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In this paper, the idea of fuzzy model reference learning control(FMRLC) technique for missile autopilot design is introduced. This controller utilizes a learning mechanism, which observes the plant outputs and adjusts the rules in a direct fuzzy controller, so that the overall system behaves like a "reference model" which characterizes the desired(More)
The difficulties in designing an effective load control missile autopilot arise from highly nonlinear and non-minimum phase plant characteristics because the missile acceleration is regarded as output. To avoid the instability problem associated with unstable zero dynamics, a modified second order sliding mode controller was proposed through reconstruction(More)
Gain scheduling controller was designed to deal with the aerodynamic variation of a winged large-airspace-maneuvering missile. The missile body equations were simplified as time-varying linear transfer functions by normal trajectory calculation. Taking height as operating condition, gain scheduling compensated for the aerodynamic uncertainty. While(More)
An approach to integrated guidance/autopilot design for missiles against maneuvering targets on the sea is studied. When the integrated guidance/autopilot model of the yaw plane is formulated, the guidance/control law is designed based on the backstepping idea and variable structure control theory. For the unavailable information of the maneuvering target,(More)
In this paper, a novel adaptive fuzzy sliding mode controller for BTT missile is proposed, which incorporates the auto-tuning fuzzy logic system to sliding-mode control, the influence of the uncertainty of parameters can be alleviated. Besides, Lyapunov stability theorem is used to prove the stability of the system and the adaptive laws are deduced which(More)
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