Abstract:

A novel differential geometric guidance law (DGG) of zeroing the sight line rate is derived in intercepting the maneuvering target. Firstly, based on the differential geometric theory the relatively kinematics model between missile and target is built after analyzing the relative motion relation. Secondly, considering the disturbance to the nonlinear affined system, the secondorder sliding controller is proposed, the stability and finite time convergence of the controller are analyzed. Thirdly, taking the target maneuver as disturbance, the novel differential guidance law is derived based on the secondorder sliding controller. In order to overcome the information loss caused by decoupling condition, the measurement method curvature command and torsion command is derived based on the Liegroup theory, the capture condition of the differential geometric guidance law is researched to overcome the singularity accruing in the process of intercepting. Finally, simulation results shows that, compared with the nonlinear differential geometric guidance law, the designed differential geometric law has higher guidance precision, the intercept time is shorter and the load is flatter, so the designed guidance law improves the guidance properties greatly.