Missile rudder fault-tolerant control method based on analytical redundancy

The invention discloses a missile rudder fault-tolerant control method based on analytical redundancy. The method comprises the following steps: step I, judging whether a missile rudder has faults or not, and judging that the rudder has faults when difference between a rudder order and rudder feedback of certain rudder exceeds a predetermined error range; step II, controlling a pitching channel of a missile, and regulating the rudder with faults to a longitudinal plane of a missile shaft coordinate system by virtue of rolling movement of the missile; and step III, re-distributing each rudder deviation by utilizing a + type layout rudder deviation synthesis and distribution formula, thereby realizing fault-tolerant control. According to the missile rudder fault-tolerant control method based on analytical redundancy, the application range, in fault-tolerant control, of a redundancy analyzing method is expanded; the method is applicable no matter the missile rudder adopts + type layout or x type layout; the method can be adopted to sufficiently give full play to control capacity of the missile pitching channel, so that after certain rudder has faults, the capacity of continuously completing an attack task of the missile is maximized.