faculty of engineering msc in systems engineering and appe… · aerodynamic flutter may have...
TRANSCRIPT
-
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