Date 29/10/13 BHARATH INSTITUTE OF ENGINEERING & TECHNOLOGY Mangalpally (V), Ibrahimpatnam Department of Aeronautical Engineering Sub: Control
Theory -Application to Flight Control System Duration: 1 Hr. Question Bank 1. Unit 3 (a) Write short notes on Root locus, Nyquist plot and Bode plot. (b) Dene Gain Margin (GM) and Phase Margin (PM) and explain how you can determine them from bode plot. (c) Write a note on determining range of gain K for stability using Bode plot. (d) Draw and explain polar plots on type-0, type-1 and type-2 systems. (e) Bring out the relevance of Bode plot from stability point of view. (f) Sketch the log magnitude bode plot of open loop transfer function G(s) = 0.75 (1 + 0.2s) s (1 + 0.16s + 0.01s2 )
Find the gain cross-over frequency of the system. (g) How does a proportional plus derivative control system improves the performance of a system? (h) What is a compensator? Describe lead-lag compensator. (i) Write short notes on notch lter and washout lter. (j) Explain Nyquist stability criteria with suitable examples. 2. Unit 4 (a) Write short note on ying quality requirements of an aircraft. (b) Write short note on reversible and irreversible ight control system. (c) Write short notes on stability augmentation, control augmentation and y by wire system. 3. Unit 5 (a) Explain the function of an autopilot of an aircraft. (b) Describe PID controller and Zeigler/Nichols method for PID controller tuning. (c) Describe displacement autopilot and roll attitude autopilot. (d) Explain in details the function of an autopilot of a stability augmenter. 4. Unit 6
(a) Describe the signicance of state-space. Dene state variable, control input and output variables in = Ax + B x y = Cx + D (b) A control system is dened by the following dierential equation
d3 y (t) dt3
= u( t )
where u is input and y is output. Write down the system in state space form = Ax + B x y = Cx + D Calculate the state transition matrix eA t of this system. 5. Unit 7 (a) A state variable formulation of a system is given by the equation
dx1 dt dx2 dt
1 0 0 3
x1 x2
1 1
; y =
1 0
x1 x2
Find the response y (t) to unit step unit. (b) Explain Controllability and Observability. (c) Consider the following matrix A= 0 2 1 3 ; B= 1 1 ; C= 0 1
Calculate the controllability and observability.
Date 29/10/13 Set-1 BHARATH INSTITUTE OF ENGINEERING & TECHNOLOGY Mangalpally (V), Ibrahimpatnam Department of Aeronautical Engineering Sub: Control Theory -Application to Flight Control System Duration: 1 Hr. 1. Write short notes on Root locus, Nyquist plot and Bode plot. 2. Write short note on ying quality requirements of an aircraft. 3. Explain the function of an autopilot of an aircraft. 4. A state variable formulation of a system is given by the equation
dx1 dt dx2 dt
1 0 0 3
x1 x2
1 1
; y =
1 0
x1 x2
Find the response y (t) to unit step unit.
Date 29/10/13 Set-2 BHARATH INSTITUTE OF ENGINEERING & TECHNOLOGY Mangalpally (V), Ibrahimpatnam Department of Aeronautical Engineering Sub: Control Theory -Application to Flight Control System Duration: 1 Hr. 1. Dene Gain Margin (GM) and Phase Margin (PM) and explain how you can determine them from bode plot. 2. Write short note on reversible and irreversible ight control system. 3. Describe PID controller and Zeigler/Nichols method for PID controller tuning. 4. A control system is dened by the following dierential equation
d3 y (t) dt3
= u( t )
where u is input and y is output. Write down the system in state space form = Ax + B x y = Cx + D Calculate the state transition matrix eA t of this system.
Date 29/10/13 Set-3 BHARATH INSTITUTE OF ENGINEERING & TECHNOLOGY Mangalpally (V), Ibrahimpatnam Department of Aeronautical Engineering Sub: Control Theory -Application to Flight Control System Duration: 1 Hr. 1. How does a proportional plus derivative control system improves the performance of a system? 2. Write short notes on stability augmentation, control augmentation and y by wire system. 3. Describe displacement autopilot and roll attitude autopilot. 4. A state variable formulation of a system is given by the equation
dx1 dt dx2 dt
1 0 0 3
x1 x2
1 1
; y =
1 0
x1 x2
Find the response y (t) to unit step unit.
Date 29/10/13 Set-4 BHARATH INSTITUTE OF ENGINEERING & TECHNOLOGY Mangalpally (V), Ibrahimpatnam Department of Aeronautical Engineering Sub: Control Theory -Application to Flight Control System Duration: 1 Hr. 1. Write short notes on notch lter and washout lter. 2. Write short notes on stability augmentation, control augmentation and y by wire system. 3. Explain in details the function of an autopilot of a stability augmenter. 4. A control system is dened by the following dierential equation
d3 y (t) dt3
= u( t )
where u is input and y is output. Write down the system in state space form = Ax + B x y = Cx + D Calculate the state transition matrix eA t of this system.
