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Mimo sliding mode control for a tailless fighter aircraft, an alternative to reconfigurable architectures
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hess, R. A. Wells, S. R. |
| Copyright Year | 2002 |
| Description | A frequency-domain procedure for the design of sliding mode controllers for multi-input, multi-output (MIMO) systems is presented. The methodology accommodates the effects of parasitic dynamics such as those introduced by unmodeled actuators through the introduction of multiple asymptotic observers and model reference hedging. The design procedure includes a frequency domain approach to specify the sliding manifold, the observer eigenvalues, and the hedge model. The procedure is applied to the development of a flight control system for a linear model of the Innovative Control Effector (ICE) fighter aircraft. The stability and performance robustness of the resulting design is demonstrated through the introduction of significant degradation in the control effector actuators and variation in vehicle dynamics. |
| File Size | 1416065 |
| Page Count | 48 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20020086714 |
| Archival Resource Key | ark:/13960/t73v4hz6f |
| Language | English |
| Publisher Date | 2002-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Robustness Mathematics Actuators Stability Control Systems Design Control Equipment Ice Tailless Aircraft Frequencies Flight Control Degradation Eigenvalues Mimo Control Systems Fighter Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
