Decoupling technique for a class of rolling missile

The characteristics of channel interaction and coupling angle were deduced by the transfer function coupling with space phase caused by servo rolling; Magnus and Gyro effects were discussed separately according to their different dynamic characteristics. The deviation of the response moment angle of missile under the stable state conditions was obtained. The command compensation of the deflection angle of control moment was carried out, and the expected result was obtained. The study indicates that the Gyro effect can be weakened by appending the propriety damping loop, and more satisfied characteristic can be obtained with stable state decoupling.