In order to attack the top of a target at large terminal anglethe optimal guidance law with impact angle constraint is applied to control the terminal angle of the missile. Since it may occur that the target moves beyond the seekers field of viewa guidance law with an amendment part is designedi.e.introducing a part based on the optimal guidance law. The part works if the view angle exceeds the predefined value to maintain the target inside the field of viewand is turned off to apply the original guidance law if not. The new guidance law can not only retain the high angle characteristics of original soptimal guidance lawbut also deal with the view angle problem effectively. Simulation results show that it is feasible to achieve navigation with impact angle and view angle constraints by this method.