

M Hassan Anwar
M Hassan Anwar
Numerade Educator
06:13

Problem 22

Determine the root sensitivity of the dominant roots of Problem P7.1(a) when $K$ is set so that the damping ratio of the unperturbed roots is 0.707 . Evaluate and compare the sensitivity as a function of the poles and zeros of $G_c(s) G(s)$.

Mir  Afzal
Mir Afzal
Numerade Educator
01:49

Problem 23

Repeat Problem P7.22 for the loop transfer function $G_c(s) G(s)$ of Problem P7.1(c).

Sheryl Ezze
Sheryl Ezze
Numerade Educator

Problem 24

For systems of relatively high degree, the form of the root locus can often assume an unexpected pattern. The root loci of four different feedback systems of third order or higher are shown in Figure P7.24. The open-loop poles and zeros of $K G(s)$ are shown, and the form of the root loci as $K$ varies from zero to infinity is presented. Verify the diagrams of Figure P7.24 by constructing the root loci.

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Problem 25

Solid-state integrated electronic circuits are composed of distributed $R$ and $C$ elements. Therefore, feedback electronic circuits in integrated circuit form must be investigated by obtaining the transfer function of the distributed $R C$ networks. It has been shown that the slope of the attenuation curve of a distributed $R C$ network is $10 n \mathrm{~dB} /$ decade, where $n$ is the order of the $R C$ filter [13]. This attenuation is in contrast with the normal $20 n \mathrm{~dB} /$ decade for the lumped parameter circuits. (The concept of the slope of an attenuation curve is considered in Chapter 8. If it is unfamiliar, reexamine this problem after studying Chapter 8.) An interesting case arises when the distributed $R C$ network occurs in a series-to-shunt feedback path of a transistor amplifier. Then the loop transfer function may be written as
$$
G_c(s) G(s)=\frac{K(s-1)(s+3)^{1 / 2}}{(s+1)(s+2)^{1 / 2}} .
$$
(a) Using the root locus method, determine the locus of roots as $K$ varies from zero to infinity. (b) Calculate the gain at borderline stability and the frequency of oscillation for this gain.

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Problem 26

A single-loop negative feedback system has a loop transfer function
$$
G_c(s) G(s)=\frac{K(s+2)^2}{s\left(s^2+1\right)(s+8)} .
$$
(a) Sketch the root locus for $0 \leq K \leq \infty$ to indicate the significant features of the locus. (b) Determine the range of the gain $K$ for which the system is stable. (c) For what value of $K$ in the range $K \geq 0$ do purely imaginary roots exist? What are the values of these roots? (d) Would the use of the dominant roots approximation for an estimate of settling time be justified in this case for a large magnitude of gain $(K>50)$ ?

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Problem 27

A unity negative feedback system has a loop transfer function
$$
\begin{aligned}
G_c(s) G(s) & =\frac{K\left(s^2+0.105625\right)}{s\left(s^2+1\right)} \\
& =\frac{K(s+j 0.325)(s-j 0.325)}{s\left(s^2+1\right)} .
\end{aligned}
$$

Sketch the root locus as a function of $K$. Carefully calculate where the segments of the locus enter and leave the real axis.

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01:00

Problem 28

To meet current U.S. emissions standards for automobiles, hydrocarbon (HC) and carbon monoxide (CO) emissions are usually controlled by a catalytic converter in the automobile exhaust. Federal standards for nitrogen oxides $\left(\mathrm{NO}_x\right)$ emissions are met mainly by exhaust-gas recirculation (EGR) techniques. However, as $\mathrm{NO}_{\mathrm{x}}$ emissions standards were tightened from the current limit of 2.0 grams per mile to 1.0 gram per mile, these techniques alone were no longer sufficient.

Although many schemes are under investigation for meeting the emissions standards for all three emissions, one of the most promising employs a three-way catalyst-for $\mathrm{HC}, \mathrm{CO}$, and $\mathrm{NO}_x$ emissions-in conjunction with a closed-loop engine-control system. The approach is to use a closed-loop engine control, as shown in Figure P7.28 [19,23]. The exhaust-gas sensor gives an indication of a rich or lean exhaust and compares it to a reference. The difference signal is processed by the controller, and the output of the controller modulates the vacuum level in the carburetor to achieve the best air-fuel ratio for proper operation of the catalytic converter. The loop transfer function is represented by
$$
L(s)=\frac{K s^2+12 s+20}{s^3+10 s^2+25 s} .
$$

Calculate the root locus as a function of $K$. Carefully calculate where the segments of the locus enter and leave the real axis. Determine the roots when $K=2$. Predict the step response of the system when $K=2$.

Manik Pulyani
Manik Pulyani
Numerade Educator

Problem 29

A unity feedback control system has a transfer function
$$
G_c(s) G(s)=\frac{K\left(s^2+8 s+25\right)}{s^2(s+4)} .
$$

We desire the dominant roots to have a damping ratio equal to 0.707 . Find the gain $K$ when this condition is satisfied. Show that the complex roots are $s=-4 \pm j 4$ at this gain.

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02:06

Problem 30

An RLC network is shown in Figure P7.30. The nominal values (normalized) of the network elements are $L-C=1$ and $R=2.5$. Show that the root sensitivity of the two roots of the input impedance $Z(s)$ to a change in $R$ is different by a factor of 4 .

Aja S
Aja S
Numerade Educator
03:15

Problem 31

The development of high-speed aircraft and missiles requires information about aerodynamic parameters prevailing at very high speeds. Wind tunnels are used to test these parameters. These wind tunnels are constructed by compressing air to very high pressures and releasing it through a valve to create a wind. Since the air pressure drops as the air escapes, it is necessary to open the valve wider to maintain a constant wind speed. Thus, a control system is needed to adjust the valve to maintain a constant wind speed. The loop transfer function for a unity feedback system is
$$
G_c(s) G(s)=\frac{K(s+4)}{s(s+0.16)(s+p)(s-\bar{p})},
$$
where $p=7.3+9.7831 j$. Sketch the root locus and show the location of the roots for $K=326$ and $K=1350$.

Narayan Hari
Narayan Hari
Numerade Educator

Problem 32

A mobile robot suitable for nighttime guard duty is available. This guard never sleeps and can tirelessly patrol large warehouses and outdoor yards. The steering control system for the mobile robot has a unity feedback with the loop transfer function
$$
G_c(s) G(s)=\frac{K(s+1)(s+5)}{s(s+1.5)(s+2)} .
$$
(a) Find $K$ for all breakaway and entry points on the real axis. (b) Find $K$ when the damping ratio of the complex roots is 0.707 . (c) Find the minimum value of the damping ratio for the complex roots and the associated gain $K$. (d) Find the overshoot and the time to settle (to within $2 \%$ of the final value) for a unit step input for the gain, $K$, determined in parts (b) and (c).

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05:30

Problem 33

The Bell-Boeing V-22 Osprey Tiltrotor is both an airplane and a helicopter. Its advantage is the ability to rotate its engines to $90^{\circ}$ from a vertical position for takeoffs and landings as shown in Figure P7.33(a), and then to switch the engines to a horizontal position for cruising as an airplane [20]. The altitude control system in the helicopter mode is shown in Figure P7.33(b). (a) Determine the root locus as $K$ varies and determine the range of $K$ for a stable system. (b) For $K=280$, find the actual $y(t)$ for a unit step input $r(t)$ and the percentage overshoot and settling time (with a $2 \%$ criterion). (c) When $K=280$ and $r(t)=0$, find $y(t)$ for a unit step disturbance, $T_d(s)=1 / s$. (d) Add a prefilter between $R(s)$ and the summing node so that
$$
G_p(s)=\frac{0.5}{s^2+1.5 s+0.5},
$$
and repeat part (b).

James Kiss
James Kiss
Numerade Educator

Problem 34

The fuel control for an automobile uses a diesel pump that is subject to parameter variations. A unity negative feedback has a loop transfer function
$$
G_c(s) G(s)=\frac{K(s+2)}{(s+1)(s+2.5)(s+4)(s+10)} .
$$
(a) Sketch the root locus as $K$ varies from 0 to 2000 .
(b) Find the roots for $K$ equal to 400,500 , and 600 .
(c) Predict how the percent overshoot to a step will vary for the gain $K$, assuming dominant roots. (d) Find the actual time response for a step input for all three gains and compare the actual overshoot with the predicted overshoot.

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03:39

Problem 35

A powerful electrohydraulic forklift can be used to lift pallets weighing several tons on top of 35 -foot scaffolds at a construction site. The negative unity feedback system has a loop transfer function
$$
G_c(s) G(s)=\frac{K(s+1)^2}{s\left(s^2+1\right)} .
$$
(a) Sketch the root locus for $K>0$. (b) Find the gain $K$ when two complex roots have a $\zeta$ of 0.707 , and calculate all three roots. (c) Find the entry point of the root locus at the real axis. (d) Estimate the expected overshoot to a step input, and compare it with the actual overshoot determined from a computer program.

Satpal Satpal
Satpal Satpal
Numerade Educator

Problem 36

A microrobot with a high-performance manipulator has been designed for testing very small particles, such as simple living cells [6]. The single-loop unity negative feedback system has a loop transfer function
$$
G_c(s) G(s)=\frac{K(s+1)(s+2)(s+3)}{s^3(s-1)} .
$$
(a) Sketch the root locus for $K>0$. (b) Find the gain and roots when the characteristic equation has two imaginary roots. (c) Determine the characteristic roots when $K=20$ and $K=100$. (d) For $K=20$, estimate the percent overshoot to a step input, and compare the estimate to the actual overshoot determined from a computer program.

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Problem 37

(a) Draw the root locus of the system given in Figure P7.37.
(b) Find the gain of the controller so that percentage overshoot is $10 \%$.
(c) Find the velocity error coefficient corresponding to this value.

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Problem 38

A unity feedback system has the loop transfer function
$$
G_c(s) G(s)=\frac{K(s+1)}{s(s-3)} .
$$

This system is open-loop unstable. (a) Determine the range of $K$ so that the closed-loop system is stable. (b) Sketch the root locus. (c) Determine the roots for $K=10$. (d) For $K=10$, predict the percent overshoot for a step input using Figure 5.13. (e) Determine the actual overshoot by plotting the response.

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09:51

Problem 39

High-speed trains for U.S. railroad tracks must traverse twists and turns. In conventional trains, the axles are fixed in steel frames called trucks. The trucks pivotas the train goes into a curve, but the fixed axles stay parallel to each other, even though the front axle tends to go in a different direction from the rear axle [24]. If the train is going fast, it may jump the tracks. One solution uses axles that pivot independently. To counterbalance the strong centrifugal forces in a curve, the train also has a computerized hydraulic system that tilts each car as it rounds a turn. On-board sensors calculate the train's speed and the sharpness of the curve and feed this information to hydraulic pumps under the floor of each car. The pumps tilt the car up to eight degrees, causing it to lean into the curve like a race car on a banked track.

The tilt control system is shown in Figure P7.39. Sketch the root locus, and determine the value of $K$ when the complex roots have maximum damping. Predict the response of this system to a step input $R(s)$.

Khoobchandra Agrawal
Khoobchandra Agrawal
Numerade Educator