In order to solve the problem that the attack missile needs to avoid the defensive missile launched by the Highly dynamic fighter aircraft and intercept which at a specific angle, in the attack missile-fighter aircraft-defensive missile three body games. A novel guidance method of attack missile based on differential countermeasure theory is proposed in this paper. The relative dynamics model of the three-body game is established first, and the three-body game model is transformed into a coupling solution problem of the guidance law in two one-to-one game scenarios considering the interception of the target by the attack missile and the evasion of the attack missile against the defensive missile. In addition, considering the angle constraint of the attack missile in the interception process, the optimal guidance law of the attack missile is developed using the matrix Riccati differential equation. In order to verify the reliability of the proposed guidance law, the numerical simulation is provided, the results show that the guidance law proposed can intercept the maneuvering fighter aircraft at a specific attack angle while avoiding the interception of defensive missiles, which verifies the feasibility of the method.