Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints
The problem of attitude stabilization of a fighter aircraft is investigated in this paper. The practical aspects of a real physical system like existence of external disturbance with unknown upper bound and actuator saturation are considered in the process of controller design of this aircraft. In o...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
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Shahid Rajaee Teacher Training University
2016-07-01
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| Series: | Journal of Electrical and Computer Engineering Innovations |
| Subjects: | |
| Online Access: | https://jecei.sru.ac.ir/article_575_96512cbf1e3ce7d71ac7f9cd3bc8f97a.pdf |
| _version_ | 1828795816195653632 |
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| author | M. Bahmani T. Binazadeh |
| author_facet | M. Bahmani T. Binazadeh |
| author_sort | M. Bahmani |
| collection | DOAJ |
| description | The problem of attitude stabilization of a fighter aircraft is investigated in this paper. The practical aspects of a real physical system like existence of external disturbance with unknown upper bound and actuator saturation are considered in the process of controller design of this aircraft. In order to design a robust autopilot in the presence of the actuator saturation, the Composite Nonlinear Feedback (CNF) controller along with the Adaptive Integral Sliding Mode (AISM) controllerand the new robust controller that is called AISM-CNF control law is proposed. The CNF part of controller is used for stabilization of the nominal system and also improvement of the transient performance by considering the actuator saturation. The AISM part guarantees robustness against the model uncertainties and/or external disturbances. Since in the proposed approach, the upper bound of the uncertain terms is estimated and therefore there is no need to the prior knowledge of the upper bound of the model uncertainties. Finally, simulation results show the performance of the proposed AISM-CNF controller in term of attitude stabilization of fighter aircraft, robustness, and the good characteristics of the transient responses of the autopilot system in spite of actuator saturation and external disturbance. |
| first_indexed | 2024-12-12T04:11:27Z |
| format | Article |
| id | doaj.art-6b457eb0c1fd449eabaaf783a8ab51d0 |
| institution | Directory Open Access Journal |
| issn | 2322-3952 2345-3044 |
| language | English |
| last_indexed | 2024-12-12T04:11:27Z |
| publishDate | 2016-07-01 |
| publisher | Shahid Rajaee Teacher Training University |
| record_format | Article |
| series | Journal of Electrical and Computer Engineering Innovations |
| spelling | doaj.art-6b457eb0c1fd449eabaaf783a8ab51d02022-12-22T00:38:36ZengShahid Rajaee Teacher Training UniversityJournal of Electrical and Computer Engineering Innovations2322-39522345-30442016-07-014214915510.22061/jecei.2017.575575Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input ConstraintsM. Bahmani0T. Binazadeh1Department of Electrical and Electronic Engineering, Shiraz university of Technology, Shiraz, Iran.Department of Electrical and Electronic Engineering, Shiraz university of Technology, Shiraz, Iran.The problem of attitude stabilization of a fighter aircraft is investigated in this paper. The practical aspects of a real physical system like existence of external disturbance with unknown upper bound and actuator saturation are considered in the process of controller design of this aircraft. In order to design a robust autopilot in the presence of the actuator saturation, the Composite Nonlinear Feedback (CNF) controller along with the Adaptive Integral Sliding Mode (AISM) controllerand the new robust controller that is called AISM-CNF control law is proposed. The CNF part of controller is used for stabilization of the nominal system and also improvement of the transient performance by considering the actuator saturation. The AISM part guarantees robustness against the model uncertainties and/or external disturbances. Since in the proposed approach, the upper bound of the uncertain terms is estimated and therefore there is no need to the prior knowledge of the upper bound of the model uncertainties. Finally, simulation results show the performance of the proposed AISM-CNF controller in term of attitude stabilization of fighter aircraft, robustness, and the good characteristics of the transient responses of the autopilot system in spite of actuator saturation and external disturbance.https://jecei.sru.ac.ir/article_575_96512cbf1e3ce7d71ac7f9cd3bc8f97a.pdffighter aircraftinput constraintscomposite nonlinear feedback (cnf)adaptive integral sliding mode (aism) |
| spellingShingle | M. Bahmani T. Binazadeh Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints Journal of Electrical and Computer Engineering Innovations fighter aircraft input constraints composite nonlinear feedback (cnf) adaptive integral sliding mode (aism) |
| title | Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints |
| title_full | Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints |
| title_fullStr | Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints |
| title_full_unstemmed | Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints |
| title_short | Robust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints |
| title_sort | robust adaptive attitude stabilization of a fighter aircraft in the presence of input constraints |
| topic | fighter aircraft input constraints composite nonlinear feedback (cnf) adaptive integral sliding mode (aism) |
| url | https://jecei.sru.ac.ir/article_575_96512cbf1e3ce7d71ac7f9cd3bc8f97a.pdf |
| work_keys_str_mv | AT mbahmani robustadaptiveattitudestabilizationofafighteraircraftinthepresenceofinputconstraints AT tbinazadeh robustadaptiveattitudestabilizationofafighteraircraftinthepresenceofinputconstraints |