Preliminary design of sliding mode controller for angular positional tracking of an aircraft
Sliding mode controllers are known to be robust to parameter changes and capable of rejecting disturbances. Most sliding mode controllers were implemented on aircraft models that were derived based on the aircraft's body axes. The aircraft model in this paper are derived from an energy based...
| Main Authors: | , , , |
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| Format: | Proceeding Paper |
| Language: | English |
| Published: |
2009
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/14158/ http://irep.iium.edu.my/14158/1/ascc2009_jn.pdf |
| _version_ | 1848777657947258880 |
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| author | Jones, Lim Jen Nee Tan, Chee Pin Man, zhihong Akmeliawati, Rini |
| author_facet | Jones, Lim Jen Nee Tan, Chee Pin Man, zhihong Akmeliawati, Rini |
| author_sort | Jones, Lim Jen Nee |
| building | IIUM Repository |
| collection | Online Access |
| description | Sliding mode controllers are known to be robust to parameter changes and capable of rejecting disturbances.
Most sliding mode controllers were implemented on aircraft
models that were derived based on the aircraft's body axes.
The aircraft model in this paper are derived from an energy based modeling technique where the aircraft dynamics can be
defined by Euler-Lagrangian equations that makes decoupling
of aircraft dynamics simple and straightforward. It is possible to do so since these equations can be derived from the inertial axes of the aircraft instead of the aircraft's body axes. The nature of these equations makes it easy to implement the sliding mode controller on all the angular positions of the aircraft for the purpose of tracking a reference trajectory. Parameter changes and disturbances were also introduced as part of the evaluation procedure in few sets of simulations to prove how well these angular positions can be tracked. The controller designed to achieve angular positional tracking includes a nominal feedback controller and a sliding mode compensator.
The performance of the controller presented are measured
using root-mean-square error values and maximum errors for
roll, pitch and yaw. Results presented shows good tracking
performances throughout entire flight trajectory that includes a one-sided engine failure, a 90 degree turn and rotations in the pitch angle.
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| first_indexed | 2025-11-14T14:49:29Z |
| format | Proceeding Paper |
| id | iium-14158 |
| institution | International Islamic University Malaysia |
| institution_category | Local University |
| language | English |
| last_indexed | 2025-11-14T14:49:29Z |
| publishDate | 2009 |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | iium-141582012-01-09T03:17:43Z http://irep.iium.edu.my/14158/ Preliminary design of sliding mode controller for angular positional tracking of an aircraft Jones, Lim Jen Nee Tan, Chee Pin Man, zhihong Akmeliawati, Rini TJ212 Control engineering Sliding mode controllers are known to be robust to parameter changes and capable of rejecting disturbances. Most sliding mode controllers were implemented on aircraft models that were derived based on the aircraft's body axes. The aircraft model in this paper are derived from an energy based modeling technique where the aircraft dynamics can be defined by Euler-Lagrangian equations that makes decoupling of aircraft dynamics simple and straightforward. It is possible to do so since these equations can be derived from the inertial axes of the aircraft instead of the aircraft's body axes. The nature of these equations makes it easy to implement the sliding mode controller on all the angular positions of the aircraft for the purpose of tracking a reference trajectory. Parameter changes and disturbances were also introduced as part of the evaluation procedure in few sets of simulations to prove how well these angular positions can be tracked. The controller designed to achieve angular positional tracking includes a nominal feedback controller and a sliding mode compensator. The performance of the controller presented are measured using root-mean-square error values and maximum errors for roll, pitch and yaw. Results presented shows good tracking performances throughout entire flight trajectory that includes a one-sided engine failure, a 90 degree turn and rotations in the pitch angle. 2009 Proceeding Paper PeerReviewed application/pdf en http://irep.iium.edu.my/14158/1/ascc2009_jn.pdf Jones, Lim Jen Nee and Tan, Chee Pin and Man, zhihong and Akmeliawati, Rini (2009) Preliminary design of sliding mode controller for angular positional tracking of an aircraft. In: the 7th Asian Control Conference (ASCC 2009), 27-29 Aug 2009, Hong Kong. |
| spellingShingle | TJ212 Control engineering Jones, Lim Jen Nee Tan, Chee Pin Man, zhihong Akmeliawati, Rini Preliminary design of sliding mode controller for angular positional tracking of an aircraft |
| title | Preliminary design of sliding mode controller for angular positional tracking of an aircraft |
| title_full | Preliminary design of sliding mode controller for angular positional tracking of an aircraft |
| title_fullStr | Preliminary design of sliding mode controller for angular positional tracking of an aircraft |
| title_full_unstemmed | Preliminary design of sliding mode controller for angular positional tracking of an aircraft |
| title_short | Preliminary design of sliding mode controller for angular positional tracking of an aircraft |
| title_sort | preliminary design of sliding mode controller for angular positional tracking of an aircraft |
| topic | TJ212 Control engineering |
| url | http://irep.iium.edu.my/14158/ http://irep.iium.edu.my/14158/1/ascc2009_jn.pdf |