Combined with strapdown inertial navigation technology

the effect of rudder technical targets on roll autopilot performance was studied systematically. According to the roll-loop characteristics

the basic relationship between the roll-loop cut-off frequency and bandwidth of rudder was analyzed; Applying the method of frequency domain analysis

on the base of comparing simplified low-order model with the high-order model

the effect of rudder bandwidth and phase angle on the roll-loop performance was Studied. In the form of second-order system step response

the maximum angular velocity of the rudder was determined contacted with the downwash torque and the rolling steady-state torque command

the roll autopilot working on the area of linearity under the condition of maneuvering flight was ensured; furthermore

Considering the restrictions on angular velocity and angle of the second-order system rudder model and the maximum disturbing torque under different total angle of attack

the roll-loop commands and the response state of roll in Saturated non-linear zone was examined

the stability of roll-loop was proved. The results showed that

for the missile time constant was

rudder surface moment efficiency was

the bandwidth of the roll autopilot needed to be more than

the bandwidth of rudder should be no less than

damping ratio of 0.6 or more. A basic method to determine the rudder technical targets when designing the roll autopilot was provided.