Rolling angular velocity suppression method suitable for missile high-attack-angle flight maneuver

The invention discloses a rolling angular velocity suppression method suitable for missile large-attack-angle flight maneuver, and belongs to the technical field of flight control. The method provided by the invention comprises the following steps: acquiring a synthetic attack angle, an airflow rolling angle, a pitching channel rudder deflection angle, a yawing channel rudder deflection angle and a rolling channel rudder instruction of a missile; calculating an attack angle compensation coefficient according to the synthesized attack angle, and carrying out amplitude limiting processing on the compensation coefficient; calculating a sine value of an airflow rolling angle and a synthetic rudder deflection included angle; calculating an included angle compensation coefficient, and carrying out amplitude limiting processing on the compensation coefficient; calculating a rolling channel compensation rudder instruction; and determining the rolling channel compensation rudder deflection angle polarity according to