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1 Phase (deg); Magnitude (db) 385 Bode Diagrams 8 Gm = Inf, Pm= deg. (at rad/sec) and using the step routine on the closed loop system shows the step response to be less than the maximum allowed 2%. 51. The open-loop transfer function of a unity feedback system is G(s) = K s(1 + s/5)(1 + s/2). (a) Sketch the system block diagram including input reference commands and sensor noise. (b) Design a compensator for G(s) using Bode plot sketches so that the closed-loop system satisþes the following speciþcations: i. The steady-state error to a unit ramp input is less than.1. ii. PM 45 iii. The steady-state error for sinusoidal inputs with ω <.2 rad/sec is less than 1/25. iv. Noise components introduced with the sensor signal at frequencies greater than 2 rad/sec are to be attenuated at the output by at least a factor of 1,.

2 Phase (deg) Magnitude 386 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD (c) Verify and/or reþne your design using MATLAB including a computation of the closed-loop frequency response to verify (iv). Solution : a. The block diagram shows the noise, v, entering where the sensor would be: b. The Þrst speciþcation implies K v 1 and thus K 1. The bode plot with K =1andD = 1 below shows that there is a negative PM but all the other specs are met. The easiest way to see this is to hand plot the asymptotes and mark the constraints that the gain must be 25 at ω.2 rad/sec and the gain must be.1 for ω 2 rad/sec. 1 5 uncompensated Bode Plot

3 387 In fact, the specs are exceeded at the low frequency side, and slightly exceeded on the high frequency side. But it will be difficult to increase the phase at crossover without violating the specs. From a hand plot of the asymptotes, we see that a combination of lead and lag will do the trick. Placing the lag according to D lag (s) = (s/2+1) (s/.2+1) will lower the gain curve at frequencies just prior to crossover so that a -1 slope is more easily achieved at crossover without violating the high frequency constraint. In addition, in order to obtain as much phase at crossover as possible, a lead according to D lead (s) = (s/5+1) (s/5 + 1) will preserve the -1 slope from ω =5rad/sectoω = 2 rad/sec which will bracket the crossover frequency and should result in a healthy PM. A look at the Bode plot shows that all specs are met except the PM =44. Perhaps close enough, but a slight increase in lead should do the trick. So our Þnal compensation is D(s) = (s/2+1) (s/4+1) (s/.2+1)(s/5 + 1) with K = 1. This does meet all specs with PM =45 o exactly, as can be seen by examining the Bode plot below.

4 Phase (deg) Magnitude 388 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD 1 5 compensated Bode Plot Consider a type I unity feedback system with G(s) = K s(s +1). Design a lead compensator using Bode plot sketches so that K v =2sec 1 and PM > 4. Use MATLAB to verify and/or reþne your design so that it meets the speciþcations. Solution : Use a lead compensation : D(s) = Ts+1 αts+1, α > 1 From the speciþcation, K v =2sec 1, = K v = limsd(s)g(s) =K =2 s = K =2

5 391 Figure 6.15: Control system for Problem 54 The Matlab margin routine shows a GM =6.3 dbandpm =48 thus meeting all specs. 54. In one mode of operation the autopilot of a jet transport is used to control altitude. For the purpose of designing the altitude portion of the autopilot loop, only the long-period airplane dynamics are important. The linearized relationship between altitude and elevator angle for the longperiod dynamics is G(s) = h(s) δ(s) = 2(s +.1) s(s 2 +.1s +.25) ft deg. The autopilot receives from the altimeter an electrical signal proportional to altitude. This signal is compared with a command signal (proportional to the altitude selected by the pilot), and the difference provides an error signal. The error signal is processed through compensation, and the result is used to command the elevator actuators. A block diagram of this system is shown in Fig You have been given the task of designing the compensation. Begin by considering a proportional control law D(s) =K. (a) Use MATLAB to draw a Bode plot of the open-loop system for D(s) =K =1. (b) What value of K would provide a crossover frequency (i.e., where G = 1) of.16 rad/sec? (c) For this value of K, would the system be stable if the loop were closed? (d) What is the PM for this value of K? (e) Sketch the Nyquist plot of the system, and locate carefully any points where the phase angle is 18 or the magnitude is unity. (f) Use MATLAB to plot the root locus with respect to K, andlocate the roots for your value of K from part (b).

6 392 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD (g) What steady-state error would result if the command was a step change in altitude of 1 ft? For parts (h)and (i), assume a compensator of the form D(s) =K Ts+1 αts+1. (h) Choose the parameters K, T,andα so that the crossover frequency is.16 rad/sec and the PM is greater that 5. Verify your design by superimposing a Bode plot of D(s)G(s)/K on top of the Bode plot you obtained for part (a), and measure the PM directly. (i) Use MATLAB to plot the root locus with respect to K for the system including the compensator you designed in part (h). Locate the roots for your value of K from part (h). (j) Altitude autopilots also have a mode where the rate of climb is sensed directly and commanded by the pilot. i. Sketch the block diagram for this mode, ii. deþne the pertinent G(s), iii. design D(s) so that the system has the same crossover frequency as the altitude hold mode and the PM is greater than 5 Solution : The plant transfer function : ³ s +1 h(s) 8 δ(s) = ½.1 ³ ¾ s 2.1 s s +1

7 393 (a) SeetheBodeplot: 1 6 Magnitude Phase (deg) (b) Since G = 865 at ω =.16, K = 1 G ω=.16 =.12 (c) The system would be stable, but poorly damped. (d) PM =.39 (e) The Nyquist plot for D(jω)G(jω) : The phase angle never quite reaches 18.

8 394 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD (f) See the Root locus : The closed-loop roots for K =.12 are : (g) The steady-state error e : s =.9,.5 ± j.16 e ss = lim = s s 1 1+K h(s) δ(s) as it should be for this Type 1 system. (h) Phase margin of the plant : 1 s PM =.39 (ω c =.16 rad/sec) Necessary phase lead and 1 α : necessary phase lead = 5.39 ' 5 From Fig : = 1 α =8 Set the maximum phase lead frequency at ω c : ω = 1 = ω c =.16 = T =18 αt so the compensation is 18s +1 D(s) =K 2.2s +1

9 395 For a gain K, wewant D(jω c )G(jω c ) =1atω = ω c =.16. So evaluate via Matlab D(jω c )G(jω c ) K ωc=.16 and Þnd it = = K = 1 = Therefore the compensation is : 4 18s +1 D(s) = s +1 which results in the Phase margin : PM =52 (ω c =.16 rad/sec) 1 6 Magnitude K=4.9x1-4 DG/K G w = Phase (deg) deg G DG/K 51.4 deg

10 396 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD (i) See the Root locus : The closed-loop roots for K = are : s =.27,.74,.95 ± j.99 (j) In this case, the referance input and the feedback parameter are the rate of climb. i. The block diagram for this mode is : ii. DeÞne G(s) as: ³ s +1 h(s) G(s) = ú 8 δ(s) =.1 ³ s 2.1 s s +1 iii. By evaluating the gain of G(s) atω = ω c =.16, and setting K equal to its inverse, we see that proportional feedback : D(s) =K =.72 satisþes the given speciþcations by providing: PM =9 (ω c =.16 rad/sec)

11 397 TheBodeplotofthecompensatedsystemis: 3 Gm = Inf,Pm =9.349 deg.(at.1659 rad/sec) 2 1 Phase (deg);m agnitude (db ) For a system with open-loop transfer function c 1 G(s) = s[(s/1.4) + 1][(s/3) + 1], design a lag compensator with unity DC gain so that PM 4.Whatis the approximate bandwidth of this system? Solution : Lag compensation design : Use D(s) = Ts+1 αts+1 K=1 so that DC gain of D(s) =1. (a) Find the stability margins of the plant without compensation by plotting the Bode, Þnd that: PM = 2 (ω c =3. rad/sec) GM =.44 (ω = 2.5 rad/sec) (b) The lag compensation needs to lower the crossover frequency so that a PM ' 4 will result, so we see from the uncompensated Bode that we need the crossover at about = ω c,new =.81

12 Phase (deg) Magnitude 42 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD (c) For a low frequency gain increase of 3.16, and the pole at 3.16 rad/sec, the zero needs to be at 1 in order to maintain the crossover at ω c =31.6 rad/sec. So the lag compensator is and D 2 (s) =3.16 D 1 (s)d 2 (s) = 1 s 1 +1 s s 2 +1 s 1 +1 s 1 +1 s The Bode plots of the system before and after adding the lag compensation are 1 2 Bode Diagrams Lead only Lead and Lag (d) By using the margin routine from Matlab, we see that PM =49 (ω c =3.16 deg/sec)ec) 58. Golden Nugget Airlines had great success with their free bar near the tail of the airplane. (See Problem 5.41) However, when they purchased a much

13 43 larger airplane to handle the passenger demand, they discovered that there was some ßexibility in the fuselage that caused a lot of unpleasant yawing motion at the rear of the airplane when in turbulence and was causing the revelers to spill their drinks. The approximate transfer function for the dutch roll mode (See Section 9.3.1) is r(s) δ r (s) = 8.75(4s 2 +.4s +1) (s/.1 + 1)(s s +1) where r is the airplane s yaw rate and δ r is the rudder angle. In performing a Finite Element Analysis (FEA) of the fuselage structure and adding those dynamics to the dutch roll motion, they found that the transfer function needed additional terms that reßected the fuselage lateral bending that occurred due to excitation from the rudder and turbulence. The revised transfer function is r(s) δ r (s) = 8.75(4s 2 +.4s +1) (s/.1 + 1)(s s +1) 1 ( s2 +2ζ s ω 2 ω b b +1) where ω b is the frequency of the bending mode (= 1 rad/sec) and ζ is the bending mode damping ratio (=.2). Most swept wing airplanes have a yaw damper which essentially feeds back yaw rate measured by a rate gyro to the rudder with a simple proportional control law. For the new Golden Nugget airplane, the proportional feedback gain, K = 1, where δ r (s) = Kr(s). (3) (a) Make a Bode plot of the open-loop system, determine the PM and GM for the nominal design, and plot the step response and Bode magnitude of the closed-loop system. What is the frequency of the lightly damped mode that is causing the difficulty? (b) Investigate remedies to quiet down the oscillations, but maintain the same low frequency gain in order not to affectthequalityofthe dutch roll damping provided by the yaw rate feedback. SpeciÞcally, investigate one at a time: i. increasing the damping of the bending mode from ζ =.2 to ζ =.4. (Would require adding energy absorbing material in the fuselage structure) ii. increasing the frequency of the bending mode from ω b = 1 rad/sec to ω b = 2 rad/sec. (Would require stronger and heavier structural elements) iii. adding a low pass Þlter in the feedback, that is, replace K in Eq. (3) with KD(s) where D(s) = 1 s/τ p +1. (4) Pick τ p so that the objectionable features of the bending mode are reduced while maintaing the PM 6 o.

14 44 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD iv. adding a notch Þlter as described in Section Pick the frequency of the notch zero to be at ω b with a damping of ζ =.4 and pick the denominator poles to be (s/1 + 1) 2 keeping thedcgainoftheþlter = 1. (c) Investigate the sensitivity of the two compensated designs above (iii and iv) by determining the effect of a reduction in the bending mode frequency of -1%. SpeciÞcally, re-examine the two designs by tabulating the GM, PM, closed loop bending mode damping ratio and resonant peak amplitude, and qualitatively describe the differences in the step response. (d) What do you recommend to Golden Nugget to help their customers quit spilling their drinks? (Telling them to get back in their seats is not an acceptable answer for this problem! Make the recommendation in terms of improvements to the yaw damper.) Solution : (a) The Bode plot of the open-loop system is : 2 G m = db (at 1.3 rad/sec),pm = deg.(at rad/sec) -2 Phase (deg);m agnitude (db ) PM = 97.6 (ω =.833 rad/sec) GM = 1.28 (ω = 1. rad/sec) The low GM is caused by the resonance being close to instability.

15 45 The closed-loop system unit step response is :.9 Unit Step R esponse.6 Amplitude Tim e (sec) TheBodeplotoftheclosed-loopsystemis: 1 Magnitude Phase (deg) From the Bode plot of the closed -loop system, the frequency of the lightly damped mode is : ω ' 1 rad/sec

16 46 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD and this is borne out by the step response that shows a lightly damped oscillation at 1.6 Hz or 1 rad/sec. i. The Bode plot of the system with the bending mode damping increased from ζ =.2 to ζ =.4 is : 2 G m =7.392 db (at 1.6 rad/sec),pm = deg.(at rad/sec) -2 Phase (deg);m agnitude (db ) PM = 97.6 (ω =.833 rad/sec) GM = 7.31 (ω = 1. rad/sec) and we see that the GM has increased considerably because the resonant peak is well below magnitude 1; thus the system will be much better behaved. ii. The Bode plot of this system (ω b = 1 rad/sec = ω b =2

17 47 rad/sec) is : 2 G m = db (at 2.3 rad/sec),pm = deg.(at rad/sec) -2 Phase (deg);m agnitude (db ) PM = 97.6 (ω =.833 rad/sec) GM = 7.34 (ω = 2. rad/sec) and again, the GM is much improved and the resonant peak is signiþcantly reduced from magnitude 1. iii. By picking up τ p =1, thebodeplotofthesystemwiththelow

18 48 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD pass Þlter is : 5 G m = db (at rad/sec),pm =92.94 deg.(at.8364 rad/sec) Phase (deg);m agnitude (db ) PM = 92.9 (ω =.831 rad/sec) GM = (ω = 8.62 rad/sec) which are healthy margins and the resonant peak is, again, well below magnitude 1.

19 49 iv. The Bode plot of the system with the given notch Þlter is : 2 G m = db (at rad/sec),pm = deg.(at rad/sec) -2-4 Phase (deg);m agnitude (db ) PM = 97.6 (ω =.833 rad/sec) GM = 55.3 (ω = 99.7 rad/sec) which are the healthiest margins of all the designs since the notch Þlter has essentially canceled the bending mode resonant peak. (b) Generally, the notch Þlter is very sensitive to where to place the notch zeros in order to reduce the lightly damped resonant peak. So if you want to use the notch Þlter, you must have a good estimation of the location of the bending mode poles and the poles must remain at that location for all aircraft conditions. On the other hand, the low pass Þlter is relatively robust to where to place its break point. Evaluation of the margins with the bending mode frequency lowered by 1% will show a drastic reduction in the margins for the notch Þlter and very little reduction for the low pass Þlter. Low Pass Filter Notch Filter GM (ω = 8.62 rad/sec) 55.3 (ω = 99.7 rad/sec) PM 92.9 (ω =.831 rad/sec) 97.6 (ω =.833 rad/sec) Closed-loop bending mode damping ratio '.2 '.4 Resonant peak.87.68

20 41 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD The magnitude plots of the closed-loop systems are : M agnitude (Low Pass Filter) Magnitude (N otch Filter) The closed-loop step responses are :.9 Unit Step R esponse Low Pass Filter N otch Filter.6 Amplitude Tim e (sec) (c) While increasing the natural damping of the system would be the best solution, it might be difficult and expensive to carry out. Likewise, increasing the frequency typically is expensive and makes the

21 411 Figure 6.16: Control system for Problem 59 structure heavier, not a good idea in an aircraft. Of the remaining two options, it is a better design to use a low pass Þlter because of its reduced sensivity to mismatches in the bending mode frequency. Therefore, the best recommendation would be to use the low pass Þlter. Problems and Solutions for Section A feedback control system is shown in Fig The closed-loop system is speciþed to have an overshoot of less than 3% to a step input. (a) Determine the corresponding PM speciþcation in the frequency domain and the corresponding closed-loop resonant peak value M r.(see Fig. 6.37) (b) From Bode plots of the system, determine the maximum value of K that satisþes the PM speciþcation. (c) Plot the data from the Bode plots (adjusted by the K obtained in part (b)) on a copy of the Nichols chart in Fig and determine the resonant peak magnitude M r. Compare that with the approximate value obtained in part (a). (d) Use the Nichols chart to determine the resonant peak frequency ω r and the closed-loop bandwidth. Solution : (a) From Fig : M p.3 = PM 4 o = M r 1.5 resonant peak : M r 1.5 (b) A sketch of the asymptotes of the open loop Bode shows that a PM of = 4 o is obtained when K =8. A Matlab plot of the Bode can be used to reþne this and yields for PM =4 o. K =7.81

22 426 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD (d) A lead compensator may provide a sufficient PM, but it increases the gain at high frequency so that it violates the speciþcation above. (e) A lag compensator could satisfy the PM speciþcation by lowering the crossover frequency, but it would violate the low frequency speciþcation, W 1. (f) One possible lead-lag compensator is : s D(s) = s s s which meets all the speciþcation : K v = 1 PM = 47.7 (at ω c =12.9 rad/sec) KG = 5.45 (at ω = 1 rad/sec) > 49 KG =.32 (at ω = 1 rad/sec) <.526 The Bode plot of the compensated open-loop system D(s)G(s) is: 1 2 Magnitude Phase (deg) Problems and Solutions for Section Assume that the system G(s) = e T ds s +1,

24 428 CHAPTER 6. THE FREQUENCY-RESPONSE DESIGN METHOD Magnitude 1 D a(s)g (s) w =8.6 w =11.1 K G (s) D a(s)g (s) Phase (deg) K G (s) PM =4 deg PM =4 deg -18 deg (b) Two lead sections : With b/a = 1, the lead compensator can add the maximum phase lead : φ max = sin 1 1 a b 1+ a b = 54.9 deg(atω = 1a rad/sec) By trial and error, one of the possible compensators is : (s + 7)2 K = 1359, a=7= D b (s) = 1359 (s + 7) 2 PM = 4 (at ω c =9.6 rad/sec)

25 429 The Bode plot is shown below. Magnitude 1 D b(s)g (s) w =8.6 w =9.57 K G (s) D b(s)g (s) Phase (deg) K G (s) PM =4 deg deg (c) The statement in the text is that it should be difficult to stabilize a system with time delay at crossover frequencies, ω c & 3/T d. This problem conþrms this limit, as the best crossover frequency achieved was ω c =9.6 rad/sec whereas 3/T d = 15 rad/sec. Since the bandwidth is approximately twice the crossover frequency, the limitations imposed on the bandwidth by the time delay is veriþed. 68. Determine the range of K for which the following systems are stable: (a) G(s) =K e 4s s (b) G(s) =K e s s(s+2) Solution : (a) G(jω) K =2.54, when G(jω) K = 18 range of stability : <K<

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