Automat Control of the Aircrafts- Lateral Movement using the Dynamic Inversion
The paper presents a new system for the automat
control of the aircrafts- flight in lateral plane using the cinematic
model and the dynamic inversion. Starting from the equations of the
aircrafts- lateral movement, the authors use two axes systems and
obtained a control law that cancels the lateral deviation of the flying
objects from the runway line. This system makes the aircrafts-
direction angle to follow the direction angle of the runway line.
Simulations in Matlab/Simulink have been done for different
aircraft-s initial points and direction angles. The inconvenience of
this system is the long duration of the “transient regime". That is why
this system can be used independently, but the results are not very
good; thus, it can be a part (subsystem) of other systems. The main
system that cancels the lateral deviation from the runway line is
based on dynamic inversion and uses, as subsystem, the control
system for the lateral movement using the cinematic model. Using
complex Matlab/Simulink models, the authors obtained the time
evolution of the direction angle and the time evolution of the aircraft
lateral deviation with respect to the runway line, for different values
of the initial direction angle and for different wind types. The system
has a very good behavior for all initial direction angles and wind
types.
[1] M. Niculescu, "Lateral Track control Law for Aerosonde UAV". AIAA
no. 2001-0016, pp. 1-11, 2001, 39th AIAA Aerospace Science Meeting
and Exhibit, 8-11 January 2001, Reno.
[2] Mc.L. Donald, Automatic Flight Control Systems. Prentice Hall
Publisher, 1990, 593 pp.
[3] V. Ricny, J. Mikulec, "Measuring flying object velocity with CCD
sensors". IEEE Aerospace and Electronic Systems Magazine, vol.9,
Issue 6, pp. 3-6, June 1994.
[4] B. Gollomp, "The angle of attack". IEEE Instrumentation &
Measurement Magazine, vol.4, Issue 1, pp. 57-58, 2001.
[5] M. Lungu, Sisteme de conducere a zborului. Sitech Publisher, 2008.
[6] Mackunis, P.M. Patre, M.K. Kaise, W.E. Dixon, "Asymptotic Tracking
for Aircraft via Robust and Adaptive Dynamic Inversion Methods",
IEEE Transactions on Control Systems and Technology, vol. 18, no.6,
2010.
[7] N.A. Denison, Automated Carrier Landing of an Unmanned Combat
Aerial Vehicle Using Dynamic Inversion, Master's thesis, June 2007.
[8] H.B. Chen, S.G. Zhang, "Robust dynamic inversion flight control law
design", 2nd International Symposion on Systems and Control in
Aerospace and Astronautics, Shenzhen, December 2008.
[9] A.J. Calise, R.T. Rysdyk, "Adaptive Model Inversion Flight Control for
Tiltrotor Aircraft", AIAA Guidance, Navigation and Control, vol. 22, pp.
402-407, 1999.
[10] C. Huang, Q. Shao, P. Jin, Z. Zhu, P. Luoyang, "Pitch Attitude
Controller Design and Simulation for a Small Unmanned Aerial
Vehicle". International Conference on Intelligent Human-Machine
Systems and Cybernetics, IHMSC '09, Hangzhou, Zhejiang, 26-27 Aug.
2009, pp. 58-61.
[11] S. Santos, N. Oliveira, "Test platform to pitch angle using hardware in
loop". 39th IEEE Frontiers in Education Conference, FIE '09, San
Antonio, 18-21 Oct. 2009, pp. 1-5.
[12] A.A. Pashilkar, N. Sundararajan, P.A. Saratchandran, "Fault-Tolerant
Neural Aided Controller for Aircraft Auto-Landing". Aerospace Science
and Technology, vol.10, Issue 1. 2006, pp. 49-61.
[13] V. Kargin, Design of An Autonomous Landing Control Algorithm for A
Fixed Wing UAV. MS Thesys, Middle East Technical University,
Ankara, Turkey, 2007.
[1] M. Niculescu, "Lateral Track control Law for Aerosonde UAV". AIAA
no. 2001-0016, pp. 1-11, 2001, 39th AIAA Aerospace Science Meeting
and Exhibit, 8-11 January 2001, Reno.
[2] Mc.L. Donald, Automatic Flight Control Systems. Prentice Hall
Publisher, 1990, 593 pp.
[3] V. Ricny, J. Mikulec, "Measuring flying object velocity with CCD
sensors". IEEE Aerospace and Electronic Systems Magazine, vol.9,
Issue 6, pp. 3-6, June 1994.
[4] B. Gollomp, "The angle of attack". IEEE Instrumentation &
Measurement Magazine, vol.4, Issue 1, pp. 57-58, 2001.
[5] M. Lungu, Sisteme de conducere a zborului. Sitech Publisher, 2008.
[6] Mackunis, P.M. Patre, M.K. Kaise, W.E. Dixon, "Asymptotic Tracking
for Aircraft via Robust and Adaptive Dynamic Inversion Methods",
IEEE Transactions on Control Systems and Technology, vol. 18, no.6,
2010.
[7] N.A. Denison, Automated Carrier Landing of an Unmanned Combat
Aerial Vehicle Using Dynamic Inversion, Master's thesis, June 2007.
[8] H.B. Chen, S.G. Zhang, "Robust dynamic inversion flight control law
design", 2nd International Symposion on Systems and Control in
Aerospace and Astronautics, Shenzhen, December 2008.
[9] A.J. Calise, R.T. Rysdyk, "Adaptive Model Inversion Flight Control for
Tiltrotor Aircraft", AIAA Guidance, Navigation and Control, vol. 22, pp.
402-407, 1999.
[10] C. Huang, Q. Shao, P. Jin, Z. Zhu, P. Luoyang, "Pitch Attitude
Controller Design and Simulation for a Small Unmanned Aerial
Vehicle". International Conference on Intelligent Human-Machine
Systems and Cybernetics, IHMSC '09, Hangzhou, Zhejiang, 26-27 Aug.
2009, pp. 58-61.
[11] S. Santos, N. Oliveira, "Test platform to pitch angle using hardware in
loop". 39th IEEE Frontiers in Education Conference, FIE '09, San
Antonio, 18-21 Oct. 2009, pp. 1-5.
[12] A.A. Pashilkar, N. Sundararajan, P.A. Saratchandran, "Fault-Tolerant
Neural Aided Controller for Aircraft Auto-Landing". Aerospace Science
and Technology, vol.10, Issue 1. 2006, pp. 49-61.
[13] V. Kargin, Design of An Autonomous Landing Control Algorithm for A
Fixed Wing UAV. MS Thesys, Middle East Technical University,
Ankara, Turkey, 2007.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:51013", author = "Mihai Lungu and Romulus Lungu and Lucian Grigorie", title = "Automat Control of the Aircrafts- Lateral Movement using the Dynamic Inversion", abstract = "The paper presents a new system for the automat
control of the aircrafts- flight in lateral plane using the cinematic
model and the dynamic inversion. Starting from the equations of the
aircrafts- lateral movement, the authors use two axes systems and
obtained a control law that cancels the lateral deviation of the flying
objects from the runway line. This system makes the aircrafts-
direction angle to follow the direction angle of the runway line.
Simulations in Matlab/Simulink have been done for different
aircraft-s initial points and direction angles. The inconvenience of
this system is the long duration of the “transient regime". That is why
this system can be used independently, but the results are not very
good; thus, it can be a part (subsystem) of other systems. The main
system that cancels the lateral deviation from the runway line is
based on dynamic inversion and uses, as subsystem, the control
system for the lateral movement using the cinematic model. Using
complex Matlab/Simulink models, the authors obtained the time
evolution of the direction angle and the time evolution of the aircraft
lateral deviation with respect to the runway line, for different values
of the initial direction angle and for different wind types. The system
has a very good behavior for all initial direction angles and wind
types.", keywords = "Direction angle, Dynamic inversion, Lateraldeviation, Lateral movement", volume = "5", number = "7", pages = "1203-8", }