Adaptive proportional navigation with terminal angular constraint

A missile motion equation with terminal angular constraint was derived and then adaptive proportional guidance laws adopting adaptive navigation constant were designed to realize effective interception of maneuvering target with certain terminal angular constraint.That is through particular derivation of missile-target motion model and the geometry relationships of angular constraint,an adaptive adjustable function was derived and then the adaptive proportional guidance law based on missile kinematics was formed with feedback form.It is proven that the proposed guidance law could meet the requirements of successful interception with arbitrary attack angle.Another adaptive proportional guidance law based on realistic model was derived after revising the previous law.Simulations were made for air-to-ground and ground-to-ground missiles in order to display the fundamental advantages and practical values.Simulation results show that the proposed guidance laws have better guidance effect and could offer some references for engineering application.