Abstract
Minimum-time control is desired for non-linear spacecraft?satellite attitude systems to save on board thruster fuel. The regulatory time depends on the initial attitude of the satellite. Bang-bang control of satellite attitude can be accomplished with Fuzzy Logic Controller (FLC) using Largest of Maxima (LOM) defuzzification technique. In case of fuzzy controller, earlier studies show that minimum response time depends on span of the fuzzy controller membership functions. This paper shows how the non-linear relation between the initial attitude of satellite and spans of the fuzzy controller membership functions are optimised to achieve minimum response time by using Nelder?Mead simplex search method. A practical demonstration of fuzzy bang-bang control is demonstrated here by controlling angular position of a single-axis attitude application. The pneumatic rotary actuator is controlled in real time using Matlab-simulink xPC target environment.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
