This paper proposed a sliding mode cooperative terminal guidance law to solve the problem of cooperative attack of the leader-follower missiles against a maneuvering target. The sliding mode surface was designed by taking the difference of the distance between the leader and the follower and its differentiation as the cooperative state variables， and the estimated time-to-go of the leader and the line of sight rate of the follower were introduced， so as to avoid the singularity problem. The target’s maneuvering acceleration was treated as a disturbance variable， and a switching control term utilizing its bounded nature was designed， ensuring the stability of the system and enhancing the robustness of the guidance law. Finally， digital simulations were conducted with three conditions. The results show that the guidance law proposed in this paper can achieve cooperative guidance.