Please use this identifier to cite or link to this item: https://hdl.handle.net/10356/19603
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dc.contributor.authorZhang, Wei Qiangen_US
dc.date.accessioned2009-12-14T06:17:38Z
dc.date.available2009-12-14T06:17:38Z
dc.date.copyright1997en_US
dc.date.issued1997
dc.identifier.urihttp://hdl.handle.net/10356/19603
dc.description.abstractThis thesis provides background, theory, and examples for a high performance fighter aircraft (a modified model of F-16) control design. There are mainly three parts in this thesis. The first part presents the development of a software package for flight simulation of a high performance fighter aircraft (a modified model of F-16). The package is developed using MATLAB\SIMULINK. It consists of one SIMULINK model for simulation, one SIMULINK model for trimming/linearization and some essential functions. In this part, an overview of aircraft equations of motion is demonstrated to provide a basic understanding of flight dynamics. The fully nonlinear aircraft model is used with the six-degree-of-freedom (6-DOF) equations of motion. Some additional nonlinear aircraft dynamics such as actuator saturation, auto-scheduled leading-edge flaps and engine model are also included. C MEX-files are programmed to compute aero-dynamic coefficients and engine thrust. This makes the software package more effective and efficient in flight simulation and flight dynamic analysis. The package is also a reliable and flexible tool for checking control design methodology in the next two parts.en_US
dc.format.extent168 p.
dc.language.isoen
dc.rightsNanyang Technological Universityen_US
dc.subjectDRNTU::Engineering::Electrical and electronic engineering::Control and instrumentation
dc.titleControl of a high performance fighter aircraft by using H(infinity) theory and neural-fuzzy conceptsen_US
dc.typeThesisen_US
dc.contributor.supervisorWang, Jianliangen_US
dc.contributor.schoolSchool of Electrical and Electronic Engineeringen_US
dc.description.degreeMaster of Engineeringen_US
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