Faculty of Engineering MSc in Systems Engineering and Appe… · aerodynamic flutter may have confused read", Aviation Safety, May 2011 Issue. Barzegari, Mohammad M., Morteza Dardel,

Sahar Sadat Tavalla ID 90082 i

References

Andrighettoni, M. and Mantegazza, P., “Multi-input/multi-output adaptive active

flutter suppression for a wing model”, Journal of Aircraft, Vol. 3, pp 462-469, 1998.

Akella, M.R. and Junkins, J.L., “Structured model reference adaptive control with

actuator saturation limits”, AIAA paper 98-4472, 1998.

Albano, E. and Rodden, W.P., “A doublet-lattice method for calculating lifting

disturbances on oscillating surfaces in subsonic flows”, AIAA Journal, Vol. 7, pp

279-285, 1969.

Antony Jameson, “Aerodynamic design via control theory”, Journal of Scientific

Computing, pp 233-260, 1988.

Arkun Y., Manousiothakis B., and Putz P., “Robust Nyquist array methodology: a

new theoretical framework for analysis and design of robust multivariable feedback

design”, International Journal of Control 40, Vol. 4, pp 603- 629, 1984.

Borglund, D. and Kuttenkeuler, J., “Active wing flutter suppression using a trailing-

edge flap”, Journal of Fluids and Structures, Vol. 3, pp 271–294, 2002.

Benjamin C. Kuo, and Farid Golnaraghi, “Automatic Control Systems”, 8th

edition,

pp 511.

Burnside, Joseph E., "VNE revisited: A recent article on never-exceed speed and

aerodynamic flutter may have confused read", Aviation Safety, May 2011 Issue.

Barzegari, Mohammad M., Morteza Dardel, Alireza Fathi, and Mojtaba Ghadimi.

"Aeroelastic characteristics of cantilever wing with embedded shape memory alloys",

Acta Astronautica, 2012.

file:///C:/viewGale.aspfile:///C:/viewGale.asphttp://dx.doi.org/10.1016/j.actaastro.2012.04.023http://dx.doi.org/10.1016/j.actaastro.2012.04.023http://dx.doi.org/10.1016/j.actaastro.2012.04.023

Sahar Sadat Tavalla ID 90082 ii

Collar, A. R., and Simpson, A., “Matrices and Engineering Dynamics”, (Ellis

Horwood, Chichester), 1987.

Chad Hebert, Dave Cowan, Attar Peter J, and Carol D. Weiseman, “Aerodynamic

Flutter”, NASA Langley Research Center, 2011.

Cooper J E., “Parameter estimation methods for flight flutter testing”, Proceedings of

the 80th AGARD Structures and Materials Panel, AGARD CP-566, 1995.

Collar, A. R. and Simpson, A., “Matrices and Engineering Dynamics”, Ellis

Horwood, Chichester, 1987.

Drof., R. and Bishop R., “MODERN CONTROL SYSTEMS”, USA, Pearson Prentice

Hall, 2001.

Daochun Li, Jinwu Xiang, and Shijun Guo, “Adaptive control of a nonlinear aeroelastic

system”, Aerospace Science and Technology, Vol 15, pp 343 – 352, 2011.

Dejan D. Ivezic´, and Trajko B. Petrovic´, “New approach to milling circuit

control—robust inverse Nyquist array design”, Int. J. Miner. Process, Vol 70, pp 171

– 182, 2003.

Fanson, J.L., and Caughey, T.K., “Positive Position Feedback Control for Large

Space Structures”, AIAA Journal, 1990.

Frazer, R. A., Duncan, W. J., and Collar, A. R., “Elementary Matrices”, Cambridge

University Press, 1963.

Grujic´ M., “Intelligent control of Majdanpek flotation plant”, Minerals Engineering

7, Vol. 14, pp 689– 704, 1995.

Sahar Sadat Tavalla ID 90082 iii

Gerschgorin, S., “Uber die Abgrenzung der Eigenwerteeiner Matrix”,

Izv.Akad.Nauk.USSR Otd.Fiz.-Mat. Nauk 7, pp 749-754, 1931.

Goh, C.J. ,and Caughey, T.K., ‘‘On the Stability Problem Caused by Finite Actuator

Dynamics in the Collocated Control of Large Space Structures’’, International

Journal of Control, pp 787-802, 1985.

H. Haddadpour, and R.D. Firouz-Abadi, "Evaluation of quasi-steady aerodynamic

modeling for flutter prediction of aircraft wings in incompressible flow", Thin-Walled

Structures, 2006.

Hawkins, D.J. and McMorran, P.D., “Determination of stability regions with the

inverse Nyquist array”, Proc.IEE, Vol. 120, No. 11, pp 1445-1448,1972.

Han, J.H. and Tani, J., “Active flutter suppression of a lifting surface using piezo

electric actuation and modern control theory”, Journal of Sound and Vibration 291,

pp 706-722, 2006.

Hu, Q., ‘‘Adaptive Output Feedback Sliding-mode Manoeuvring and Vibration

Control of Flexible Spacecraft with Input Saturation’’, IET Control Theory

Application, pp 467-478, 2008.

John J. Burken, Gurbux S. Alag, and Glenn B. Gilyard, “Aeroelastic Control of

Oblique-Wing Aircraft”, NASA Technical Memorandum, California, June 1986.

Jeffrey M. Barker, Gary J. Balast, and Paul A. Bluet, “Active Flutter Suppression via

Gain-Scheduled Linear Fractional Control”, University of Minnesota, June 1999.

Jeang-Lin Chang, "Robust Output Feedback Disturbance Rejection Control by

Simultaneously Estimating State and Disturbance", Journal of Control Science and

Engineering, 2011.

http://www.sciencedirect.com/science/article/pii/S0263823106001431http://www.sciencedirect.com/science/article/pii/S0263823106001431http://dx.doi.org/10.1016/j.tws.2006.08.020http://dx.doi.org/10.1016/j.tws.2006.08.020http://dx.doi.org/10.1016/j.tws.2006.08.020http://dx.doi.org/10.1155/2011/568379http://dx.doi.org/10.1155/2011/568379http://dx.doi.org/10.1155/2011/568379

Sahar Sadat Tavalla ID 90082 iv

Kalman, R.E., “On the General Theory of Control Systems”, In Proceedings of the

First IFAC Congress on Automatic Control, Moscow, Vol 1, pp 481–

492, 1960.

Koudstaal J., Hulbert D.G., Braae, M., and Gossman G.I., “The application of a

multivariable controller to an industrial grinding circuit”, Proceedings of the 8th

Triennial World Congress, Control Science and Technology for the Progress of

Society, Vol. 22 (104– 110). IFAC, Kyoto, pp 204– 215, 1981.

Karthik Palaniappan, Pradipta Sahu, Juan Alonso, and Antony Jameson, “Active

Flutter Control using an Adjoint Method”, 44th AIAA Aerospace Sciences Meeting

and Exhibit, Reno, Nevada, Jan 2006.

Ko, J., Strganac, T.W. and Kurdila, A.J., “Stability and control of a structurally

nonlinear aeroelastic system”, Journal of Guidance, Control, and Dynamics, pp 718-

725, 1998.

Kanai K., “Trend of Active Control Technology”, 23rd

Aircraft Symposium (in

Japanese), pp 16, 1985.

Karpouzian, G. and Librescu, L., “Comprehensive model of anisotropic composite

aircraft wings suitable for aeroelastic analyses”, Journal Aircr, Vol. 3, pp 703-12,

1994.

Kehoe, M. W., “A Historical Overview of Flight Flutter Testing Proceedings of

Advanced Aeroservoelastic Testing and Data Analysis”, AGARD-CP-566, Nov

1995.

Karpouzian, G. and Librescu, L., “Non-classical effects on divergence and flutter of

anisotropic swept aircraft wings”, AIAA Journal, Vol. 4, pp 786-94, 1996.

Sahar Sadat Tavalla ID 90082 v

Librescu, L. and Marzocca, P., “Advances in the linear/nonlinear control of

aeroelastic structural systems”, Acta Mechanica, pp 147-186, 2002.

Munro, N., “Multivariable systems design using the inverse Nyquist array”, UMIST,

Manchester, 1972.

Milic R. Stojic., "Design of PI controller for multivariable feedback control system

using the inverse-Nyquist-array method", International Journal of Systems Science,

1979.

Mees, A.I., “Achieving diagonal dominance”, Systems and Control Letters, Vol. 1,

pp 155–158, 1981.

Mingli Yu, and Haiyan Hu, "Flutter control based on ultrasonic motor for a two-

dimensional airfoil section", Journal of Fluids and Structures, 2012.

Nima Mahmoodi, S., M. Ahmadian, and D. J. Inman. "Adaptive Modified Positive

Position Feedback for Active Vibration Control of Structures", Journal of Intelligent

Material Systems and Structures, 2010.

Rao, S. S., “Mechanical Vibrations”, Addison-Wesley Reading, Massachusetts,

1986.

Rosenbrock, H.H., “Reduction of System Matrices”, Electronic Letters, No. 8, pp

368, 1967.

Rosenbrock, H.H., “Approximate Between Transient and Frequency Response”,

Journal Brit.I.R.E, pp 57-64, 1958.

Rosenbrock, H.H., “Design of multivariable control systems using the inverse

Nyquist array”, No.11, pp 1929-1936, 1969.

http://dx.doi.org/10.1080/00207727908941651http://dx.doi.org/10.1080/00207727908941651http://dx.doi.org/10.1080/00207727908941651http://www.sciencedirect.com/science/article/pii/S0889974611001472http://dx.doi.org/10.1177/1045389X10361631http://dx.doi.org/10.1177/1045389X10361631http://dx.doi.org/10.1177/1045389X10361631

Sahar Sadat Tavalla ID 90082 vi

Siva Nadarajah, “The Discrete Adjoint Approach to Aerodynamic Shape

Optimization”, PhD thesis, Stanford University, 2003.

Sahar Tavalla, “Multivariable Systems and Control 2 sys-1508”, assignment

submitted to BUiD, 2011.

Theodorsen, T., “General Theory of Aerodynamic Instability and the Mechanism of

Flutter”, NACA, pp 496, 1935.

Tang Wei, Shi Zhongke, and Chen Jie, “Aircraft Flutter Modal Parameter

Identification Using a Numerically Robust Least-squares Estimator in Frequency

Domain”, College of Automation, Northwestern Polytechnical University, 2008.

Trendafilova I., “An Investigation on Vibration-based Damage Detection in an

Aircraft Wing Scaled Model”, Department of Mechanical Engineering, University of

Strathclyde, Key Engineering Materials Vols. 293-294, pp 321-328, 2005.

Theodorsen, T and Garrick, I. E., “Mechanism of flutter, a theoretical and

experimental investigation of the flutter problem”, Technical report, N.A.C.A.

Report, pp 685, 1940.

Tseng, Y. W. and Yedavalli, R. K., “Control designs of the generalized state space

system with state derivative measurement and the reciprocal state space system”, to

be submitted to IEEE Transactions on Automatic Control.

Taher Khalifa, “A Design Study for Multivariable Feedback Control System

Regulation for Aircraft Turbo-Jet Engines”, Dissertation submitted to BUiD, 2012.

Whalley, R, “Spectral Factorisation of the Transfer Matrix”, I.Mech.E. Proceedings

Vol 11, No.9, 1987.

Sahar Sadat Tavalla ID 90082 vii

Whalley, R and Ebrahimi, M, “Vibration and control of aircraft wings”, Proc.

IMechE, Part G: Journal of Aerospace Engineering, Vol 212, pp 353 - 365, 1998.

Whalley, R and Ebrahimi, M, "The impedance matrix in series", Mechanical Systems

and Signal Processing, 1999.

Whalley, R and Ebrahimi, M, “Multivariable System Regulation with Minimum

Control Effort”, Proc. IMechE, Part I: Journal of Mechanical Engineering Science,

Vol 213, No.16, pp 505 – 514, 1999.

Whalley, R and Ebrahimi, M, "Process control with minimum control effort",

Proceedings of the Institution of Mechanical Engineers Part E Journal of Process

Mechanical Engineering, 1999.

Whalley, R and Ebrahimi, M, "Process system regulation with minimum control

effort", Proceedings of the Institution of Mechanical Engineers Part E Journal of

Process Mechanical Engineering, 2000.

Whalley, R and Ebrahimi, M, "Optimum wind tunnel regulation", Proceedings of the

Institution of Mechanical Engineers Part G Journal of Aerospace Engineering, 2001.

Whalley, R and Ebrahimi, M, "Multivariable System Regulation", Proceedings of the

Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering

Science, Vol 220, No.5, pp 653 – 667, 2006.

Whalley, R and Ebrahimi, M, "Closed-loop system disturbance recovery",

Proceedings of the Institution of Mechanical Engineers Part C Journal of Mechanical

Engineering Science, 2003.

http://dx.doi.org/10.1243/0954408991529889http://dx.doi.org/10.1243/0954408991529889http://dx.doi.org/10.1243/0954408991529889http://dx.doi.org/10.1243/0954408001530092http://dx.doi.org/10.1243/0954408001530092http://dx.doi.org/10.1243/0954408001530092http://dx.doi.org/10.1243/0954410011533220http://dx.doi.org/10.1243/0954410011533220http://dx.doi.org/10.1243/095440603321919563http://dx.doi.org/10.1243/095440603321919563http://dx.doi.org/10.1243/095440603321919563

Sahar Sadat Tavalla ID 90082 viii

Whalley, R and Ebrahimi, M, "Optimum Multivariable Wind Tunnel System Control",

Proceedings of the Institution of Mechanical Engineers Part I Journal of Systems and

Control Engineering, 2005.

Whalley, R and A. Abdul-Ameer, "Warship propulsion system control", Proceedings

of the Institution of Mechanical Engineers Part C Journal of Mechanical Engineering

Science, 2012.

Waszak, M.R. and Fung, J., “Parameter Estimation and Analysis of Actuators for the

BACT Wind-Tunnel Model”, AIAA Paper No. 96-3362. 1996.

Yuan-Wei Tseng, and Rama K. Yedavalli, “Vibration Control of a Wing Box via

Reciprocal State Space Framework”, Department of Aerospace Engineering, Applied

Mechanics and Aviation, Ohio State University, Proceedings of the 1997 IEEE

International Conference on Control Applications CCA-97, October 1997.

Zhao, Y.H., “Flutter suppression of a high aspect-ratio wing with multiple control

surfaces”, Institute of Vibration Engineering Research, Nanjing University of

Aeronautics and Astronautics, Journal of Sound and Vibration, April 2009.

http://dx.doi.org/10.1243/095965105X33590http://dx.doi.org/10.1243/095965105X33590http://dx.doi.org/10.1243/095965105X33590http://dx.doi.org/10.1177/0954406211434389http://dx.doi.org/10.1177/0954406211434389http://dx.doi.org/10.1177/0954406211434389

Sahar Sadat Tavalla ID 90082 ix

Appendix

Least Effort Control Strategy

fl

ft

5.443s +29s+2502.72

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g22

-2.907s +9s+614.72

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g21

-2.907s +9s+614.72

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g12

4.743s +9s+1487.72

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g11

q2

q1

29s+2502.7

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g22

9s+614.7

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g21

9s+614.7

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g12

9s+1487.7

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g11

ft

fl

q2

q1

Figure A.1, General Open Loop Simulation Model (At zero velocity)

Figure A.2, Reduced Open Loop Simulation Model (At zero velocity)

Sahar Sadat Tavalla ID 90082 x

q2

trail ing edge

deflection

q1

leading edge

deflection

0.3521

k2

1

k1

93.9313*0.01

h2

79.5066*0.01

h1

29s+2502.7

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g22(s)

9s+614.7

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g21(s)

9s+614.7

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g12(s)

9s+1487.7

17.365s +238.86s +2.372e4s +5.46e4s+3.345e64 3 2

g11(s)

Step

s +.895s+161.52

s +25.5s+162.52

C(s)

0.3521

k2

1

k1

93.9313*0.01

h2

79.5066*0.01

h1

29s+2502.7

den(s)

g22

9s+614.7

den(s)

g21

s +.895s+161.52

s +25.5s+162.52

g2

9s+614.7

den(s)

g12

9s+1487.7

den(s)

g11

s +.895s+161.52

s +25.5s+162.52

g1

ft

fl

0.55

f2

0.55

f1

q2

T.disp

Step

-K-

P22

-K-

P21

-K-

P12

-K-

P11q1

L.disp

Figure A.3, Inner loop system block diagram with compensator Simulation

Model (At zero velocity)

Figure A.4, Outer loop system block diagram with compensator Simulation

Model (At zero velocity)

Sahar Sadat Tavalla ID 90082 xi

Nyquist Array Method

0.1

k2

0.1

k1

11

k

29s+2502.7

den(s)

g22

9s+614.7

den(s)

g21

9s+614.7

den(s)

g12

9s+1487.7

den(s)

g11

ft

fl

q2

q1

614.7

614.7

2502.7

1487.7

0.1

k2

0.1

k1

11

k

37.932s+2.2495e3

den(s)

g22

15.912s+577.1

den(s)

g21

-9.152s+361.5

den(s)

g12

25.128s+1.5453e3

den(s)

g11

ft

fl

q2

q1

614.7

614.7

2502.7

1487.7

Figure A.5, Closed Loop by Nyquist Array Method Simulation Model

(At zero velocity)

Figure A.6, Closed Loop by Nyquist Array Method Simulation Model

(At m/s)

Sahar Sadat Tavalla ID 90082 xii

0.1

k2

0.1

k1

11

k

29s+2502.7

den(s)

g22

9s+614.7

den(s)

g21

9s+614.7

den(s)

g12

9s+1487.7

den(s)

g11

ft

fl

q2

q1

Step1

Step

614.7

614.7

2502.7

1487.7

0.1

k2

0.1

k1

11

k

37.932s+2.2495e3

den(s)

g22

15.912s+577.1

den(s)

g21

-9.152s+361.5

den(s)

g12

25.128s+1.5453e3

den(s)

g11

ft

fl

q2

q1

Step1

Step

614.7

614.7

2502.7

1487.7

Figure A.7, Closed Loop by Nyquist Array Method Simulation Model for

computing disturbance rejection (At zero velocity)

Figure A.8, Closed Loop by Nyquist Array Method Simulation Model for

computing disturbance rejection (At m/s)

Sahar Sadat Tavalla ID 90082 xiii

0.1

k2

0.1

k1

11

k

29s+2502.7

den(s)

g22

9s+614.7

den(s)

g21

9s+614.7

den(s)

g12

9s+1487.7

den(s)

g11

ft

fl

E

q2

q1

Random

Number1

Random

Number

1

s

Integrator

614.7

614.7

2502.7

1487.7

u^2

u^2

u^2

u^2

Figure A.9, Closed Loop by Nyquist Array Method Simulation Model for

computing energy dissipation