Abstract: To increase penetration rate for low attitude cruise missile, a minimum deviation of the missile along the flight path must be satisfied, after the flight path plan to be finished. During the missile flight simulation, missile overload exceeds requirement when waypoint is switching and overshoot time becomes extended. To solve this problem, new missile guidance method for longitudinal and lateral aisles and command generated method were proposed, control law of missile was designed to satisfy requirement of the missile low attitude penetration. By way of terrain following and terrain avoidance (TF/TA) 6-degree of freedom simulation, performances of two guidance methods on TF/TA were compared. Simulation results shows that, use this new guidance method of longitudinal and lateral aisles and command generated method, TF/TA performance of missile is increased.