Determination of Q and R Matrices for Optimal Pitch Aircraft Control
In this paper, the process of obtaining Q and R
matrices for optimal pitch aircraft control system has been described.
Since the innovation of optimal control method, the determination of
Q and R matrices for such system has not been fully specified. The
value of Q and R for optimal pitch aircraft control application, have
been simulated and calculated. The suitable results for Q and R have
been observed through the performance index (PI). If the PI is small
“enough", we would say the Q & R values are suitable for that
certain type of optimal control system. Moreover, for the same value
of PI, we could have different Q and R sets. Due to the rule-free
determination of Q and R matrices, a specific method is brought to
find out the rough value of Q and R referring to rather small value of
PI.
[1] G. F. Franklin, D. J. Powell, and A. E. Naeini, Feedback Control of
Dynamic Systems. New Jersey, The United States of America: Pearson
Prentice Hall, Pearson Education, Inc, 2006.
[2] J. L. Meriam, and L. G. Kraige, Engineering Mechanics Dynamics. The
United States of America: John Wiley & Soms, Inc, 2003.
[3] D. S. Naidu, Optimal Control Systems. The United States of America:
CRC Press LLC, 2003.
[4] R. C. Nelson, Flight Stability and Automatic Control. The McGraw-Hill
Companies, Inc, 1998.
[5] K. Ogata, Discrete Time Control Systems. New Jersey, The United
States of America: Prentice-Hall, 1995.
[6] K. Ogata, Modern Control Engineering. New Jersey: Prentice-Hall, Inc,
2002.
[7] S. M. Shinners, Advanced Modern Control System Theory and Design.
John Wiley & Sons, Inc, 1998.
[8] N. Popovich, P. Yan, Optimal Digital Pitch Aircraft Control,
InternationalConference, ICCESSE 2010, Singapore, December 18-20,
2010.
[1] G. F. Franklin, D. J. Powell, and A. E. Naeini, Feedback Control of
Dynamic Systems. New Jersey, The United States of America: Pearson
Prentice Hall, Pearson Education, Inc, 2006.
[2] J. L. Meriam, and L. G. Kraige, Engineering Mechanics Dynamics. The
United States of America: John Wiley & Soms, Inc, 2003.
[3] D. S. Naidu, Optimal Control Systems. The United States of America:
CRC Press LLC, 2003.
[4] R. C. Nelson, Flight Stability and Automatic Control. The McGraw-Hill
Companies, Inc, 1998.
[5] K. Ogata, Discrete Time Control Systems. New Jersey, The United
States of America: Prentice-Hall, 1995.
[6] K. Ogata, Modern Control Engineering. New Jersey: Prentice-Hall, Inc,
2002.
[7] S. M. Shinners, Advanced Modern Control System Theory and Design.
John Wiley & Sons, Inc, 1998.
[8] N. Popovich, P. Yan, Optimal Digital Pitch Aircraft Control,
InternationalConference, ICCESSE 2010, Singapore, December 18-20,
2010.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:59010", author = "N. Popovich and P. Yan", title = "Determination of Q and R Matrices for Optimal Pitch Aircraft Control", abstract = "In this paper, the process of obtaining Q and R
matrices for optimal pitch aircraft control system has been described.
Since the innovation of optimal control method, the determination of
Q and R matrices for such system has not been fully specified. The
value of Q and R for optimal pitch aircraft control application, have
been simulated and calculated. The suitable results for Q and R have
been observed through the performance index (PI). If the PI is small
“enough", we would say the Q & R values are suitable for that
certain type of optimal control system. Moreover, for the same value
of PI, we could have different Q and R sets. Due to the rule-free
determination of Q and R matrices, a specific method is brought to
find out the rough value of Q and R referring to rather small value of
PI.", keywords = "Aircraft, control, digital, optimal, Q and R matrices", volume = "5", number = "2", pages = "399-7", }