Abstract: Abstract： In view of the phenomenon that the solar wings of multiple MEO navigation satellites have obvious interference torque after deployment, which has certain influence on the stability control of the satellite, this paper presents the calculation method of interference torque according to the dynamic model, attitude, angular velocity and the change of reaction wheel speed. According to the telemetry data of several satellites in orbit, the interference moment produced during deflation is obtained. Using this interference moment for simulation, the results of the satellite simulator are basically the same as those in orbit. This study is helpful for optimizing the process of satellite flight control and guiding the design of satellite exhaust hole.

Key words: Keywords： solar wing, airbleed, disturbance torque, in orbit