Abstract
Launch vehicle attitude control is a complex nonlinear problem that is compounded by several internal and external factors such as modeling uncertainties, fuel sloshing and unstable aerodynamics. An anti-interference attitude controller of launch vehicle based on fuzzy logic system (FLS) and proportional-differential (PD) control is proposed to attenuate the effect of parameter variation and disturbances on attitude control accuracy and stability. The FLS is designed to estimate and compensate impact of parametric uncertainties and disturbances, when used in conjunction with a proportional derivative (PD) controller offers improved the attitude control performance when encountering uncertainty and external disturbances. Further, the comparison simulation of the FLS augmented PD controller with a traditional PD controller is done. The results show that the controller exhibits better dynamic performance, stronger robustness.
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