The invention provides a disturbance compensation control method for a
missile pilot, and relates to the field of
guidance control. The method comprises the following steps: modeling by taking a
missile as a controlled object, and designing a corresponding traditional attitude
pilot; establishing a nonlinear kinetic equation set of the controlled object; considering the comprehensive interferencez3 to establish a
state space standard form; obtaining an input and output result of the controlled object through a nonlinear
kinematics equation set, and designing an extended
state observer; feeding back the comprehensive interference z3 and the control
gain b0 to the control output position of the traditional attitude driving instrument through the extended
state observer to obtain the active-disturbance-rejection three-loop attitude driving instrument; and performing disturbance compensation control on the
missile. The beneficial effects of the method are that: the structure and design parameters of the existing driving instrument are inherited, unmodeled disturbance and uncertain disturbance generated by parameter solidification and small disturbance
hypothesis in the missile modeling process are estimated and compensated through the active disturbance rejection extended
state observer, and comprehensive disturbance is fed back to the control output position through the extendedstate observer, so that attitude driverscope decoupling design is achieved.