Abstract: To address the problem of the attacking accuracy degradation resulting from the jitters of the line of the sight angle and the angular velocity in the vibration environment, the guidance law with anti-interference ability and impact angle constraint is investigated. The relative motion equations between aircraft and target are established. The guidance law with impact angle constraint is obtained by using the variable structure control theory, with introduction of the vibration components of the angle of the line of sight and the angular velocity. The simulation comparative analysis of the proposed guidance law and a modified proportional guidance is made. It is demonstrated that in attacking the fixed targets, both guidance laws can meet the requirements of the missing distance and angle constraint. In attacking maneuvering targets, the attack performance of the proposed guidance law is better than the modified proportional guidance law and the control quantity can response faster when the angular velocity of the line of sight changes.