Non-linear simulation of controller for longitudinal control augmentation system of F-16 using numerical approach

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Non-linear simulation of controller for longitudinal control augmentation system of F-16 using numerical approach

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dc.contributor.author Rachman, Endri
dc.contributor.author Jaam, Jihad M.
dc.contributor.author Hasnah, Ahmad
dc.date.accessioned 2009-12-30T07:32:27Z
dc.date.available 2009-12-30T07:32:27Z
dc.date.issued 2003-09-25
dc.identifier.citation Volume 164, Issues 1-4, 2 August 2004, Pages 47-60 en_US
dc.identifier.uri http://dx.doi.org/10.1016/j.ins.2003.09.013
dc.identifier.uri http://hdl.handle.net/10576/10581
dc.description.abstract The non-linear simulation of controller for automatic flight control system is an essential part of the complete control design process. After using the linear approach in the design and simulation of the controller (control laws), it is important to simulate the controller on the non-linear real aircraft model. This simulation allows us to evaluate its functional performance during the real-time flight on the computer. The results of that process are used to determine whether the designed controller meets the design requirement and objective or not. The paper deals with application of numerical method fourth-order Runge–Kutta to simulate the function of the longitudinal-CAS controller that is embedded into the non-linear, six degree of freedom model of fighter F-16. A computer program is made to implement the numerical approach and to illustrate the result of that simulation on the computer. en_US
dc.language.iso en en_US
dc.subject Numerical method en_US
dc.subject Non-linear simulation en_US
dc.subject Control augmentation system en_US
dc.title Non-linear simulation of controller for longitudinal control augmentation system of F-16 using numerical approach en_US
dc.type Article en_US

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