The invention discloses a
missile interference identification
algorithm, which belongs to the field of
missile flight test data analysis, and comprises the following steps: 1, preprocessing
angular velocity information acquired by an inertial
measurement device, including unit transformation and high-
frequency noise filtering; 2, selecting a
proper time interval according to the processed angularvelocity information, and resolving
angular acceleration information; 3, according to the
angular acceleration information and the
moment of inertia of the
missile, solving the total moment
componentof each axis under the
missile system; 4, according to the Mach number, the synthetic
attack angle, the
airflow roll angle, the
mass center, the
rudder deflection angle and other information, solvingtorque components of all shafts under a
missile system under the
free flow of the missile; and 5, subtracting the moment flowing down freely from the total moment of each shaft under the
projectile system to obtain a
projectile disturbance moment component of each shaft under the
projectile system. According to the missile interference identification
algorithm, high-frequency signals are filteredout in a targeted mode, and phase
lag is reduced as much as possible, and it is ensured that the processed
angular velocity information can be used for extracting mechanical missile interference.