Missile integrated guidance and control design with multiple constraints
In order to increase the damage efficiency of missile warhead and ensure the structural safety and flight stability,an integrated guidance and control design method considering the impact angle constraints,state constraints and control constraints is proposed based on the fixed-time stability theory and backstepping sliding mode control.An integrated design model of guidance and control with impact angle constraint is constructed in the longitudinal plane.Target maneuver,system disturbance and modeling errors are regarded as unknown bounded disturbances,and a sliding mode disturbance observer with fixed-time convergence is used for estimating and compensating the disturbances.The non-singular terminal sliding mode surface with strictly fixed-time convergence is constructed to solve impact angle constraint.A second-order instruction filter is applied to constrain the system states and control instructions,and an auxiliary system is constructed to compensate the filter tracking error.Using Lyapunov stability theory,the fixed-time convergence of closed-loop system is proved strictly.Finally,the effectiveness and superiority of the proposed integrated guidance and control algorithm are verified by comparative simulation.
integrated guidance and controlimpact angle constraintstate constraintcontrol con-straintbackstepping controlfixed-time convergence
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