Missile adaptive control law design method suitable for navigation precision reduction

The invention relates to a missile adaptive control law design method suitable for navigation precision reduction, and belongs to the field of controllers. The method comprises the steps of firstly establishing a six-degree-of-freedom model of a missile; secondly, introducing disturbance and uncertainty of the system into a system model; and finally, designing a control law and a self-adaptive law, and eliminating the influence of uncertain external disturbance and uncertainty of the system by introducing a self-adaptive compensation item. The method is simple in design, has better robustness for controller parameters, and can well eliminate uncertain external errors and uncertainty caused by reduction of guided missile navigation precision.