Abstract: In order to reduce structural weight and costs and to improve system reliability, the rolling control system of advanced missiles is always simplified or eliminated. At the same time, missile surfaces are generally arranged with protrusions such as cable covers and hooks. These protrusions could produce a small rolling aerodynamic moment under certain flow angles, which could induce missiles to depart from their predetermined trajectory, and even lead to mission failure. Therefore, the rolling aerodynamic moment caused by protrusions should be measured and evaluated accurately before flight tests. In this paper, the test technology of continuous rolling of gas bearing to measure small rolling moment is used to complete wind tunnel tests of a tailless missile. The missile has a slenderness ratio of nearly 9, with cable covers installed on all three boost sections. Based on experimental data and aerodynamic modeling technique, a mathematical model of the variation of the rolling aerodynamic moment is established. Based on this mathematical model, a parameter identification method is used to identify the rolling aerodynamic moment coefficient induced by different cable covers from the rolling angular velocities measured in different wind tunnel tests. The results indicate that the rolling aerodynamic moment induced by cable covers of the secondary boost section, which are circumferential 180° symmetrically distributed, is most significant and ten times greater than that induced by cover on other sections. Meanwhile, the maximum value appears at transonic tests. The rolling aerodynamic moment induced by cable covers of the first boost section, which are circumferential 90° uniformly distributed, is relatively small, and its effect on the motion of missiles can be ignored.