Adaptive multiple sliding surface control for integrated missile guidance and autopilot with terminal angular constraint

Integrated guidance and control for homing missiles with terminal angular constraint is considered. A time-varying integrated guidance and control model with unmatched uncertainties is formulated. In order to solve the multiple states regulation problem of such a system, an adaptive multiple sliding surface control algorithm is developed. It is proved that the proposed feedback controller can drive the missile to intercept the target accurately with a desired terminal attitude angle, and ensure the stability of the missile dynamics simultaneously. The 6DOF nonlinear missile simulation results demonstrate the feasibility of the proposed integrated guidance and control design scheme.