Adaptive sliding-mode guidance with terminal angle constraints based on explicit space engagement model

In this paper, an explicit guidance model of space movement for air to ground missile has been built by deducing the transitions of parameters between two dimensional plane and space movement, such as velocities, angles and angular rates. Afterwards an adaptive sliding-mode guidance law is deduced on the basis of the proposed model, which satisfies the intercept angular constraints in both longitudinal plane and lateral plane. Simulations are carried out and demonstrate the effectiveness of the stated method.