Aiming at the problem of missile integrated guidance and control design, the Nussbaum gain adaptive sliding mode control method is proposed. Fully considering that the model of integrated guidance and control has the features of the channel coupling, the uncertainty of aerodynamic modeling, and the interference caused by the target maneuver and pneumatic parameters perturbation, based on the strong ability of adaptive control to identify unknown quantities, the ability of the sliding-mode control law to resist interference, and the control ability of the Nussbaum gain adaptive control to the system with uncertain coefficients, the Nussbaum gain adaptive sliding-mode control law is designed, and the stability of the system is proved. The simulation results show the effectiveness of the proposed method.